2026-05-16T15:51:23Z https://ejournal.brin.go.id/ijoa/oai

oai:ejournal.brin.go.id:article/27 2025-10-03T07:30:21Z ijoa:ART

Impact Point Dispersion Prediction for 300 mm R-Han 300 Artillery Rocket Riyadl, Ahmad Robertus Heru TriHarjanto Pujo Widodo impact point dispersion Monte Carlo simulation R-Han 300 The effectiveness of artillery rocket in battlefield is the determined by its impact point dispersion, which may occur due to manufacturing and measurement inaccuracy, initial launch perturbations and atmospheric conditions. Therefore, the objective of this study is to establish model that could predict the impact point dispersion of R-Han 300 rocket using Monte Carlo method. Generic rocket of 6 Degree-of-Freedom model was implemented to investigate the impact point. Initially two simulations with 1000 iterations were carried out, first to study the effect of value uncertainty of every parameter on the impact point dispersion at launch elevation angle 50 degrees, second to study the impact point dispersion caused by value uncertainty of all the parameters at launch elevation angles ranging from 30 to 70 degrees. The second simulation is then repeated with 10000 iterations. This study showed that the dispersion increases as the launch elevation angle increases, except around the optimal launch elevation angle that give the farthest range. Monte Carlo simulation with 10000 iterations showed a better normal distributed data then the simulation with 1000 iterations, but the maximum difference in value of CEP resulted from both simulations is very small, which is 3.16%. BRIN Publishing 2023-11-24 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/27 10.55981/ijoa.2023.27 Indonesian Journal of Aerospace; Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace; 51-64 3032-0895 10.55981/ijoa.v21i1 eng https://ejournal.brin.go.id/ijoa/article/view/27/1740 Copyright (c) 2023 Ahmad Riyadl, Robertus Heru TriHarjanto, Pujo Widodo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/38 2025-10-03T07:30:21Z ijoa:ART

Design of Mini Turbojet Engine Combustion Chamber Liner With 200N Static Thrust Santoso, Rais Ryacudu Wuwung, Vicky Annisa, Reina Fadjrin Nurul Kartanegara, Radi Suradi Mini turbojet liner design recirculation zone air mass flow pressure loss Design of mini turbojet engine with 200N static thrust at an air mass flow of 0.55kg/s, requiring annular type combustion chamber with liner capability of dividing the air mass flow in the primary zone by 20%, secondary zone 30%, dilution zone 50%, and with 4%- 10% pressure loss. In the primary zone, it is necessary to have a recirculation zone that will become a stable combustion place. Liner geometry is obtained by analytical and empirical calculations, that is validated by numerical simulations at cold flow steady conditions. Analytical and empirical calculations resulting in the primary, secondary, and dilution zone respectively: the hole diameter: 2.153mm, 2.503mm, 5.005mm; number of holes: 44, 52, 44 holes; the distance of hole from inlet liner: 28.5mm, 47.5mm, 113.6 mm; air mass flow rates: 19.4%, 29.6%, 50%, and the pressure loss of the combustion chamber is 4%. The numerical simulation is performed by using the turbulent k-e model (extended wall) and has a difference resulted with analytical and empirical calculations on mass flow in the primary, secondary, and dilution zone: 3.44%, 9.09%, 8.88%, and the pressure drop is 10.86%. The recirculation zone that is fulfil injector placement criteria formed in the primary zone at the longitudinal cross-section position (q) from 32.72o to 360o with 32.73o in increment, with horizontal (H) and vertical (V) distance from inner liner wall are varies from 34 to 40 mm for H, and from 35 to 43 mm for V with outer recirculation tangential velocity variation from 43 to 60 m/s. BRIN Publishing 2023-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/38 10.55981/ijoa.2023.38 Indonesian Journal of Aerospace; Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace; 65-82 3032-0895 10.55981/ijoa.v21i2 eng https://ejournal.brin.go.id/ijoa/article/view/38/4817 Copyright (c) 2023 Rais Ryacudu Santoso, Vicky Wuwung, Reina Fadjrin Nurul Annisa, Radi Suradi Kartanegara https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/39 2025-10-03T07:30:21Z ijoa:ART

FEM Modal Analysis of Blades Number Effect in UAV Propellers Ruseno, Neno Modal analysis UAV Propeller Propeller Blades Eigen Frequency Finite Element Method The propeller is one of the most important components in an Unmanned Aerial Vehicle (UAV) because it produces the thrust force. However, its structural strength is affected by the vibration phenomenon. The modal analysis can be used to study the dynamic behavior of mechanical structures under dynamic vibration. This study aims to analyze the vibration characteristics of UAV propellers in terms of propeller blade numbers using modal analysis. The propeller configurations used are two, three, and four blades. The Finite Element Method (FEM) is used to calculate the eigen frequencies of the system. The ANSYS Workbench is selected as the FEM software to simulate the study. The result shows that the propeller with 3 blades has the highest eigen frequency compared to the propeller with 2 and 4 blades which could make it preferable for UAV operations BRIN Publishing 2024-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/39 10.55981/ijoa.2024.39 Indonesian Journal of Aerospace; Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace; 1-12 3032-0895 10.55981/ijoa.v22i1 eng https://ejournal.brin.go.id/ijoa/article/view/39/8895 Copyright (c) 2024 Neno Ruseno https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/116 2025-10-03T07:30:21Z ijoa:ART

Integrated Numerical Investigation on the Aerodynamics Characteristic and Vortex Development of Airfoil using Spalart-Allmaras Model Dinaryanto, Okto Jalaali, Bahrul Hisyam, Muhammad Wibowo, Teguh aerodynamics CFD turbulent In this paper, the numerical simulation successfully obtained good results in analyzing fluid flow over the airfoil. Detailed explanations of simulation steps were also presented. The flow characteristics over three airfoil models were numerically simulated in this work: NACA0021, NACA2409, NACA2409+Fowler flap. The reliable Spalart-Allmaras (S-A) turbulent model was used and validated using reported data from experimental in terms of lift and drag coefficients. In this regard, the discrepancies of less than 10% were obtained for both coefficients, respectively. The boundary layer separation, vortex development, and air separation were clearly captured. The results of symmetric airfoil showed that the vortex shedding regimes occurred at α = 8o, and the stall critical-angle was about 14o. The value was higher for the NACA2409, where the airflow exhibited a relatively more stable behavior. Moreover, it is evident that flap addition altered lift-drag characteristics. The value of the lift-to-drag ratio increased due to the increase of  Cl and the reduction of  Cd. The parametric study was done on the α and flap deflection angle to attain the desirable airfoil configuration. The maximum result of airfoil configuration was obtained on the NACA2409 at α = 12o with 100 flap deflection angle while it enhanced the lift coefficient by about 54%. This result strengthens the robustness of the S-A turbulence model and projects the use of the S-A model for dealing with the aerodynamics analysis. This study is beneficial for initial aircraft design on the aerodynamics aspect of a wing. BRIN Publishing 2023-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/116 10.55981/ijoa.2023.116 Indonesian Journal of Aerospace; Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace; 25-38 3032-0895 10.55981/ijoa.v21i1 eng https://ejournal.brin.go.id/ijoa/article/view/116/499 Copyright (c) 2023 Okto Dinaryanto, Bahrul Jalaali, Muhammad Hisyam, Teguh Wibowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/272 2025-10-03T07:30:22Z ijoa:ART

A Study on Lug Structure at Fuselage - Wing Joint of an Unmanned Aerial Vehicle Using Finite Element Method Cahya, Fadli Pramana, Nurhadi Chairunnisa Adhynugraha, Muhammad Ilham Aribowo, Agus Nurrohmad, Abian UAV lug aluminum material finite element strain criteria Research on structural analysis of an unmanned aerial vehicle (UAV) is carried out. The primary material used in most structures is carbon composite. Having a high aspect ratio wing, the lugs connecting the wing and fuselage are likely to experience maximum forces during flight tests. In predicting the occurrence of deformation and stress, the finite element method is used by applying max./min. strain criteria to evaluate the structural integrity of composite wings due to the load applied on aluminum-based lugs. The evaluation shows that the current wing configuration has good structural integrity. An optimization approach is also carried out to obtain more optimum results. BRIN Publishing 2024-08-23 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/272 10.55981/ijoa.2023.272 Indonesian Journal of Aerospace; Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace; 133-146 3032-0895 10.55981/ijoa.v21i2 eng https://ejournal.brin.go.id/ijoa/article/view/272/4823 Copyright (c) 2024 Fadli Cahya, Nurhadi Pramana, Chairunnisa, Muhammad Ilham Adhynugraha, Agus Aribowo, Abian Nurrohmad https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/286 2025-10-03T07:30:22Z ijoa:ART

A Comparison of Vacuum Infusion, Vacuum Bagging, and Hand Lay-Up Process on The Compressive and Shear Properties of GFRP Materials Abdurohman, Kosim Pratomo, Rezky Agung Hidayat, Ryan Ramadhan, Redha Akbar Nurtiasto, Taufiq Satrio Ardiansyah, Riki P.P.P., Mikhael Gilang fiber-reinforced plastics GFRP UAV composite; VARI Fiber-reinforced plastics are widely used in aerospace, marine, military, automotive, wind turbine, sports, and civil engineering applications. GFRP is a common material used in engineering applications such as for UAV structural material. Several techniques that can be used in the composite structure manufacturing process are HLU, VB, and, VARI. This paper studies the influence of the three manufacturing processes on the compressive and shear properties of GFRP composites. This study uses e-glass fiber as reinforcement material and a clear epoxy polymer called lycal as matrix material. The composites were manufactured by using HLU, VB, and VARI processes. The specimen dimensions, compressive, and shear tests are following ASTM standards. The microstructural characteristics were observed using a scanning electron microscope. The compressive strength of VARI composite is higher than HLU and VB composites up to 71% and 53%, respectively. The shear strength of the VARI composite is higher than HLU and VB composites up to 71% and 53%, respectively. BRIN Publishing 2023-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/286 10.55981/ijoa.2023.286 Indonesian Journal of Aerospace; Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace; 39-50 3032-0895 10.55981/ijoa.v21i1 eng https://ejournal.brin.go.id/ijoa/article/view/286/500 Copyright (c) 2023 Kosim Abdurohman, Rezky Agung Pratomo, Ryan Hidayat, Redha Akbar Ramadhan, Taufiq Satrio Nurtiasto, Riki Ardiansyah, Mikhael Gilang P.P.P. https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/302 2025-10-03T07:30:22Z ijoa:ART

Stability Analysis of 3D UAV Gimbal using Flexible Body Ruseno, Neno 3D UAV gimbal RecurDyn PID controller stability analysis flexible body Unmanned aerial vehicle (UAV) application in visual object tracking requires a gimbal to stabilize the camera in following the object’s movement. External disturbance and gimbal stability are the issues in this application. This study aims to analyze disturbance effects and study the stress and modal analysis on UAV gimbal using flexible body concepts. The three-dimensional (3D) gimbal is modeled using the RecurDyn software consisting of 3 arms and a camera. Each of the arms is connected using a revolute joint and a rotational force to represent a motor. The considered disturbances are step, pulse, ramp, and sine wave input. The PID controller is used to stabilize the gimbal arm from the gravity of the camera and external disturbance. The result shows that the PID controller is robust to step, pulse, and ramp disturbance, but not to the sin wave disturbance. In addition, the second arm of the gimbal is the most stressed component and is prone to vibration. BRIN Publishing 2023-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/302 10.55981/ijoa.2023.302 Indonesian Journal of Aerospace; Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace; 1-12 3032-0895 10.55981/ijoa.v21i1 eng https://ejournal.brin.go.id/ijoa/article/view/302/497 Copyright (c) 2023 Neno Ruseno https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/304 2025-10-03T07:30:22Z ijoa:ART

Automatic Gain Control for UAV Stability Augmented System Using Jacobian Method Suseno, Prasetyo Ardi Probo Rizaldi, Ardian Wijaya, Yusuf Giri Septiyana, Angga Pranoto, Fuad Surastyo UAV Flight control Longitudinal Jacobian Stability A flight control system is an important system in aircraft to direct the aircraft and maintain the aircraft’s attitudes. One of the most important parts of the flight system is the stability augmented system designed to improve the stability of the aircraft during flight. This system is usually located as the most inner-loop part of the flight control system. There are many methods to design gain control feedback for aircraft stability systems. In this paper, the longitudinal stability augmented system for Unmanned Aerial Vehicle Albatross is designed using the Jacobian methods. The Jacobian method is capable to generate feedback value automatically within the limitation given by design requirements and objectives. This method allows a faster design for the stability augmented system on multi-trim points compared to the classical method such as PID tuning. The results that the designed system works well and conforms with the design requirements and objectives. BRIN Publishing 2023-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/304 10.55981/ijoa.2023.304 Indonesian Journal of Aerospace; Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace; 13-24 3032-0895 10.55981/ijoa.v21i1 eng https://ejournal.brin.go.id/ijoa/article/view/304/498 Copyright (c) 2023 Prasetyo Ardi Probo Suseno, Ardian Rizaldi, Yusuf Giri Wijaya, Angga Septiyana, Fuad Surastyo Pranoto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/723 2025-10-03T07:30:22Z ijoa:ART

Correction Maneuver Optimization to Maintain The Local Time of Lapan-A4 Satellite Zuhri, Muhammad Rizki Poetro, Ridanto Eko Indriyanto, Toto Faturrohim, Luqman In order for a satellite to achieve a sun-synchronous orbit (SSO), it must have a nodal precession rate equal to the revolution rate of the Earth around the Sun. However, sun-synchronous satellites generally encounter significant perturbations, which lead the local time of the satellite to drift gradually. In this research, the author analyzed potential maneuvers to maintain the local time of an SSO satellite for 5 years of operation of LAPAN-A4 satellite. The analysis was conducted by simulation using GMAT (General Mission & Analysis Tools) software with the LAPAN-A4 satellite as a case study. Furthermore, this research also attempted to find the optimum maneuvering period for each potential maneuver. The results showed that the RAAN correction maneuver is ineffective. It was also found that the most optimum maneuvering plan obtained from this research was a semi-major axis correction maneuver with 4 month maneuvering period with a particular correction targeting strategy. BRIN Publishing 2023-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/723 10.55981/ijoa.2023.723 Indonesian Journal of Aerospace; Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace; 145-162 3032-0895 10.55981/ijoa.v21i2 eng https://ejournal.brin.go.id/ijoa/article/view/723/4824 Copyright (c) 2023 Muhammad Rizki Zuhri, Ridanto Eko Poetro, Toto Indriyanto, Luqman Faturrohim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/855 2025-10-03T07:30:22Z ijoa:ART

Image Quality Comparison of Filter Placement Effect on the LWIR Camera of LAPAN A4 Satellite Hartono, Rommy Dede Ardianto Syafrudin, A. Hadi filter lens image placement statistic analysis LAPAN LWIR The LAPAN A4 LWIR camera has already been installed with a bandpass filter, generating a spectral response whose value is near the spectral response of TIRS bands 10 and 11 of LANDSAT 8. Due to the small size of the mechanical part of the LWIR bandpass filter, which has a diameter of 32.5mm, a problem arises when installing the LWIR filter. The filter can be placed in four different positions inside the LWIR camera, and these four positions are also viable for capturing images. This paper aims to compare images generated from four possible filter placements on the LWIR camera using the LAPAN LWIR filter to obtain the best image quality from the LAPAN LWIR camera. To achieve optimal results from these four possible placements, statistical analyses such as standard deviation, SNR calculation, dynamic range, and spatial response area using a moving average filter are employed to assess image quality. Based on the tests and the analysis of signal-to-noise ratio and dynamic range, filter placements behind the zoom lens and in front of the focus lens are nearly identical and superior to those in front of the zoom lens and behind the focus lens. Conversely, the analysis of spatial response area using a moving average filter shows that the filter in front of the zoom and focus lens is superior to that behind the zoom lens. Therefore, the recommendation is to place the filter in front of the zoom and focus lens for the final assembly BRIN Publishing 2024-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/855 10.55981/ijoa.2024.855 Indonesian Journal of Aerospace; Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace; 13-26 3032-0895 10.55981/ijoa.v22i1 eng https://ejournal.brin.go.id/ijoa/article/view/855/8896 Copyright (c) 2024 Rommy Hartono, Dede Ardianto, A. Hadi Syafrudin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/900 2025-10-03T07:30:22Z ijoa:ART

Impact of Airfoil Section on Winglet Design for Enhancing Aerodynamics Performance of Aircraft using CFD Analysis Pinindriya, Sinung Tirtha Soemaryanto, Arifin Rasyadi Fajar, Muhammad Hidayat, Kurnia Hamonangan, Jefri Abner Ramadiansyah, Mohamad Luthfi winglet design airfoil CFD experimental aerodynamics This research paper investigates the influence of airfoil section on winglet design to enhance aerodynamic performance while considering structural aspects. The selection of the airfoil section significantly affects the distribution of lift and drag along the winglet, influencing the overall lift-to-drag ratio of the aircraft and its ability to reduce drag by smoothing the airflow over the wingtip. Three airfoil sections, namely NACA 0010 (symmetrical), NACA 64-009 (thin cambered), and PSU 94-047 (cambered), were compared using computational fluid dynamics (CFD) simulations. The study examines the forces and moments experienced by the winglet, including drag force, lift force, and bending moment on wing surface. The CFD simulations were conducted using a Computational Wind Tunnel (CWT) tool, which employs numerical methods and mathematical models to analyze fluid flow around objects. The solver code is based on RANS method.  The wind tunnel testing is provided to validate one of CFD simulation results. The findings indicate that the installation of winglets increases both the lift-to-drag ratio and bending moment compared to the clean wing configuration. Among the studied airfoil profiles, NACA 0010 demonstrated the optimum lift-to-drag ratio, showing a 9.5% improvement over the clean wing configuration. Although it is a symmetrical airfoil, the thickness of NACA 0010 contributed to higher lift production and increased bending moment compared to the cambered airfoils (NACA 64-009 and PSU 94-047), which showed approximately 10% improvement in lift-to-drag ratio. While the differences in aerodynamic characteristics between the airfoil profiles were marginal, the overall addition of winglets proved effective in increasing lift and reducing induced drag. The research highlights the significance of airfoil shape and thickness in optimizing winglet performance. Future studies should focus on refining the winglet airfoil profile to maximize the benefits derived from both thickness and cambered shape, aiming to further enhance aerodynamic efficiency. BRIN Publishing 2024-08-23 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/900 10.55981/ijoa.2023.900 Indonesian Journal of Aerospace; Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace; 99-108 3032-0895 10.55981/ijoa.v21i2 eng https://ejournal.brin.go.id/ijoa/article/view/900/4819 Copyright (c) 2024 Sinung Tirtha Pinindriya, Arifin Rasyadi Soemaryanto, Muhammad Fajar, Kurnia Hidayat, Jefri Abner Hamonangan, Mohamad Luthfi Ramadiansyah https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/1050 2025-10-03T07:30:22Z ijoa:ART

Parachute Design and Wind Tunnel Testing of Class 10 kg LAPAN UAV Recovery System Herdiana, Dana M. Ichwanul Hakim, Teuku M. Pramutadi, Ardanto Waryoto UAV recovery system parachute wind tunnel LAPAN (BRIN) has already developed several types of fixed-wing UAVs that are intended to conduct civil applications. The UAV is divided by a weight class, which is 10 kg, 20 kg, and 30 kg in MTOW. In some missions, the UAV can operate in the normal way, take-off and landing by using a small runway. In some other missions, the UAV has to be launched by using a catapult and landing by net because of limited space. In the case where the UAV has to be landed between the trees, the usage of nets is not possible. Therefore the recovery system by using a parachute is designed. The cross-type parachute is designed by using analytical and simulation methods to calculate the descent velocity when the aircraft vertically lands. The descent velocity is derived from structure and payload requirements where the impact when the aircraft touches the ground will not cause damage. The designed parachute was then tested in a LAPAN Low-Speed Tunnel (LLST) to verify the design. The tests are conducted in various Reynolds numbers to observe parachute characteristics at a wide range of velocity. The wind tunnel model which is used in the test has a scale of 1:6. The Result of the simulation and the test shows that the design of the parachute was sufficient to be used as a recovery system for a class 10 kg LAPAN UAV because the descent velocity requirement is fulfilled. BRIN Publishing 2024-08-23 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/1050 10.55981/ijoa.2023.1050 Indonesian Journal of Aerospace; Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace; 121-132 3032-0895 10.55981/ijoa.v21i2 eng https://ejournal.brin.go.id/ijoa/article/view/1050/4822 Copyright (c) 2024 Dana Herdiana, Teuku M. Ichwanul Hakim, Ardanto M. Pramutadi, Waryoto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/1168 2025-10-03T07:30:22Z ijoa:ART

SolaSolar Flare Effect to Sq Variation of Geomagnetic Field Observed at Biak Station from 1992 to 2003 Visca Wellyanita La Ode, Muhammad Musafar Ahmad Zulfiana Utama Mira Juangsih Siska Filawati Rizal Suryana Setyanto Cahyo Pranoto Yana Robiana Refina Sri Fitri Wisnu Sq field variation geomagnetic strom solar flares We analyzed the dependence of the geomagnetic Sq field variation at the Biak magnetic field observation station using data from a magnetometer from 1992 to 2003. The Biak station is a low magnetic latitude station, making the dominant variation of the magnetic field component that related to ionospheric currents representable by H-component. The Sq field was extracted from the magnetometer data using the 4th Harmonics Fourier decomposition method. This technique was applied to 1-hour average data of the H-component of the magnetic field. To investigate the dependence of the Sq field amplitude on solar flare events, we selected Sq field variations during flare events without magnetic storms. Additionally, before conducting the Fourier decomposition, we applied Dst index correction to the magnetic field variation data to eliminate the effects of magnetospheric currents. The study shows that Sq variation is highly correlated with X-class flares, which are the most energetic type of flares. Conversely, the lowest amplitude is linked to A-class flares with the lowest energy. These findings indicate that X-class flares generate Sq currents and induce the strongest magnetic fields compared to other classes of flares. BRIN Publishing 2024-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/1168 10.55981/ijoa.2024.1168 Indonesian Journal of Aerospace; Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace; 27-34 3032-0895 10.55981/ijoa.v22i1 eng https://ejournal.brin.go.id/ijoa/article/view/1168/8897 Copyright (c) 2024 Visca Wellyanita, Muhammad Musafar La Ode, Ahmad Zulfiana Utama, Mira Juangsih, Siska Filawati, Rizal Suryana, Setyanto Cahyo Pranoto, Yana Robiana, Refina Sri Fitri Wisnu https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/1319 2025-10-03T07:30:22Z ijoa:ART

Evolution Study Of Solar Like Star τ Ceti Using Mesa Program Mumtahana, Farahhati Nurzaman, M. Zamzam Putri, Gerhana Puannandra Zulfiana, Ahmad τ Ceti solar-like star stellar evolution MESA Tau (τ) Ceti is a G8V class star that has similarities to the sun and several comparable physical properties, although in general its value is smaller and not as active as the sun. Similarities also occur in the planetary system, which has been studied and confirmed to be terrestrial types, four of them were confirmed in the Habitable Zone. This paper aims to study the evolutionary traces of the star Ceti related to the initial studies of its influence on the planetary system through modelling experiments. Interior structure modelling and evolution were carried out with the MESA program. The study of stars belonging to population II begins with the determination of several fundamental parameters obtained from observations such as interferometry and spectroscopy from several references and calculations, which are then used as input in building the model. Static modeling has been carried out by the current condition of the star in the main sequence phase with an age of 9.5 Gyr producing various physical parameters and the division of the star’s atmospheric zone. The evolutionary modelling was carried out up to the Asymptotic Giant Branch (AGB) stage, related to the initial studies of its relationship to the planetary system. Result shows that, without consideration of planetary tidal effect, three of the four planets are likely to be affected by the evolution of τ Ceti. Even though the simulation was only carried out up to the AGB stage, the end history of τ Ceti will be similar to a Solar-mass star, yet over a longer period of time than the Sun. BRIN Publishing 2024-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/1319 10.55981/ijoa.2024.1319 Indonesian Journal of Aerospace; Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace; 35-44 3032-0895 10.55981/ijoa.v22i1 eng https://ejournal.brin.go.id/ijoa/article/view/1319/8898 Copyright (c) 2024 Farahhati Mumtahana, M. Zamzam Nurzaman, Gerhana Puannandra Putri, Ahmad Zulfiana https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/2516 2025-10-03T07:30:22Z ijoa:ART

Implementation of Backprojection Algorithm for Synthetic Aperture Radar Image Processing on Low-Cost Hardware Platform Agus Wiyono Chasanah, Nurul Abner Hamonangan, Jefri Ruhiyat, Abdurrasyid Rohman, Abdul Kurniawan, Farohaji Muksin Arief Aditya, Satria Hendra Wahyudi, Agus Rahayu, Novelita Arisal, Andria Setiadi, Bambang Synthetic Aperture Radar (SAR) Image Processing Low cost Low size Low weight Low power Raspberry Pi Backprojection Algorithm This work presents the implementation of back-projection algorithm for Synthetic-Aperture Radar (SAR) signals on a low-cost, small, lightweight, and low-power consumption platform: Raspberry Pi. The algorithm is implemented with GNU Octave open-source software and the performance was tested on Raspberry Pi 3B and 4 hardware. For performance comparison, a single-threaded baseline implementation of back-projection is created and then modified to run on several threads on an available multicore processor. Executing a single-threaded code Raspberry PI is too slow for real-time imaging. However, the parallelized version shows computation improvement over the baseline version. We include a discussion of parallel implementation on a single Pi using Octave’s parallel package. This study contributes to the understanding of implementing SAR image processing on affordable single-board platforms with constrained computing resources. BRIN Publishing 2024-08-23 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/2516 10.55981/ijoa.2023.2516 Indonesian Journal of Aerospace; Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace; 83-98 3032-0895 10.55981/ijoa.v21i2 eng https://ejournal.brin.go.id/ijoa/article/view/2516/4818 Copyright (c) 2024 Agus Wiyono, Nurul Chasanah, Jefri Abner Hamonangan, Abdurrasyid Ruhiyat, Abdul Rohman, Farohaji Kurniawan, Muksin, Satria Arief Aditya, Agus Hendra Wahyudi, Novelita Rahayu, Andria Arisal, Bambang Setiadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/2553 2025-10-03T07:30:22Z ijoa:ART

LabVIEW based Ground Monitoring System for RX200 Rohmah, Nurul Fahrizatul Faisa Lailiyul Mutho'Affifah Fikana Mahardika Cantri Ardian Wardhana Mirza Zulfikar Rahmat real time monitoring; data acquisition flight time calculation queue management The implementation and deployment of a comprehensive ground monitoring system for rockets is essential to ensure the safety, efficiency, and success of space missions. Ground monitoring systems for rockets play a crucial role in providing real-time information and analysis of critical parameters during rocket operations, including ground testing and launch operations. The ground monitoring system encompasses various functionalities including the acquisition, processing, visualization, recording and storage of data. The data acquisition process in LabVIEW involves the use of TCP/IP Visa function to collect information. The processing involves various functions such as parsing, flight time calculation, and queue management for efficient data handling and calculations. The data can be recorded and stored using the TDMS function. The system efficiently managed all the received data. This study achieved 90,94% accurate data in processing the entire dataset and obtaining accurate values for calculating flight time. This combination yields precise and dependable data that can be utilized for making real-time decisions, analyzing performance, and evaluating missions after they have been completed. BRIN Publishing 2024-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/2553 10.55981/ijoa.2024.2553 Indonesian Journal of Aerospace; Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace; 45-56 3032-0895 10.55981/ijoa.v22i1 eng https://ejournal.brin.go.id/ijoa/article/view/2553/8899 Copyright (c) 2024 Nurul Fahrizatul Rohmah, Faisa Lailiyul Mutho'Affifah, Fikana Mahardika Cantri, Ardian Wardhana, Mirza Zulfikar Rahmat https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/2669 2025-10-03T07:30:22Z ijoa:ART

Stress Analysis of Load Cell Adaptor Designs For The Caliber450mm Solid Rocket Motor Static Test Moranova, Starida Putro, Idris Eko Abrizal, Haryadi Mariani, Lilis Prianto, Bayu Hanif, Azizul Andiarti, Rika Ekadj, Firza Fadlan load cell adaptor stress analysis solid rocket motor structural analysis static test This study presents a structural analysis of two load cell adaptor designs for a caliber-450 mm solid rocket motor. The structural analysis of a C-shape load cell adaptor and the newly designed truncated-cone shape is presented incorporates a 30-degree truncated disc section and varies the thickness to 30 mm, 25 mm, and 20 mm. The numerical simulation using PATRAN reveals that by altering the arm thickness while maintaining the constant hinge thickness, the 30 mm thickness in the disc section yields the best local maximum stress. However, considering the global maximum stress, the 25 mm thickness emerges as the optimal design. The simulation results show that the 25 mm disc section of the load cell adaptor surpasses the aerospace standard safety factor (SF = 1.5) for both local and global maximum stress. BRIN Publishing 2024-08-23 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/2669 10.55981/ijoa.2023.2669 Indonesian Journal of Aerospace; Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace; 109-120 3032-0895 10.55981/ijoa.v21i2 eng https://ejournal.brin.go.id/ijoa/article/view/2669/4821 Copyright (c) 2024 Starida Moranova, Idris Eko Putro, Haryadi Abrizal, Lilis Mariani, Bayu Prianto, Azizul Hanif, Rika Andiarti, Firza Fadlan Ekadj https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/2784 2025-10-03T07:30:22Z ijoa:ART

Evaluation of Artificial Neural Networks Technique for Calibration of Five-Hole Probe Measurement Birry, Abdurrahman Arifianto, Ony Mulyanto, Taufiq five-hole probe artificial neural network calibration wind tunnel rational function In the present study, the Artificial Neural Networks (ANN) technique was implemented to predict the flow parameters of a Five-Hole Probe (FHP). The experimental data were obtained from a subsonic open jet wind tunnel at a speed increased from 0 to 1180 rpm in increments of 200 rpm. The ANN approach is carried out in stages, starting with the method of selecting training data and validation, then increasing the number of neurons, varying the correlation between the activation function and the optimizer, and finally finding the optimal number of hidden layers. In the ANN approach, the mean absolute errors of 0.2705, 0.3326, and 1.0748 were achieved for estimating angle α which represents the angle of attack, angle β which represents the angle of sideslip, and speed, respectively. At the end of this study, the results were compared with the rational function approach. It was concluded that the ANN approach was more accurate compared to the rational function based on statistical parameters such as mean absolute error, max absolute error, and coefficient of determination (r2). BRIN Publishing 2025-05-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/2784 10.55981/ijoa.2024.2784 Indonesian Journal of Aerospace; Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace; 57-70 3032-0895 10.55981/ijoa.v22i1 eng https://ejournal.brin.go.id/ijoa/article/view/2784/8900 Copyright (c) 2025 Abdurrahman Birry, Ony Arifianto, Taufiq Mulyanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/2787 2025-10-03T07:30:22Z ijoa:ART

Model-Based Systems Engineering Capabilities to Connect Descriptive and Analytic Model: Case Studies Hybrid Propulsion of Electric Aircraft Zulkarnain, Muhammad Fikri Nurprasetio, Ignatius Pulung Mulyanto, Taufiq Pasaribu, Hisar Manongam model-based systems engineering electric aircraft hybrid propulsion descriptive-analytic modelling Model-based Systems Engineering (MBSE) is a system development framework that utilizes the formalization of modeling to support systems engineering processes beginning early in the system development stage. This research aim is to explore and evaluate the implementation of the MBSE tool chain, especially in descriptive-analytic capabilities, traceability, ease of design customizations, and ease of making changes. MBSE processes, including requirements definition, functional decomposition, physical decomposition (architecture), and analysis were performed using a case study. The case study is the design and analysis of several hybrid propulsion configurations for electric aircraft. The ease of change and modification is shown by the process of adding, removing, and rerouting system elements and connections to modify from one configuration to another. Analysis has been performed by modeling the analysis context via the SysML Block Diagram, the interconnection of value via the SysML Parametric Diagram, and the calculation and results via the Cameo Instance Table. The result of the proposed propulsion model in SysML for full electric configuration has similar results to reference, while the results for hybrid propulsion have similar trends compared to other studies without MBSE. The method to compare analysis results and requirements with Measure of Performances (MoPs) as mediators has been proposed and performed BRIN Publishing 2024-12-31 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/2787 10.55981/ijoa.2024.2787 Indonesian Journal of Aerospace; Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace; 71-84 3032-0895 10.55981/ijoa.v22i1 eng https://ejournal.brin.go.id/ijoa/article/view/2787/8901 Copyright (c) 2024 Muhammad Fikri Zulkarnain, Ignatius Pulung Nurprasetio, Taufiq Mulyanto, Hisar Manongam Pasaribu https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/2942 2025-10-03T07:30:22Z ijoa:ART

Observations of Ionospheric Conditions Over Pontianak During The Partial Solar Eclipse Suraina Abadi, Prayitno Yolanda Putra, Angga Puannandra Putri, Gerhana Nurmali, Dadang Nurdiansah, Lambang Rakhman, Arif Ednofri Muzirwan Partial solar eclipse Critical frequency Total electron content Declining phase Recovery phase Solar energy plays a significant role in creating ionospheric layers through photoionization. However, when a solar eclipse occurs, the ionizing radiation from the sun will be obstructed by the moon, resulting in a decrease in ionization processes and a depletion of ionospheric plasma density. Our research examines the effects of two partial solar eclipse events that occurred on December 26, 2019 (Eclipse 1) and April 20, 2023 (Eclipse 2) over Pontianak. We observed changes in foF2 and TEC during these events. Our observations show that foF2 and TEC decreased at the start of a partial eclipse but returned to normal once the eclipse ended. The maximum decrease in foF2 observed was 1.88 MHz for Eclipse 1 and 1.26 MHz for Eclipse 2, while the decreases in TEC were 5.68 and 12.81 TECU for Eclipse 1 and 2 respectively. We noted that geomagnetic activity was quiet during both eclipses, indicating that the reduction in ionospheric parameters (TEC and foF2) is affected by the solar eclipse. During a solar eclipse, the decrease in ionization intensity results in a reduction in electron numbers in the ionospheric layers, leading to a reduction in TEC and foF2. BRIN Publishing 2025-05-26 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/2942 10.55981/ijoa.2024.2942 Indonesian Journal of Aerospace; Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace; 85-94 3032-0895 10.55981/ijoa.v22i2 eng https://ejournal.brin.go.id/ijoa/article/view/2942/8905 Copyright (c) 2025 Suraina, Prayitno Abadi, Angga Yolanda Putra, Gerhana Puannandra Putri, Dadang Nurmali, Lambang Nurdiansah, Arif Rakhman, Ednofri, Muzirwan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/2989 2025-10-03T07:30:22Z ijoa:ART

The Occurrence Of Geomagnetic Storm In Solar Cycles 23 And 24 And Their Correlation With Cycle Peaks Juangsih, Mira Nuraeni, Fitri Ratnasari, Elvina Hakim, Lukmanul Geomagnetic Storm Dst Index Solar Cycle Coronal Mass Ejection The 23rd solar cycle occurred from 1996 to 2008, while the 24th solar cycle occurred from 2009 to 2020. Throughout the cycles there were various solar activities that caused geomagnetic storm such as high speed stream (HSS), co-rotating interaction region (CIR), and coronal mass ejection (CME). By using Disturbance storm time (Dst) index, we identified 243 storms during cycle 23 and 149 storms during cycle 24. The distribution of geomagnetic storms corresponds to the distribution of the solar cycle based on sunspot numbers. The cycle 23 exhibited higher activity with 84 strong to extreme storms compare to cycle 24 which had 22 strong to very strong storms. In both cycles, 65% moderate geomagnetic storms were caused by the high speed stream, whereas 85% of strong geomagnetic storms were caused by CMEs. In this study, both cycles exhibit distinct characteristic in producing geomagnetic storms. The low or high maximum phase of a cycle is not associated with the frequency occurrence of strong to extreme geomagnetic storms; both cycles show comparable results in this regard. However a longer declining phase of solar cycle has more impact on production of more moderate storms BRIN Publishing 2025-05-26 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/2989 Indonesian Journal of Aerospace; Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace; 95-102 3032-0895 10.55981/ijoa.v22i2 eng https://ejournal.brin.go.id/ijoa/article/view/2989/8906 Copyright (c) 2025 Mira Juangsih, Fitri Nuraeni, Elvina Ayu Ratnasari, Lukmanul Hakim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/3090 2025-10-03T07:30:22Z ijoa:ART

A Review of Absolute Radiometry Calibration Method for Satellite Multispectral Camera while in Orbit Sartika Salaswati Saputro, Adhi Harmoko Hasbi, Wahyudi onboard Rayleigh vicarious cross calibration Multispectral cameras on satellites are a type of camera that is widely used in satellite remote sensing and has wide applications. Therefore, it is necessary to carry out absolute radiometric calibration to maintain the accuracy of radiometric information in satellite camera images. There are several types of absolute radiometric calibration, including onboard, Rayleigh, vicarious, and cross-calibration. These methods have strengths and weaknesses. Therefore, it is necessary to conduct a literature review to find out which calibration method is appropriate for certain conditions. Based on a literature review, all methods can be used and adapted to the conditions of the satellite. The onboard calibration method is suitable for satellites equipped with calibration instruments. The Rayleigh calibration method is suitable for large FOV cameras with visual wavelengths. The vicarious calibration method is suitable for satellites from countries close to standardized calibration sites. Meanwhile, the cross-calibration method is suitable for satellites cameras that have specifications and conditions close to the reference camera. Therefore, these calibration methods can be carried out together to complement each method. BRIN Publishing 2025-05-26 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/3090 10.55981/ijoa.2024.3090 Indonesian Journal of Aerospace; Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace; 103-118 3032-0895 10.55981/ijoa.v22i2 eng https://ejournal.brin.go.id/ijoa/article/view/3090/8907 Copyright (c) 2025 Sartika Salaswati, Adhi Harmoko Saputro, Wahyudi Hasbi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/4098 2026-05-05T01:31:03Z ijoa:ART

Characterization of Do-It-Yourself (DIY) Ultra Compact ITERA Robotic Telescope (UTOPIA-Scope) Mounting Barends, Renza Alvionzo Prastyo, Hendra Agus Rozzykin, Achmad Zainur Wahidin, Alka Budi Wibowo, Ridlo Wahyudi Yusuf, Aditya Abdilah Oktaviandra, Adhitya 3D printer DIY telescope instrument characterization robotic telescope UTOPIA-Scope Low-cost and locally fabricated robotic telescope systems are increasingly important for education, amateur astronomy, and basic scientific observation. This paper presents the characterization of the UTOPIA-Scope, a do-it-yourself (DIY) alt-azimuth robotic telescope mount developed using extruded aluminum structures and 3D-printed strain-wave gears. The performance of the mount was evaluated through pointing and tracking tests using an alt-azimuth grid and selected equatorial stars. Image center coordinates were obtained using plate-solving techniques and analyzed with descriptive statistical methods. The results show average pointing errors of 1.600° ± 0.123° in azimuth, 0.415° ± 0.048° in altitude, and 0.451° ± 0.106° in equatorial pointing, corresponding to approximately 96′, 25′, and 27′, respectively. Tracking tests indicate drift rates of 22–36 arcsec per minute, depending on the observed sky region. These results provide a quantitative baseline for the performance of the UTOPIA-Scope mount and serve as a reference for further mechanical and control-system improvements toward future scientific applications. BRIN Publishing 2026-05-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/4098 10.55981/ijoa.2025.4098 Indonesian Journal of Aerospace; Vol. 23 No. 2 (2025): Indonesian Journal Of Aerospace; 117-126 3032-0895 10.55981/ijoa.v23i2 eng https://ejournal.brin.go.id/ijoa/article/view/4098/11890 Copyright (c) 1970 Renza Alvionzo Barends, Hendra Agus Prastyo, Achmad Zainur Rozzykin, Alka Budi Wahidin, Ridlo Wahyudi Wibowo, Aditya Abdilah Yusuf, Adhitya Oktaviandra https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/4671 2025-10-03T07:30:23Z ijoa:ART

A Review: Flight Envelope Monitoring and Protection as One of the Flight Safety System Sarah, Annisa Prajitno, Prawito Hasim, Fadillah Hakim, Teuku Mohd Ichwanul loss of control flight envelope protection flight warning system The development of civil aircraft technology, especially commercial aircraft, is now very advanced and complex. This development is intended to assist the pilots to control aircraft in various flight conditions with the main goal to achieved is flight safety. This literature review will discuss research on the flight warning system, which will support the flight envelope protection system development study, which has been conducted over the past few years. The review includes an analysis of existing literature, case studies of aviation accidents, and the evaluation of flight envelope protection systems in current aircraft models. This review shows that the development of technologies and systems can make a significant contribution to flight safety and pilot situational awareness of flight envelope boundaries, so the possibility of aircraft accidents due to loss of control can be reduced BRIN Publishing 2025-05-26 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/4671 10.55981/ijoa.2024.4671 Indonesian Journal of Aerospace; Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace; 119-134 3032-0895 10.55981/ijoa.v22i2 eng https://ejournal.brin.go.id/ijoa/article/view/4671/8908 Copyright (c) 2025 Annisa Sarah, Prawito Prajitno, Fadillah Hasim, Teuku Mohd Ichwanul Hakim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/5505 2025-10-20T06:54:06Z ijoa:ART

Potentially Habitable Terrestrial Exoplanets based on the Habitability Index for Transiting Exoplanets (HITE) Value Rozzykin, Achmad Zainur Lomban, Claudia Amelia Ikhsan, Muhammad Isnaenda exoplanet habitable planet terrestrial transit In-depth exploration of exoplanet habitability involves a crucial screening processto identify a subset with the potential for sustaining life. The Habitability Index for TransitingExoplanets (HITE) emerges as a vital tool, quantifying a planet’s habitability byassessing the probability of it having a solid surface and liquid water. Represented bythe symbol H, the index assigns values on a scale from 0 to 1. The closer the value to 1,the greater the potential for habitability. H integrates parameters derived from transitdata, encompassing orbital period, transit depth, duration, surface gravity, radius, andeffective temperature of the host star. Through the Virtual Planetary Laboratory (VPL),the calculation of H is executed for exoplanets with terrestrial mass (0.3–10 M⊕) sourcedfrom the Transiting Exoplanet Survey Satellite (TESS) and K2 missions. The results showthat the exoplanets with the highest H values are TOI-700 d from TESS, with a value of0.95202. Of the 228 planets examined, around 9.21% are identified as potentially habitable. BRIN Publishing 2025-10-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/5505 10.55981/ijoa.2025.5505 Indonesian Journal of Aerospace; Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace; 1-12 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/5505/10627 Copyright (c) 2025 Achmad Zainur Rozzykin, Claudia Amelia Lomban, Muhammad Isnaenda Ikhsan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/7078 2026-05-05T01:31:02Z ijoa:ART

On The Use Of The Cohesive Zone Model In Validating Mixed-Mode Bending Apparatus Design Syamsudin, Hendri Suada, M Giri Adhitama, Muhammad Daffa mixed-mode bending mixed-mode ratio aluminum adherends cohesive zone model (czm) b-k model Understanding the strength of adhesive materials has been increasingly relevant due to their expanding use in many industries. The importance of understanding its mixed-mode behavior also increases since realistic loading cases rarely involve pure mode I and pure mode II loads. The mixed-mode bending (MMB) test, standardized by ASTM D6671, is a particularly intriguing test that could be used to map adhesive strength in a whole range of mixed-mode ratios, only by using a single specimen design. An MMB apparatus design has been developed based on guidelines provided by ASTM D6671 to test aluminum adherends with modifications that conform to local manufacturing capabilities and material availability. This design was then numerically inspected using the Cohesive Zone Model (CZM) and Benzeggagh-Kenane (B-K) model to check its validity and understand its work range. Mesh convergence test, adherend stiffness variation, and adhesive strength variation were conducted in ABAQUS. Results show satisfactory stability and validity of the design to test aluminum adherends. BRIN Publishing 2026-05-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/7078 10.55981/ijoa.2025.7078 Indonesian Journal of Aerospace; Vol. 23 No. 2 (2025): Indonesian Journal Of Aerospace; 77-94 3032-0895 10.55981/ijoa.v23i2 eng https://ejournal.brin.go.id/ijoa/article/view/7078/11888 Copyright (c) 2025 Hendri Syamsudin, M Giri Suada, Muhammad Daffa Adhitama https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/7981 2025-10-03T07:30:23Z ijoa:ART

Optimization of Powered Landing Control for Reusable Rockets Using Softmax DDGN Rafika Arum Sari Muhammad Hadi Widanto Imron Rosadi Softmax Double Deep Q-Networks Landing Control Optimization Curriculum Learning Fuel Efficiency Reusable Rockets This research presented a novel approach to optimize powered landing control on reusable rockets by using Softmax Double Deep Q-Networks (DDQN). We combined the advantages of Double DQN with Softmax exploration and curriculum learning to achieve precise and efficient landing control. Through extensive experiments in a specially developed 2D simulation environment, our method achieves improved landing accuracy by 37% (reduced final position error from 2.4 m to 1.5 m), better fuel efficiency by 28% (reduced average fuel consumption from 850 kg to 612 kg per landing), and improved adaptability to initial conditions (improved successful landing rate from 76% to 94% across a wide range of altitudes and initial orientations) compared to traditional PID control methods. The results showed that the curriculum learning method significantly outperformed the non-curriculum approach, achieving 27% higher average awards (11.97 vs. 8.61) and 60% better performance consistency as measured by standard deviation (0.92 vs. 2.29). Both Softmax and ε-greedy exploration strategies proved effective with curriculum learning, with ε-greedy DDQN achieving the highest average award of 11.97. This approach allows for higher precision rocket landings while reducing operational costs through. BRIN Publishing 2025-05-26 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/7981 Indonesian Journal of Aerospace; Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace; 135-150 3032-0895 10.55981/ijoa.v22i2 eng https://ejournal.brin.go.id/ijoa/article/view/7981/8909 Copyright (c) 2025 Rafika Arum Sari, Muhammad Hadi Widanto, Imron Rosadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/8155 2025-10-20T06:48:29Z ijoa:ART

Comparative Performance of U-Net CNN in Multi-Class Aircraft Segmentation and Classification Using Polygon and Bounding Box Annotations Sitanggang, Rivilyo Mangolat Rizky Dani, Wa Ode Dianita Putri Suaiba Setiadi, Bambang Kuntjoro, Yanif Dwi U-Net CNN Multi-Class Classification Polygon Annotations Bounding Box Annotations Image Segmentation Recent advancements in deep learning have revolutionized image processingtasks such as segmentation and classification. This study investigates theperformance of U- Net-CNN models in multi-class aircraft segmentation andclassification using polygon and bounding box annotations. Military aircraftclassification is crucial for defense applications, as it aids in rapid and accuratedecision-making during critical missions. This study investigates howthese annotation methods affect training time, segmentation accuracy, andclassification performance in multi-class segmentation and classification tasksinvolving military aircraft. The research compares polygon and bounding boxmethods to evaluate their effectiveness in capturing object details and computationalefficiency. While polygon annotations achieved superior precision witha mean test accuracy of 0.987 and lower loss of 0.041, bounding boxes excelledin computational efficiency. Future research should expand datasets and exploreadditional annotation techniques to further generalize these findings. BRIN Publishing 2025-10-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/8155 10.55981/ijoa.2025.8155 Indonesian Journal of Aerospace; Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace; 13-22 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/8155/10625 Copyright (c) 2025 Rivilyo Mangolat Rizky Sitanggang, Dianita, Bambang Setiadi, Yanif Dwi Kuntjoro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/8941 2026-05-05T01:31:02Z ijoa:ART

Ensuring Suitability of Ground Support Equipment: The Role of AMC in Maintenance Supervision Sari, Mustika Virgie Priskila Alit Sodikin suitability ground support equipment analytical networking process Apron Movement Control The decision of Apron Movement Control (AMC) in supervising the feasibility of Ground Support Equipment (GSE) is a crucial aspect of airport operations to ensure the safety and efficiency of flight services. This study aims to develop an effective and comprehensive decision-making model in assessing the feasibility of GSE using  the Analytical Network Process (ANP) method. The research was conducted at Yogyakarta International Airport, Indonesia involving various criteria and subcriteria which include Engines, Safety Features, Vehicle Operation Licenses. The ANP method was chosen because of its ability to handle complex relationships and interrelationships between various assessment elements. The data was obtained through a questionnaire filled out by experts and related industry players, then analyzed to determine the weight and priority of each criterion. The results of the analysis show that Document Validity, Corrective Actions and Leaks have the greatest influence in the feasibility assessment of GSE. This study is expected to make a significant contribution to improving GSE safety standards and operational efficiency at airports, as well as a reference for AMC in conducting more structured and systematic supervision. The findings are also expected to encourage the application of the ANP method in various aspects of feasibility assessment and other managerial decisions in the aviation industry. BRIN Publishing 2026-05-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/8941 10.55981/ijoa.2025.8941 Indonesian Journal of Aerospace; Vol. 23 No. 2 (2025): Indonesian Journal Of Aerospace; 147-158 3032-0895 10.55981/ijoa.v23i2 eng https://ejournal.brin.go.id/ijoa/article/view/8941/11892 Copyright (c) 1970 mustika sari https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/8949 2025-10-03T07:30:23Z ijoa:ART

A Corotational Formulation For Geometrically Nonlinear Dynamics of 2D Flexible Beams Andria, Novi Zuhal, Lavi Rizki Muhammad, Hari Gunawan, Leonardo 2D corotational formulation geometrically nonlinear flexible beam dynamic analysis A simple and efficient 2D corotational formulation for dynamic analysis of geometrically nonlinear flexible beam is presented in this paper. The corotational approach can easily facilitate the evaluation of internal elactic forces by introducing an element frame to separate rigid body motion and the deformational part. In the present study, the Euler-Bernoulli beam models with simple geometric stiffness matrix is employed and Newmark’s implicit time-stepping scheme with iterative predictor-corrector algorithm is adopted. The validity and efficiency of the present corotational formulation are verified by simulating three numerical examples. Despite its simple numerical implementation, simulation results confirms that the proposed formulation is highly accurate and efficient in simulating flexible beams undergoing large deformation. BRIN Publishing 2025-05-26 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/8949 10.55981/ijoa.2024.8949 Indonesian Journal of Aerospace; Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace; 151-166 3032-0895 10.55981/ijoa.v22i2 eng https://ejournal.brin.go.id/ijoa/article/view/8949/8910 Copyright (c) 2025 Novi Andria, Lavi Rizki Zuhal, Hari Muhammad, Leonardo Gunawan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/8968 2025-10-03T07:30:23Z ijoa:ART

Fuel Efficiency Comparison of PBN and ILS Approach Procedures at Sam Ratulangi Airport M'Azzuri, Banni Yulia Indriyanto, Toto Sembiring, Javensius pbn ils fuel efficiency BlueSky Simulation FlightRadar24 Sam Ratulangi International Airport This study evaluates the efficiency of approach procedures at Sam Ratulangi International Airport-Manado by comparing Required Navigation Performance (RNP) under Performance-Based Navigation (PBN) with the Instrument Landing System (ILS) as a conventional procedure. A simulation using the BlueSky ATM Simulator was conducted with 30 aircraft instances for each approach, utilizing real-time FlightRadar24 speed data to ensure operational realism. The analysis focused on three key metrics: distance flown, time spent, and fuel consumption. Results show that implementing of PBN procedures reduces distance flown by 15%, flight time by 15% and fuel consumption by 14% compared to ILS, demonstrating improved operational efficiency. This research provides a quantitative assessment of PBN systems’ effectiveness in optimizing approach procedures, supporting aviation sustainability, and reducing operational costs. BRIN Publishing 2025-05-26 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/8968 10.55981/ijoa.2024.8968 Indonesian Journal of Aerospace; Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace; 167-182 3032-0895 10.55981/ijoa.v22i2 eng https://ejournal.brin.go.id/ijoa/article/view/8968/8911 Copyright (c) 2025 Banni Yulia M'Azzuri, Toto Indriyanto, Javensius Sembiring https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/8981 2026-05-05T01:31:02Z ijoa:ART

Implementation of Kalman Filter for Accuracy Improvement and Angular Stability as a Control Reference Parallel Manipulator for Camera Pointing on CAN Satellite Fahrizal, Muhammad Hanafi, Nofria Kalman Filter Parallel manipulator CanSat Inertial Measurement Unit This study focuses on the application of the Kalman Filter to improve the accuracy and stability of angular data obtained from Inertial Measurement Unit sensors, which are often affected by noise and bias. The refined angular data serves as a control reference for the parallel manipulator used in the camera pointing system on CAN satellites. Accurate and stable reading angles are essential to ensure precise camera alignment, especially in dynamic environments with disturbances. This study integrates the Kalman Filter into the IMU data processing pipeline to filter the raw roll, pitch, and yaw. We tested the yaw stability improvement by 5.29% and filter performance improvement with 29.25% accuracy, pitch stability improved by 4.63% with 31.12% filter accuracy improvement, and roll stability improved by 1.71% with 28.99% filter accuracy improvement. These filtered angles are then used to control the parallel manipulator, allowing for precise orientation adjustment. The system performance is evaluated in terms of angular accuracy, stability, and manipulator responsibility. The results show a significant improvement in the angular quality of the data, with reduced noise and bias, leading to improved manipulator control. This implementation supports the development of high-precision camera systems for CAN satellites, which require robust and reliable orientation mechanisms. The proposed approach contributes to advancing control systems in small-scale satellite technology, where accuracy and stability are of critical importance. This study highlights the potential of the Kalman Filter in enhancing sensor accuracy for CAN satellite camera pointing systems. However, further research is needed to address dynamic environmental variations that may affect sensor performance. Future studies could explore integrating complementary filtering techniques or machine learning models to optimize data fusion and improve overall system resilience. BRIN Publishing 2026-05-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/8981 10.55981/ijoa.2025.8981 Indonesian Journal of Aerospace; Vol. 23 No. 2 (2025): Indonesian Journal Of Aerospace; 95-116 3032-0895 10.55981/ijoa.v23i2 eng https://ejournal.brin.go.id/ijoa/article/view/8981/11889 Copyright (c) 1970 Muhammad Fahrizal, Nofria Hanafi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/9041 2025-10-20T06:45:04Z ijoa:ART

Guidance and Control System Design of a Surface-to-Air Missile Based on 122 mm Rocket Yogaswara, Y. H. Alvin Ardiansyah Rianto Adhy Sasongko Taufiq Mulyanto proportional navigation flight control flight dynamics missile guidance This paper applies and analyzes the design of a proportional navigation guidanceand control system for a 122 mm rocket platform. The research involves modeling missiledynamics, guidance systems, and control systems. The missile dynamics model relies onthe 6 DOF (Degrees of Freedom) equation for a rigid body, with aerodynamic data obtainedfrom the Missile Datcom program. The propulsion model is generated by a genericthrust profile of a 122 mm unguided rocket. The guidance system model is based on theproportional navigation guidance law, and the control system model employs the LinearQuadratic Regulator (LQR) method. Modeling is conducted using Simulink software, andsimulations encompass various scenarios. The analysis considers aspects such as missiletrajectory, acceleration command, actual acceleration, control surface deflection, and thetime required to hit the target. The simulation results indicate the missile’s capability tointercept targets under numerous conditions, although limitations are observed in specifictarget scenarios where interception is not achievable. BRIN Publishing 2025-10-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/9041 10.55981/ijoa.2025.9041 Indonesian Journal of Aerospace; Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace; 23-44 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/9041/10624 Copyright (c) 2025 Y. H. Yogaswara https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/9106 2025-10-20T06:51:14Z ijoa:ART

Flight Control Design for Rudder Failure Event on Cessna 172 Aircraft Zuhri, Muhammad Rizki Cessna 172 Rudder failure Flight control Waypoint following The Cessna 172, a widely used small commercial aircraft, is renowned for its stabilityin both longitudinal and lateral-directional dimensions. Despite its intrinsic stability, arobust control system is essential to mitigate potential failures, such as rudder malfunctions.This study developed and simulated a control system for the Cessna 172 underrudder failure conditions, relying solely on aileron input for heading control. Using a linearstate-space approach implemented in Matlab/Simulink, the control system incorporatedyaw damping, roll damping, and heading hold for stability and waypoint tracking. Initialsimulations showed that the controller could guide the aircraft to the destination waypointbut exhibited significant deviations of up to 20% under constant rudder inputs. Controllermodification to the PID controller significantly improved performance, reducing deviationsto a maximum of only 0.1% for ±5° rudder input. These results demonstrate the effectivenessof the proposed control system in compensating for rudder failure, though slightoscillations observed at the start of the trajectory suggest the need for further refinement.This research underscores the potential for adaptive and unconventional control methodsto enhance safety and reliability in small aircraft operations. BRIN Publishing 2025-10-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/9106 10.55981/ijoa.2025.9106 Indonesian Journal of Aerospace; Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace; 45-56 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/9106/10626 Copyright (c) 2025 Muhammad Rizki Zuhri https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/9551 2025-10-20T07:01:21Z ijoa:ART

Cosmic Ray Intensity Analysis Based on the Earth’s Latitude and Hemisphere Putri, Annisa Novia Indra cosmic ray intensity Northern Hemisphere (NH) Southern Hemisphere (SH) Halloween Storm geomagnetic avticity The interaction between cosmic rays and solar activity has been extensively investigated,particularly in relation to how solar phenomena modulate cosmic ray intensity inthe heliosphere. The strength of cosmic rays absorbed by the Earth’s hemisphere is notuniform across the Northern Hemisphere (NH) and Southern Hemisphere (SH). This studywill include an investigation of cosmic ray intensity as recorded at various latitudes andhemispheres of the Earth. We employed nine cosmic ray stations in each NH and SH,separated into three types of latitudes: low, middle, and high. The method of percentagechange in cosmic ray intensity was used, which was evaluated during the HalloweenStorm phenomenon on October 29-30, 2003. The results showed that cosmic ray intensitydecreased more at high latitudes than at low latitudes in both hemispheres (NH and SH).Furthermore, the reduction in cosmic ray intensity observed in the NH was approximately1% greater than that observed in the SH. This can be attributed to the Rc value’s dependenceon latitude, variations in geomagnetic activity under different Interplanetary MagneticField (IMF) circumstances, and interplanetary space parameters such as the tilt of theHeliospheric Current Sheet (HCS). BRIN Publishing 2025-10-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/9551 10.55981/ijoa.2025.9551 Indonesian Journal of Aerospace; Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace; 57-64 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/9551/10629 Copyright (c) 2025 Annisa Novia Indra Putri https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/11394 2025-10-20T05:21:19Z ijoa:ART

Mass Optimization of Rocket Nozzles Using Ablative Materials: A Case Study on Indonesian Sounding Rockets Abrizal, Haryadi Juwono, Ariadne Laksmidevi Jihad, Bagus Hayatul nozzle solid rocket mass optimization alternative materials simulation fabrication technology This study presents a comprehensive redesign of the RX450 sounding rocket nozzleaimed at reducing mass while maintaining thermal and structural integrity. The baselinedesign, characterized by heavy steel casing and monolithic graphite liners, imposes significantlimitations on payload capacity and flight performance due to its weight and thermalmanagement challenges. The proposed design replaces the divergent section’s steel casingwith a combination of ablative silica-phenolic composite liners and aluminum 6061 structuralsupport, achieving a substantial mass reduction from approximately 59 kg to 14.5 kgin this critical region. Thermal simulations demonstrate that the addition of a glass-phenolicinsulation layer effectively limits heat transfer to the metallic casing, allowing for thinnerstructural components without compromising safety. Structural analyses confirm thatboth steel and aluminum sections maintain high safety factors under operational loads.Comparative evaluations of alternative configurations further highlight the benefits of advancedcomposite materials and innovative structural concepts, with the lightest modelreducing total nozzle mass by around 40% compared to the baseline. While these resultsare based on literature-derived properties and simplified assumptions, they underscore thepotential of integrating ablative composites and lightweight metals to enhance rocket nozzleperformance. Future work will focus on detailed thermochemical modeling, experimentalvalidation, and full-scale testing to confirm thermal-structural behavior and erosionrates. Overall, this study supports Indonesia’s strategic objective of advancing indigenousrocket technology through accessible, high-performance materials and design innovations. BRIN Publishing 2025-10-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/11394 10.55981/ijoa.2025.11394 Indonesian Journal of Aerospace; Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace; 65-76 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/11394/10623 Copyright (c) 2025 Haryadi Abrizal, Ariadne Laksmidevi Juwono, Bagus Hayatul Jihad https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12160 2025-10-03T07:30:24Z ijoa:FP

Front Pages JTD Vol 17 no.2 Desember 2019 Jurnal, Redaksi - BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12160 10.30536/j.jtd.2019.v17.a3283 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12160/9486 Copyright (c) 2019 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12161 2025-10-03T07:30:24Z ijoa:ART

Aerodynamic Characteristic Optimization on The Design of Anti - Ship Missile for Indonesian Fast - Attack Boat Dwiastuty, Fuji Bura, Romie Oktovianus Triharjanto, Robertus Heru aerodynamic design optimization anti-ship missile Missile is one of Indonesia 7 self – reliant main weapon system programs. Therefore research on the anti – surface ship missile system concept had been carried out at the Faculty of Defense Technology, Defense University. This research aims to abtain optimal design of anti – ship missile concept from previous research, i.e. 2 stages cruise missile with diameter of 0.36 m, total length of 5.19 m, cruise flight altitude of 17 m, and cruise flight speed of 0.88 Mach. The optimation is done on the missile’s aerodynamics characteristics to maximize its lift to drag ratio, which is one of the factor that determine the missile’s performance. Variables of nose cone shapes, number of wings, and body cross sections were chosen for evaluation of lift to drag ratio. The research found that nose cone shape did not affect the aerodynamic characteristics since the flight speed is subsonic. From the rest of the variables, it is found that the best configuration is missile with 2 wings with root length of 1.18 m, height of 0.79 m, and tip length of 0.71 m, elliptical body cross section,  and the missile is to be flown at 6o angle of attack.   BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12161 10.30536/j.jtd.2019.v17.a3157 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 91-100 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12161/9487 Copyright (c) 2019 Fuji Dwiastuty, Romie Oktovianus Bura, Robertus Heru Triharjanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12162 2025-10-03T07:30:24Z ijoa:ART

AnaLISIS KESELAMATAN RADIASI GEDUNG LABORATORIUM RADIOGRAFI PUSTEKROKET LAPAN SECARA TEKNIS DAN LEGAL Budi, Rika Suwana Syaifudin, Rofiq paparan kebocoran radiasi perisai radiasi Analisis keamanan radiasi diperlukan untuk mengevaluasi tingkat keamanan radiasi dan tindakan yang diperlukan pada saat bekerja atau berada dilingkungan dengan radiasi tinggi. Hasil pengujian tingkat kebocoran radiasi menunjukkan bahwa gedung laboratorium uji radiasi memerlukan penambahan dinding perisai.  BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12162 10.30536/j.jtd.2019.v17.a3208 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 101-108 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12162/9488 Copyright (c) 2019 Rika Suwana Budi, Rofiq Syaifudin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12163 2025-10-03T07:30:24Z ijoa:ART

ANALISIS PENENTUAN POWER LOADING PADA DESAIN AWAL PESAWAT TERBANG TANPA AWAK LSU-05 NG Atmasari, Novita Jayanti, Eries Bagita Ula, Nur Mufidatul Ramadiansyah, M. Luthfi Ramadhan , Redha Akbar Suseno, Prasetyo Ardi Probo Rizaldi, Ardian Hidayat, Kurnia Septiyana , Angga power loading estimasi matching chart optimal Penelitian ini berfokus pada analisa penentuan power loading pada awal desain pesawat LSU-05 NG. Dengan menentukan power loading maka kebutuhan daya engine untuk pesawat LSU-05 NG dapat diestimasi. Artinya pemilihan engine dapat dilakukan sehingga menghasilkan gaya dorong agar pesawat dapat melakukan misi pemantauan dan foto udara dengan baik.  Metode yang digunakan untuk analisa penentuan power loading adalah teknik Matching Chart atau Matching Plot dengan memilih titik optimal dari lima konstrain yaitu jarak take-off, climb rate, stall speed, cruise speed, dan landing. Hasil penelitian menunjukkan bahwa dengan massa 85 kg dan luas sayap 3,22 m2 pesawat LSU-05 NG membutuhkan daya 9.7 hp. Penjelasan lebih detail akan dijabarkan pada bagian selanjutnya.   BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12163 10.30536/j.jtd.2019.v17.a3162 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 109-122 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12163/9489 Copyright (c) 2019 Novita Atmasari, Eries Bagita Jayanti, Nur Mufidatul Ula, M. Luthfi Ramadiansyah, Redha Akbar Ramadhan , Prasetyo Ardi Probo Suseno, Ardian Rizaldi, Kurnia Hidayat, Angga Septiyana https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12164 2025-10-03T07:30:24Z ijoa:ART

Effect Of Rubber Damper Stiffness And Tire Pressure To Reduce Ground Reaction Load Factor On Main Landing Gear Using Multi-Body Simulation (MBS) Rigid Model Hidayat, Dony Istiyanto, Jos Marta, Aryandi Hidayat, Kurnia Sumarsono, Danardono Agus Contact/impact force landing gear drop test multi-body simulation rigid body Landing Gear Drop Test (LGDT) utilizes the apparatus requiring a substantial time and cost. Virtual LGDT (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. From simulation with vsink 1.7 m/s and load 22000 N obtained contact/impact force that ensue in MSC ADAMS was 73650 N, while from experimental was 73612 N. The difference between vLGDT and LGDT result is 0.05 %. To obtain ground reaction load factor below 3 in vsink = 3.05 m/s, the rubber damper should have stiffness in the range of 1900 - 2100 N/mm and for the tire pressure of 60 - 65 psi.   BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12164 10.30536/j.jtd.2019.v17.a3131 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 123-128 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12164/9490 Copyright (c) 2019 Dony Hidayat, Jos Istiyanto, Aryandi Marta, Kurnia Hidayat, Danardono Agus Sumarsono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12165 2025-10-03T07:30:24Z ijoa:ART

LOW COST EMBEDDED CONTROLLER SIMULATION FOR MISSILE IN REAL-TIME ENVIRONMENT Putro, Idris E. Septanto, Harry real-time simulation xPC Target single board computer (SBC) standalone target LQR This paper focuses on the development of real-time environment for low cost embedded system to control flight performance of missile. Real-time simulation is generated by using xPC target so that standalone target boot can be developed, and target PCs can be simulated in real-time. Two PCs and single board computers (SBCs) are required to configure the host and standalone target respectively. The host PCs are used to control the target PCs while these target PCs run simultaneously in real-time. Target PCs are divided into plant platform and controller platform. Plant platform represents missile dynamics model, while control algorithm is compiled to the other system as controller platform. Linear control synthesis will be implemented for maintaining flight stability of missile using optimal control approach based linear quadratic regulator (LQR). This real-time system should resemble the environment of future flight test. BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12165 10.30536/j.jtd.2019.v17.a3159 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 129-140 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12165/9491 Copyright (c) 2019 Idris E. Putro, Harry Septanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12166 2025-10-03T07:30:24Z ijoa:ART

Pemilihan Airfoil Pesawat Terbang Tanpa Awak LSU-05 NG dengan Menggunakan Analytical Hierarchy Process Hidayat, Kurnia Rizaldi, Ardian Septiyana, Angga Ramadiansyah, M. Luthfi Ramadhan , Redha Akbar Suseno, Prasetyo Ardi Probo Jayanti, Eries Bagita Atmasari, Novita Nurtiasto , Taufiq Satrio airfoil pesawat AHP perancangan Pada perancangan pesawat terbang tanpa awak, pemilihan airfoil sangat penting untuk meningkatkan performa pesawat. Airfoil dipilih berdasarkan karakteristik geometri dan performa aerodinamikanya. Penelitian ini membahas tentang pemilihan airfoil dengan banyak kriteria berdasarkan karakteristik masing-masing airfoil. Pada tahap awal, sebanyak 1504 airfoil tersaring menjadi 5 airfoil terpilih. Airfoil tersebut dianalisis berdasarkan 7 kriteria utama, yaitu Camber, Thickness, Manufacturability, Max C_L, C_(L_0 ), Max C_L angle, dan Max L/D. Berdasarkan analisis tersebut, FX 76-MP-160 terpilih sebagai airfoil terbaik untuk pesawat terbang tanpa awak yang dirancang.   BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12166 10.30536/j.jtd.2019.v17.a3161 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 141-156 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12166/9492 Copyright (c) 2019 Kurnia Hidayat, Ardian Rizaldi, Angga Septiyana, M. Luthfi Ramadiansyah, Redha Akbar Ramadhan, Prasetyo Ardi Probo Suseno, Eries Bagita Jayanti, Novita Atmasari, Taufiq Satrio Nurtiasto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12167 2025-10-03T07:30:24Z ijoa:ART

PRELIMINARY THERMAL CONTROL DESIGN ANALYSIS OF LAPAN SAR-MICROSATELLITE DEPLOYABLE SOLAR ARRAY PANEL USING ONE NODAL METHODE Budiantoro, Poki Agung Fauzi, Ahmad solar array panels solar cell temperature energy LAPAN SAR-Microsatellite is the first LAPAN micro satellite being developed and planned to carry a Synthetic Aperture Radar (SAR) payload.  Different from optical satellites that have been developed, LAPAN SAR-Microsatellite requires a lot more power. Solar array panels are needed to generate solar radiation into electrical energy which is used by all of subsystem satellite as energy to turn on and turn off all of components. More larger the area of solar array panel, more greater to the energy obtanied. Therefore, the needed of deployable solar array panel is a must caused by the dimension of the main body structur (MBS) are not large enough. Solar cells will experience a decrease in efficiency if they experience excessive heat. If there is a decrease in efficiency in the solar cell, it will have an impact on the decrease in power produced. The purpose of this study is to conduct thermal design on solar panels to maintain temperature according to their working temperature. Calculations are carried out on the temperature of solar array panel with various optical properties in the upper and lower panel that best which will be use using one nodal analysis methode According to the calculation result from all of the designs passive thermal control system on this study show that Design-5 is the best thermal control design which can be used for LAPAN SAR-microsatellite deployable solar array panel which α=0.24 at the top and ε=0.9 at the bottom surface of solar array panel.   BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12167 10.30536/j.jtd.2019.v17.a3155 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 157-168 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12167/9493 Copyright (c) 2019 Poki Agung Budiantoro, Ahmad Fauzi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12168 2025-10-03T07:30:24Z ijoa:ART

SISTEM KENDALI KOOPERATIF UAV UNTUK MENDUKUNG PENGAWASAN ILLEGAL FISHING Wiyono, Agus UAV monitoring kopperatif illegal fishing Terjadinya kegiatan illegal fishing sangat merugikan bagi bangsa Indonesia, terutama bagi para nelayan. Kementerian Kelautan dan Perikanan merupakan institusi pemerintah yang memiliki kewenangan dalam melakukan pengawasan dan penindakan terhadap kegiatan illegal fishing. Salah satu kegiatan pengawasan yang dilakukan selama ini adalah dengan memanfaatkan pesawat terbang berawak. Hal tersebut memiliki beberapa kelemahan. Untuk melengkapi kekurangan yang ada dalam penggunaan pesawat terbang berawak, pengoperasian UAV dapat digunakan untuk mendukung operasi pengawasan illegal fishing. Penggunaan single-UAV tidak akan sesuai tugas pengawasan dimana area yang diawasi sangatlah luas. Aplikasi multi-UAV untuk melaksanakan tugas semacam ini akan cukup efektif. Untuk mewujudkannya suatu system kendali kooperatif telah dibangun. Pada tahap pertama, sistem kendali dibangun dan diuji dalam lingkungan virtual yaitu melalui simulasi. Perangkat lunak yang digunakan untuk membangun system kendali adalah: Matlab/Simulink untuk membangun sistem kendali terbang dan X-Plane 9 digunakan untuk pemodelan matematis pesawat dan visualisasi dinamika pesawat. Metoda kooperatif yang digunakan adalah leader-follower. Hasil yang diperoleh menunjukan bahwa simulasi multi-UAV dengan menggunakan Matlab/Simulink dan X-Plane telah berhasil digunakan untuk mengendalikan 3 UAV mengikuti topologi kooperatif.   BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12168 10.30536/j.jtd.2019.v17.a3128 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 169-178 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12168/9494 Copyright (c) 2019 Agus Wiyono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12169 2025-10-03T07:30:24Z ijoa:ART

VISUALISASI 2 DIMENSI POSISI SATELIT ORBIT RENDAH MENGGUNAKAN SGP4, MERCATOR, DAN VISUAL BASIC 6 Pratomo, Bina Mayditia, Hasan satelit SG4P Mercator Visual basic 6 Perkiraan posisi satelit sangat diperlukan oleh banyak penggiat satelit untuk dapat mengakses satelit tepat waktu terutama satelit orbit rendah yang posisinya tidak selalu tepat di atas sebuah daerah secara terus menerus, dengan menggunakan data TLE, algoritma SGP4, dan teknik mercator yang di implementasikan ke dalam bahasa pemrograman visual basic 6 berhasil memvisualisasikan posisi satelit dalam tampilan dua dimensi.   BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12169 10.30536/j.jtd.2019.v17.a3154 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara; 179-190 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12169/9495 Copyright (c) 2019 Bina Pratomo, Hasan Mayditia https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12170 2025-10-03T07:30:24Z ijoa:BP

Back Pages JTD Vol 17 No.2 Desember 2019 Jurnal, Redaksi - BRIN Publishing 2019-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12170 10.30536/j.jtd.2019.v17.a3284 Indonesian Journal of Aerospace; Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12170/9496 Copyright (c) 2019 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12174 2025-10-03T07:30:24Z ijoa:FP

Front Pages JTD Vol 19 No.1 June 2021 Jurnal, Redaksi - BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12174 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12174/9497 Copyright (c) 2021 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12175 2025-10-03T07:30:24Z ijoa:ART

The Effect of Cross-section and Elliptical Hole Ratio on Crashworthiness Parameters of Crash-Box Structure Warsiyanto, Budi Aji Widanto, Muhammad Hadi Musthofa, Ilham Maulana, Ichsan Sitompul, Sahril Afandi Yuniarti, Endah The thin-walled column structure or crash-box with metal material and consisting of multi-cell were found to be much more efficient in energy absorption than single-cell under axial impact loads. In this study, a numerical analysis was performed using the Abaqus finite element method for the cross-section differences in thin-walled column structures. The cross-section differences are compared to get a configuration that complies with the indicator parameters using the complex proportional assessment (COPRAS) method. The chosen cross-section configuration is further enhanced by creating elliptical holes with different diameter ratios. The results show that the thin-walled column structure with nine-cell cross-section accompanied by an elliptical hole ratio of 0.3 indicates the potential corresponding to the indicator parameters for the crashworthiness application. BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12175 10.30536/j.jtd.2021.v19.a3408 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 1-14 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12175/9498 Copyright (c) 2021 Budi Aji Warsiyanto, Muhammad Hadi Widanto, Ilham Musthofa, Ichsan Maulana, Sahril Afandi Sitompul, Endah Yuniarti https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12176 2025-10-03T07:30:24Z ijoa:ART

Investigation of Wire Diameter of Helical Compression Spring for Payload Separation Laksono, Shandi Prio The payload is designed to be separated from rocket at an altitude over 100 km.  One of critical component in the payload separation system is the helical compression spring. The helical compression spring ensures safe release the payload. The spring must satisfy some parameters such as static failure and buckling, also spring has enough energy storing to release the payload during launch. The objective of this paper is to do investigation of wire diameter of helical compression spring which can be used in the payload separation system of sounding rocket based on several constraints. The results obtained show that with payload weight of 60 kg, minimum wire diameter should be 8 mm with mean coil diameter of 80 mm. The maximum separation velocity of 1.76 m/swas obtained by using wire diameter of 8 mm and mean coil diameter of 96 mm.   BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12176 10.30536/j.jtd.2021.v19.a3490 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 15-24 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12176/9499 Copyright (c) 2021 Shandi Prio Laksono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12177 2025-10-03T07:30:24Z ijoa:ART

Properties Comparison of Open Hole and Non-Hole Carbon UD-Lycal Composite with Vacuum Bagging Manufacturing Method Isna, Lathifa Rusita Nugroho, Afid P, Rezky Agung R, Redha Akbar composite carbon fiber vacuum bagging tensile testing hole specimen Carbon fiber reinforce polymer is one of some composite materials that has the high strength with light weight material. To apply this composite to the amphibious airplane structure, it should through the experimental tensile test to know the tensile strength and modulus of elasticity of the composite. In this experiment, we use Carbon UD fiber and Lycal resin as the composite material that manufactured with Vacuum Bagging Method. Specimens and testing process refer to ASTM D3039 for non-hole specimen, and ASTM D5766 for open hole specimen of tensile test standard for composite matrix polymers. The result of the experimental test shows that the tensile modulus of elasticity for non-hole composite is 34.92 ± 0.13 GPa, with the Ultimate Tensile Strength of this composite is 1081± 0.03 MPa, and the modulus of elasticity for open hole composite is 41.87± 0.02 GPa, with the Ultimate Tensile Strength of this composite is 899.04± 0.02 MPa. The simulation yields nearly same stress-strain graph with the result of experiment. The result shows that, the open hole composite has the ultimate tensile strength lower than non-hole composite, it’s due to the open hole composite has a trigger failure that may decreasing the tensile strength value.   BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12177 10.30536/j.jtd.2021.v19.a3494 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 25-32 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12177/9500 Copyright (c) 2021 Lathifa Rusita Isna, Afid Nugroho, Rezky Agung P, Redha Akbar R https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12178 2025-10-03T07:30:24Z ijoa:ART

INFORMATION EXTRACTION FROM LAPAN SATELLITE AIS DATABASE FOR SHIP CLASSIFICATION IN THE INDONESIAN TERRITORIAL WATERS Nugroho, Muazam Ferdiansyah, Nurrochman Rahayu, Dicka Ariptian Permala, Rizki Hakim, Patria Rachman Hasbi, Wahyudi AIS database LAPAN satellite marine traffic Automatic Identification System (AIS) is a system used to monitor ship activity by sending ship information via Very High Frequency (VHF) waves. Information sent by ships around the world is recorded by AIS receivers carried by the LAPAN-A2 and LAPAN-A3 satellites along their orbital trajectories. The AIS data recorded by the satellite will then be acquired and stored at the LAPAN earth station. This study focuses on extracting information from the LAPAN satellite AIS database to obtain information on the number of vessels based on a unique Maritime Mobile Service Identity (MMSI) grouped according to the type of vessel entering Indonesian waters with coordinates 95BT / 141BT, -11LS / 6LU every month. in the period January to December 2019. The results of extracting the information are in the form of the number of ships based on unique MMSI which are grouped according to the type of ship in the territory of Indonesia with that region and time period   BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12178 10.30536/j.jtd.2021.v19.a3566 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 33-42 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12178/9501 Copyright (c) 2021 Muazam Nugroho, Nurrochman Ferdiansyah, Dicka Ariptian Rahayu, Rizki Permala, Patria Rachman Hakim, Wahyudi Hasbi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12179 2025-10-03T07:30:24Z ijoa:ART

POWERED LANDING GUIDANCE ALGORITHMS USING REINFORCEMENT LEARNING METHODS FOR LUNAR LANDER CASE Nugroho, Larasmoyo Zani, Novanna Rahma Qomariyah, Nurul Akmeliawati, Rini Andiarti, Rika Wijaya, Sastra Kusuma Planetary Landing Lunar Lander Q-Learning DQN DDQN DDPG PPO Any future planetary landing missions, just as demonstrated by Perseverance in 2021 Mars landing mission require advanced guidance, navigation, and control algorithms for the powered landing phase of the spacecraft to touch down a designated target with pinpoint accuracy (circular error precision < 5 m radius). This requires a landing system capable to estimate the craft’s states and map them to certain thrust commands for each craft’s engine. Reinforcement learning theory is used as an approach to manage the mapping  guidance algorithm and translate it to engine thrust control commands. This work compares several reinforcement learning based approaches for a powered landing problem of a spacecraft in a two-dimensional (2-D) environment, and identify the advantages/disadvantages of them. Five methods in reinforcement learning, namely Q-Learning, and its extension such as DQN, DDQN, and policy optimization-based such as DDPG and PPO are utilized and benchmarked in terms of rewards and training time needed to land the Lunar Lander. It is found that Q-Learning method produced the highest efficiency. Another contribution of this paper is the use of different discount rates for terminal and shaping rewards, which significantly enhances optimization performance. We present simulation results demonstrating the guidance and control system’s performance in a 2-D simulation environment and demonstrate robustness to noise and system parameter uncertainty.   BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12179 10.30536/j.jtd.2021.v19.a3573 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 43-56 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12179/9502 Copyright (c) 2021 Larasmoyo Nugroho, Novanna Rahma Zani, Nurul Qomariyah, Rini Akmeliawati, Rika Andiarti, Sastra Kusuma Wijaya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12180 2025-10-03T07:30:24Z ijoa:ART

Station-Keeping Simulation and Planning for LAPAN-A4 Satellite Using Finite-Burn Thruster Zuhri, Muhammad Rizki Poetro, Ridanto Eko LAPAN-A4 SSO inclination maneuver finite-burn thruster To be a Sun-synchronous orbit (SSO), the orbit must have a certain value of nodal precession rate, which equals to 360°/year. However, the value of nodal precession rate is usually drifted by orbit perturbations, mainly by the oblateness of the Earth and atmospheric drag, to be no longer 360°/year as expected for SSO. Thus, the local time of the satellite will change too, so it needs to be corrected by some correction maneuvers. In this research, the authors studied about station-keeping planning for SSO satellite via inclination correction maneuver by simulation using GMAT, a software developed by NASA, with a finite-burn propulsion approach. In this research, LAPAN-A4 satellite is chosen to be the satellite that will be simulated. Some  alternative plans of inclination correction maneuver based on maneuvering periods are chosen, they are maneuver for every 2 months, 4 months, 6 months, 12 months, and 24 months. The simulation results show that the optimal station keeping planning is the maneuver for every 2 months. This alternative gives the lowest fuel consumption so that the fuel and launch cost will be minimum, and the local time drift that is still may be tolerated. BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12180 10.30536/j.jtd.2021.v19.a3474 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 57-66 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12180/9503 Copyright (c) 2021 Muhammad Rizki Zuhri, Ridanto Eko Poetro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12182 2025-10-03T07:30:24Z ijoa:ART

Preliminary Power Budget Analysis for Equatorial Low Earth Orbit (LEO) Communication Satellite Suryanti, Desti Ika Ramayanti, Sri Mukhayadi, Mohammad Micro satellite communication satellite power budget solar panel li-ion battery Satellite Technology Center – LAPAN would develop a constellation of 9 communication satellites in a low equatorial orbit. These satellites would perform as data collection platforms for many sensors that spread across the Indonesian territory. The data from the sensors will be downlink to Indonesia’s ground stations in real-time. This research aims to analyze the power budget of those satellites to decide how many solar panels and batteries are required to perform their mission. The method in this research began by calculating the power requirements of each mission per orbit period to estimate power consumption and calculate the power generated by the solar panels. The results of these calculations will be implemented to the power system design to find the satellite solar cells/ panels arrangement and battery capacity allocation. To minimize the development time and cost, the solar array design in this study considers the utilization of previous solar panel design of LAPAN-A series satellites as a design constraint. This study shows the configuration of 3 body-mounted solar panels and 2 deployable solar panels could support the mission operation of communication satellite in the low equatorial orbit. For energy storage, these satellites should be equipped with 28 V Li-ion in the 8Sx3P configuration.   BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12182 10.30536/j.jtd.2021.v19.a3479 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 67-78 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12182/9504 Copyright (c) 2021 Desti Ika Suryanti, Sri Ramayanti, Mohammad Mukhayadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12183 2025-10-03T07:30:24Z ijoa:ART

Dynamic response of the wing during UAV collision Warsiyanto, Budi Aji Widanto, Muhammad Hadi Musthofa, Ilham Maulana, Ichsan drone collision damage assessment wing leading edge simulation An airborne collision between civil Unmanned Aerial Vehicles (UAVs) and manned aircraft is a potential threat to aircraft operation safety. In this paper, the UAV collision test was performed on a commuter aircraft wing section to investigate the dynamic response of this primary operation component. The projectile was a 735 g drone named ‘Mavic’. Explicit dynamic code ABAQUS was employed to simulate the collision process based on the difference of collision scenarios to assess the hazard. The results showed that 735 g drone impact at the aircraft maximum approach flap and cruising speed could cause some damage on the wing front spar and the situation is more serious than 910 g bird strike in which the hardness of drone components rather than kinetic energy is a decisive factor. The lithium-ion battery penetrated the airframe which may be a potential source of ignition.   BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12183 10.30536/j.jtd.2021.v19.a3514 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 79-92 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12183/9505 Copyright (c) 2021 Budi Aji Warsiyanto, Muhammad Hadi Widanto, Ilham Musthofa, Ichsan Maulana https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12184 2025-10-03T07:30:25Z ijoa:ART

Research on the Transmissibility of Wire Rope Insulators as Damping Equipment on the RX 200 Rocket Payload Djatmiko, Agus Budi Ediwan, Ediwan Ronald, Ronald Putra, Gunawan wire rope isolator resonance transmissibility Wire rope insulator or steel wire rope insulator has applications for vibration isolation in equipment and structures in many industrial machinery. Steel wire rope insulators can also be used as suitable equipment to dampen vibrations in rocket loads. The disturbance acceleration as the excitation caused by the combustion process on the rocket can cause a vibration with a large amplitude which results in damage to the rocket's payload structure and the electronic equipment on the rocket's payload cannot work as desired. Based on the experience of electronic equipment, it will be damaged if the disturbance acceleration of 3 g acting on the rocket is not reduced, for this reason a vibration damping device is designed, the apparatus consists of several stainless steel wire ropes tied between two parallel binders arranged in such a way as to provides a damping effect on the rocket's payload. A wire rope insulator consists of several stainless steel wire ropes tied between two parallel straps. One application of this type of wire rope insulator is to isolate the vibrations that occur in the rocket, so that it does not interfere with the performance of the electronic equipment on the rocket's payload. Electronic equipment is used to determine the position of the rocket and its stability. In this study, the wire rope material used is stainless steel with syield = 350 e+6 N / m2 with a diameter of d = 3 mm. The research objective of the vibratory damper of wire rope insulators was to determine the magnitude of the transmissibility of the ruffler during and after resonance. Transmissibility (TR) is the ratio of the force transmitted to the disturbing or excitation force. The results of the research on a damper with a disturbance acceleration of 3 g at resonance, obtained the transmissibility value (TR) = 2.54, the spring stiffness k = 200537.3 N/m and the damping coefficient c = 331.5 N/m/sec, then after conditions  obtained transmissibility (TR) <1 This shows that the damper with steel wire isolator is good enough to dampen vibrations in the RX 200 rocket payload. BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12184 10.30536/j.jtd.2021.v19.a3556 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 93-100 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12184/9506 Copyright (c) 2021 Agus Budi Djatmiko, Ediwan, Ronald, Gunawan Putra https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12185 2025-10-03T07:30:25Z ijoa:ART

Effects of Bleeder Schedule to Fiber Mass Fraction and Composites Surface Topography on Wet Lay-up Manufacturing Process Dewi, Wiwiek Utami Sutrisna, Rizky Sutrisno, Sutrisno thermal protector material bleeder schedule fiber mass fraction SEM analysis peel ply The thermal protector materials of the rocket’s motor are made by a wet lay-up manufacturing process. Since the fiber mass fraction of the product is low, several experiments were conducted to solve this problem including changing the type of the epoxy resin and selecting the most suitable bleeder schedule. Bleeder cloth application results in increasing the fiber mass fraction. The fiber mass fraction of thermal protector material manufactured by hand lay-up can reach a maximum of 56,78%, whereas vacuum bagging can reach a maximum of 66,43%. Peel ply and breather fabric combination are the best bleeder schedule for the hand lay-up method meanwhile perforated release film and breather fabric are the best bleeders for the vacuum bagging method. Composite surface topography obtained from peel ply is visible on the surface. The imprints of the nylon peel ply weave are visible through SEM analysis. Meanwhile, the surface topography obtained from the perforated release film is not visible. The vacuum bagging method helped reduce the number of voids and ductile polymer fractures from the composite surface. This paper recommends peel ply usage in the thermal protector manufacturing process to replace the sanding or filling method that the author use nowadays.   BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12185 10.30536/j.jtd.2021.v19.a3572 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021); 101-110 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12185/9507 Copyright (c) 2021 Wiwiek Utami Dewi, Rizky Sutrisna, Sutrisno https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12186 2025-10-03T07:30:25Z ijoa:FUP

Full Pages JTD Vol 19 No.1 June 2021 Jurnal, Redaksi - BRIN Publishing 2021-06-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12186 Indonesian Journal of Aerospace; Vol. 19 No. 1 (2021) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12186/9508 Copyright (c) 2021 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12187 2025-10-03T07:30:25Z ijoa:FP

Front Pages JTD Vol 19 No.2 December 2021 Jurnal, Redaksi - BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12187 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12187/9509 Copyright (c) 2021 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12188 2025-10-03T07:30:25Z ijoa:ART

The effect of Impact Angle on Dynamic Response of 19 Passenger Commuter Aircraft Windshield against Bird Strike Warsiyanto, Budi Aji Nurrohmad, Abian Fitriansyah, Rizky Utama, Agus Bayu Sitompul, Sahril Afandi Yuniarti, Endah This paper's objective was to determine the dynamic response of a 19 passenger commuter aircraft windshield to impact angle variations. The phenomenon was performed using the finite element method, and the smoothed particle hydrodynamics (SPH) was chosen as a method for modeling bird material. The elastic-plastic polymethyl methacrylate (PMMA) material with the maximum principal strain failure criterion was used to model the windshield's dynamic response. The variation of the impact angle consists of 15°, 0°, -8°, and -15°, which are measured of the longitudinal axis of the aircraft. The simulation result showed that the impact angle that causes the windshield's dynamic response in the elastic, plastic deformation, and the greatest failure is the angle -15°. The upper end of the windshield (fixed) is the weakest part due to the stress concentration.   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12188 10.30536/j.jtd.2021.v19.a3560 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 111-126 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12188/9510 Copyright (c) 2021 Budi Aji Warsiyanto, Abian Nurrohmad, Rizky Fitriansyah, Agus Bayu Utama, Sahril Afandi Sitompul, Endah Yuniarti https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12189 2025-10-03T07:30:25Z ijoa:ART

Identification of Flow-Induced Noise Sources on Two-Dimensional High Lift Devices of Commuter Aircraft Soemaryanto, Arifin Rasyadi Fajar, M Hakim, TMI Hidayat, Kurnia Tirtha, Sinung computational aeroacoustics computational aerodynamics high-lift devices aircraft design Full Text: A numerical predictive tool of flow induced noise generated by deployed high-lift devices of commuter aircraft is presented in this paper. The aircraft high-lift devices are consisting of vane and flap component. The aim of this study is to identify the sources of flow induced noise on the wing and flap cross-section of the aircraft. This study is investigated only two-dimensional effects and two configuration of flap deflection. A numerical computation is carried out using a CFD software with Large Eddy Simulation fluid turbulence model and Ffowcs-Williams & Hawkings analogy for acoustic prediction. Several sound receivers have been installed on far-field and near-field region of the wing-vane-flap cross-section of aircraft to measure the sound spectra. It has been identified that on the cavity of wing and vane-flap cross-section has the highest sound pressure level than another region. There is a vortical separation and shear layer which is contributed to the generation of sound emission downward the cross-section   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12189 10.30536/j.jtd.2021.v19.a3500 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 127-134 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12189/9511 Copyright (c) 2021 Arifin Rasyadi Soemaryanto, M Fajar, TMI Hakim, Kurnia Hidayat, Sinung Tirtha https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12190 2025-10-03T07:30:25Z ijoa:ART

Preliminary Fault tree Analysis of Landing Gear Control and Warning for LSA 02 Motorized Glider Type Aircraft Wirawan, Adi Pranoto, Fuad Surastyo LSA-02 FTA Landing gear In this paper, the authors present an approach of reliability analysis to analyze the landing gear control and warning system, which is planned to be installed on LSA-02 aircraft. The reliability analysis will use fault tree analysis as starting point to investigate what is the top undesired event which might occur in this system. The construction of causal tree analysis offers a framework privileged to the deductive analysis, which consists of seeking the various possible combinations of events, leading to the occurrence of a top undesired event. The fault tree analysis shows that the top undesired event for this system is when the landing gear is commanded to extended, the system fails to extend the landing gear, and warning system is failed to operate.   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12190 10.30536/j.jtd.2021.v19.a3574 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 135-146 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12190/9512 Copyright (c) 2021 Adi Wirawan, Fuad Surastyo Pranoto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12191 2025-10-03T07:30:25Z ijoa:ART

Design and experimental Verification of Vibration Testing Fixture for Flight Control Panel Wijaya, Yusuf Giri Ula, Nur Mufidatul P.P., Mikhael Gilang Pribadi Muksin, Muksin Syah, Agus Harno Nurdin Test Fixture Vibration Natural Frequency Shaker In this research, experimental design and testing of the vibration test fixture were carried out. The designed vibration test fixture is used to test the FCP, which is one of the components of avionics in aircraft. FCP vibration testing is carried out using the DO-160 test standard. The test has a test frequency range from 5 to 500 Hz. Therefore, the vibration test fixture must have a natural frequency above 600 Hz. The vibration test fixture is designed using a T-type model with modifications to get optimal results. The raw material used to make the test fixture is aluminum. The test fixture has a natural frequency value above 500 Hz, and both were tested using FEM simulation and experimental tests. Therefore, the vibration test fixture that is made meets the requirements for vibration testing on FCP. The difference in the natural frequency value from the FEM simulation and experimental test results on the vibration test fixture is 14.61% on the Z-axis, 10.61% on the X-axis, and 9.74 on the Y-axis.   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12191 10.30536/j.jtd.2021.v19.a3701 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 157-168 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12191/9513 Copyright (c) 2021 Yusuf Giri Wijaya, Nur Mufidatul Ula, Mikhael Gilang Pribadi P.P., Muksin, Agus Harno Nurdin Syah https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12194 2025-10-03T07:30:25Z ijoa:ART

Design Optimization of A Conventional Rocket Nozzle Using Coupled Thermo-Structural Analysis Saputra, M. Dito Andria, Novi Solid Rocket Nozzle Thermo-Structural Analysis Thrust in a rocket is gained by expelling the combustion gas through a nozzle.  This rocket nozzle is a vital component during the conversion of chemical energy into kinetic energy. Consequently, it is exposed to extreme temperature and pressure resulted from gas combustion. Therefore to ensure a successful rocket operation, the nozzle must be able to maintain structural integrity when exposed to such environment. On the other hand, its structural weight must be kept minimum to reduce the overall weight of the rocket. Due to these circumstances, the nozzle design phase is very important since the nozzle significantly affects the whole rocket performance. LAPAN is currently developing some solid propellant based rocket. Each rocket’s nozzle is still designed using conventional configuration, consisting of a metal case and graphite insert. The nozzle relies on a thick structure geometry to maintain structural integrity. This approach induces a heavy-weight nozzle that burdens the rocket performance. This paper is attempted to optimize LAPAN’s conventional solid rocket nozzle design. A series of procedures are proposed to generate a lighter nozzle design. RX-450 rocket’s nozzle will be used as the studied model in this paper.  Coupled thermo-structural analysis forms the main procedure to evaluate the proposed nozzle geometry structural integrity. The study succesfully provided an optimized nozzle geometry with sufficient strength and reduced weight. BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12194 10.30536/j.jtd.2021.v19.a3570 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 157-168 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12194/9514 Copyright (c) 2021 M. Dito Saputra, Novi Andria https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12195 2025-10-03T07:30:25Z ijoa:ART

Effect of Hybridization on Tensile, Shear and Compressive Properties of Carbon Based Fiber Reinforced Composites Abdurohman, Kosim Adhitya, Mohammad hybrid composites hybrid fiber resin infusion kevlar-carbon mechanical properties The high specific stiffness and strength of composites make them widely used   in defence, marine, and aerospace applications. Hybrid composites have increased use in high-tech applications. The glass/carbon and KC/carbon hybrid composites manufactured by vacuum assisted resin infusion methods are used in this study. The matrix used for both composites are vinylester resin. The glass/carbon and KC/carbon hybrid laminates arrangement is [G/C/G2/C/G2/C]s and [(KC)2/C3]s, respectively. The mechanical properties are evaluated according to ASTM standards. Fracture micrograph analysis are investigated using SEM. The comparison of mechanical properties and surface fracture of both hybrid composites have been investigated. The tensile and compressive strength of KC/carbon are higher than glass/carbon hybrid composites. However, the shear strength of KC/carbon is lower than glass/carbon hybrid composites. SEM micrograph exhibits that the KC/carbon has a good fiber/matrix and interlayer bond better than glass/carbon hybrid composites.   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12195 10.30536/j.jtd.2021.v19.a3575 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 169-176 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12195/9515 Copyright (c) 2021 Kosim Abdurohman, Mohammad Adhitya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12196 2025-10-03T07:30:25Z ijoa:ART

Integrated Quality Analysis Method of Aluminum for Composite Propellant Production Sitompul, H. R. Wibowo, H. B. Abdillah, L. H. Ardianingsih, R. Restasari, A. Budi, R. S. Hartaya, K. Baiquni, M. Aluminum Composite Propellant Quality Analysis Quality analysis of Aluminum powder for solid fuel composite propellant was carried out to determine the critical parameters of the composite propellant characteristics. Two types of aluminum were analyzed for quality, including bulk density and true density using the Archimedes principle, particle shape, and size using SEM (Scanning Electron Microscope), crystallinity, and purity using XRD (Xray Diffraction), particle area with BET (Brunnauer-Emmet-Teller) and BJH  (Barret-Joyner-Halenda) adsorption isotherm. To test the composite propellant made with 87.5% solid content and 18% AL content, then tested the characteristics of the propellant. The results of the analysis of the quality of aluminum for composite propellant raw materials have a very large influence on the quality of the resulting propellant, so an integrated, quick, and efficient quality analysis is needed. The critical parameters of Aluminum quality as propellant fuel are density, purity, particle shape and size, porosity/surface area, and crystallinity. Fast and efficient integrated analysis can be performed using new instruments, such as shape and size analysis with SEM, purity and crystallinity analysis with XRD, density analysis with a densitometer. AL2 which have smaller particle size, better density and shape parameters value, less pores and surface area than AL1, can be used to produce a higher quality composite propellant. BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12196 10.30536/j.jtd.2021.v19.a3655 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 177-192 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12196/9516 Copyright (c) 2021 H. R. Sitompul, H. B. Wibowo, L. H. Abdillah, R. Ardianingsih, A. Restasari, R. S. Budi, K. Hartaya, M. Baiquni https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12197 2025-10-03T07:30:25Z ijoa:ART

Structure Relaxation Disruption on Temperature-dependence of Polymerization of HTPB-based Polyurethane Restasari, Afni Hamid, Nur Marpaung, Leonard Rusnaenah, Andi Sukma, Adi Sukma, Rahmawati Polymerization Polyurethane Relaxation temperature Temperature effect The temperature-dependence of polymerization rate of hydroxyl-terminated polybutadiene (HTPB)-based polyurethane can be disrupted by a structure relaxation of polymer.  Objective of the study is to investigate the disruption on the polyurethane (PU) formed of various molecular weight of HTPB. The study was carried out by applying temperature of 50, 60 and 70 oC in measuring viscosity until 80 minutes of reaction. The sample that were used is HTPB with various molecular weight and Toluene diisocyanate (TDI). Based on decreasing value of viscosity, it is obtained that relaxation temperature of HTPB-based PU is around 60 – 70 oC. By applying Eyring equation of flow, it is found that relaxation of structure causes the existence of relaxation dominant-time (RDT). RDT is the reaction time at which molar volume reaches the maximum value. Furthermore, by determining activation entropy, the RDT was revealed to be a borderline between two type of polymerization. Linear reaction occurs before RDT, while cross-link reaction occurs after RDT. From structure point of view, PU-polymerization type of HTPB with low molecular weight tend to be more sensitive towards structure relaxation which is originated from hard segment. BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12197 10.30536/j.jtd.2021.v19.a3654 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 193-200 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12197/9517 Copyright (c) 2021 Afni Restasari, Nur Hamid, Leonard Marpaung, Andi Rusnaenah, Adi Sukma, Rahmawati Sukma https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12200 2025-10-03T07:30:25Z ijoa:ART

Study on The Development of Guidance System Technology for 122-140 mm Artillery Rocket Nugroho, Widianto Riyadl, Ahmad Muslimin, Ahmad Novi Setiawan, Rudi Triharjanto, Robertus Heru Yogaswara, Y. H. MRLS Rocket Control system Canard Thurster Circular Error Probable The increase in rocket Artillery accuracy means there will be fewer rockets to be used to destroy a target. This could reduce the needed budget and risk of weapon mobilization. Therefore, this research investigates the advancement in the guidance system technology for Artillery rockets, especially for 122-140 mm caliber. The objective of the research is to find a direction for the development guidance system for the Indonesian Artillery rocket (RHAN). The research use the descriptive-analytic method, in which data was collected from literature studies and inductive analysis was performed. The data shows two kinds of actuators were used, a canard and thrusters. In canard mode, 2 strategies were used, i.e. with bearing to isolate the roll from the rocket, in which 5 control algorithms were used, and without bearing, which 2 control algorithms were used. In thruster mode, there was 5 control algorithms used. Further analysis shows that the best performance is obtained from 2 modes of the canard strategy with bearing, and 2 modes of the thruster strategy. Therefore, it is concluded that the 4 modes can be used to be implemented in RHAN which needs to be added to the control system.   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12200 10.30536/j.jtd.2021.v19.a3691 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 201-212 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12200/9518 Copyright (c) 2021 Widianto Nugroho, Ahmad Riyadl, Ahmad Novi Muslimin, Rudi Setiawan, Robertus Heru Triharjanto, Y. H. Yogaswara https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12201 2025-10-20T06:58:16Z ijoa:ART

Numerical Investigation of Supersonic and Hypersonic Shock-Wave/Boundary-Layer Interactions Bura, Romie Oktovianus Graham T. Roberts Yufeng Yao Neil D. Sandham supersonic hypersonic shock-wave/boundary-layer interactions numerical Numerical simulations of 2-D supersonic and hypersonic laminar Shock-Wave/Boundary-Layer Interactions (SBLIs) were carried out by solving the Navier-Stokes (NS)equations using a compressible flow code over a wide range of Mach numbers and shockstrengths. The results obtained at Mach 2.0 and 7.73 were compared with experimentaldata. In addition, the numerical data were further analyzed using correlation laws derivedby previous researchers based on the free interaction concept, extended here to higherMach numbers. The results indicate that this concept is valid for separated laminar hypersonicflows with SBLIs. For interference heating, the correlation technique based on thewell-established power law relationship between peak heating and peak pressures yieldedencouraging results consistent with other correlations for laminar interference heating athypersonic speeds. BRIN Publishing 2025-10-05 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12201 10.55981/ijoa.2025.12201 Indonesian Journal of Aerospace; Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace; 77-96 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12201/10628 Copyright (c) 2025 Author (s) https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12202 2025-10-03T07:30:25Z ijoa:ART

The Effect of Payload Weight to Mean Coil Diameter of Helical Compression Spring for Payload Separation Laksono , Shandi Prio Weight is one of major factors in sounding rocket or launch vehicle design. Indeed, payload weight contributes to the rocket weight. Sounding rocket release the payload in the upper atmosphere at the certain altitude. Sounding rocket is intended to carry the payload as much as possible. In payload jettison/separation system, helical compression spring is commonly used. The previous study result show that in order to avoid mechanical failure of the spring, if the payload weight was 60 kg, the minimum wire diameter of helical compression spring must be 8 mm with mean coil diameter of 80-96 mm. Based on the previous study result, this study investigated the effect of payload weight to mean coil diameter of helical compression spring for payload separation. The numerical method was used in this study. In order to increase the payload weight, the mean coil diameter must be decreased. The results obtained show that the maximum payload weight that can be used was 77 kg with the maximum mean coil diameter of 80 mm, and free length of 0.417 m.  In addition, safety factor of 1.65 and energy storing of 81.8 N.m was obtained.   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12202 10.30536/j.jtd.2021.v19.a3565 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 213-222 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12202/9519 Copyright (c) 2021 Shandi Prio Laksono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12203 2025-10-03T07:30:25Z ijoa:ART

Three-Dimensional (3D) Flight Planning Optimization Using Genetic Algorithm Considering FCOM Data Nugraha, Calvarico Bima Ruseno, Neno 3D Flight Planning Trajectory Optimization Genetic Algorithm Flight Crew Operating Manual Fuel Saving Flight Planning is a document prepared by airline which consist of aircraft information, planned route, required fuel, carried load, weather forecast, etc. It needs to be submitted to ATC to get approval and then it will be used by pilot to guide the flight to reach the destination. Optimization in flight planning route is one of the essential factors in reducing fuel consumption to reduce cost and emission. The aim of this research is to optimize the flight planning route in Three-Dimensional approach using Genetic algorithm. Genetic algorithms (GA) are widely used in optimizations that includes many parameters, thus it could be used in flight planning optimization. The concept of GA is a heuristic search approach that inspired by Darwin’s theory of natural evolution which mimics “Survival of the fittestâ€. The method starts with a hexagon size containing nodes of possible points connecting departure and arrival airports. In this research the nodes are extracted using Dijkstra algorithm from previous research. The algorithm used population size of 500 individuals that generated with 0.01 mutation rate, 100 generation cycle, and 20 elite size. The case study covers routes in area of Indonesia which are flights of Jakarta – Tanjung Pinang, Jakarta – Makassar, and Jakarta – Manado. The different aircraft gross weights are analyzed to study the effect of aircraft weight to the resulted flight route. The aircraft performance database from Flight Crew Operating Manual (FCOM) of A320 aircraft was used to calculate the fuel burn. It is concluded that the algorithm able to find the optimal flight route as the best individual with range of cruise altitude from 35,000 to 39,000 ft. Results from Jakarta - Tanjung Pinang showed an average of fuel reduction of around 2.29% followed by Jakarta - Makassar with 13.28% and Jakarta - Manado with 15.68%. Although, the resulted altitude profile shows a fluctuation in the middle of route, in average it is a climb.   BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12203 10.30536/j.jtd.2021.v19.a3607 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021); 223-241 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12203/9521 Copyright (c) 2021 Calvarico Bima Nugraha, Neno Ruseno https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12204 2025-10-03T07:30:25Z ijoa:FUP

Full Pages JTD Vol 19 No.2 December 2021 Tekgan, Editorial Jurnal - BRIN Publishing 2021-12-30 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion https://ejournal.brin.go.id/ijoa/article/view/12204 Indonesian Journal of Aerospace; Vol. 19 No. 2 (2021) 3032-0895 Copyright (c) 2021 Editorial Jurnal Tekgan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12216 2025-10-03T07:30:25Z ijoa:FP

Front Pages JTD Vol 17 No.1 Juni 2019 Jurnal, Redaksi - BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12216 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12216/9525 Copyright (c) 2019 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12217 2025-10-03T07:30:25Z ijoa:ART

REVIEW VISUALISASI SCHLIEREN PADA TEROWONGAN ANGIN SUPERSONIK Hamonangan , Jefri Abner Visualisasi Schlieren Terowongan Angin Supersonik Terowongan angin merupakan sebuah fasilitas yang mensimulasikan aliran udara dengan berbagai variasi kecepatan pada sebuah benda. Peneliti dan perekayasa menggunakan terowngan angin untuk mengamati dan mengevaluasi perilaku sebuah benda pada kecepatan udara tertentu. Terdapat 2 metode dalam proses pengamatan perilaku benda pada pengujian terowongan angin, yaitu dengan menggunakan balance dan visualisasi dengan menggunakan schlieren.   BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12217 10.30536/j.jtd.2019.v17.a2999 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 1-10 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12217/9527 Copyright (c) 2019 Jefri Abner Hamonangan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12218 2025-10-03T07:30:25Z ijoa:ART

IN-ORBIT IMPLEMENTATION OF ERROR PATCHING METHODS FOR LAPAN-A3/IPB OBDH FIRMWARE SYSTEM Taufik, Muhammad Hasbi, Wahyudi Karim, Abdul error patching methods OBDH LAPAN-A3/IPB Satellites OBDH (On-board data handling) is a satellite subsystem that receives, processes, decides and executes commands from and to satellites. OBDH is built on two systems namely hardware and software integrated system (firmware system). In terms of hardware, OBDH uses a processor with 32bit RISC architecture, 128/256 Kbyte internal memory and a firmware system that is built using primitive programming. This programming uses the super loop architecture program and interrupt to manage the system to function properly. Problems occur when an error occurs in one of the functions in the interrupt routine resulting in failure of interpretation of commands or data from satellite sensors. This paper describes the implementation of the error patching methods on the LAPAN-A3/IPB Satellite OBDH firmware system in order to keep the system working well. Initial verification through testing on the ground have been successfully performed using engineering model of OBDH and hardware in the loop simulators (HWIL) module. Based on the test results, implementation on satellite has also been successfully done. BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12218 10.30536/j.jtd.2019.v17.a3012 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 11-18 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12218/9528 Copyright (c) 2019 Muhammad Taufik, Wahyudi Hasbi, Abdul Karim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12219 2025-10-03T07:30:25Z ijoa:ART

THE INFLUENCE OF THE ANGLE OF ATTACK ALPHA ON THE PRESSURE RECOVERY AT AERODYNAMICS INTERFACE PLANE INVESTIGATION Subagyo, Subagyo In the process of design, anaircraft to know the performance and stability requires testing in a wind tunnel.Similarly, the selection of engines for aircraft design embedded on conducted tests in a wind tunnel model air intake with some variation of the angle of attack.This paper examines the effect ofthe high angle of attack alpha testing aircraft air intake with a position of beta 0° on the subsonic regime with wind speeds of 65 ms-1.  Combat aircraft flying with an unexpected manoeuvre to avoidenemy attack nor did defence against missiles.Often the aircraft must fly to the position of a very high angle of attack.The theoretical value of the Pressure Recovery is approaching one in order to make the machine pinned can work optimally.Experimental observations of Pressure Recovery plotted against the variation of the angle of attack alpha.The observations show the performance design of aircraft engine inlet on the angle of attack alpha large can still give adequate pressure recovery.   BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12219 10.30536/j.jtd.2019.v17.a3033 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 19-28 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12219/9529 Copyright (c) 2019 Subagyo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12220 2025-10-03T07:30:25Z ijoa:ART

Analisis Kekuatan Struktur Komposit Dengan Ply Drop-off Pada Roda Pendarat Utama Pesawat Nir Awak Menggunakan Metode Elemen Hingga Wandono, Fajar Ari Adhitya, Mohammad ply drop-off struktur komposit roda pendarat utama pesawat nir awak metode elemen hingga, MSC Patran/Nastran kriteria kegagalan Tsai-Wu pengurangan massa Penggunaan ply drop-off telah banyak digunakan untuk mengoptimalkan struktur komposit sehingga memiliki massa yang lebih ringan dibandingkan dengan struktur komposit dengan penggunaan ketebalan seragam. Tulisan ini akan memprediksi kekuatan dan potensi pengurangan massa struktur komposit dengan menggunakan ply drop-off pada roda pendarat utama pesawat nir awak terhadap beban operasional menggunakan metode elemen hingga. Beban operasional diasumsikan merupakan beban statik akibat landing sebesar 245 N arah vertikal dan sebesar 78.75 N arah horizontal. Struktur roda pendarat utama dimodelkan menggunakan elemen Quad4 dengan memasukkan sifat mekanis dari material e-glass Woven Roving 185 pada software MSC. Patran/Nastran. Kriteria kegagalan yang digunakan adalah berdasarkan kriteria kegagalan Tsai-Wu dalam indeks kegagalan dan margin of safety. Hasil yang didapatkan adalah struktur roda pendarat utama memiliki indeks kegagalan 0.62 dan margin of safety sebesar 1.39. Dari hasil tersebut menandakan struktur roda pendarat utama cukup kuat dan tidak terjadi kegagalan dalam menerima beban operasional yang diberikan. Di samping itu, potensi pengurangan massa pada struktur roda pendarat utama menggunakan ply drop-off adalah sebesar 18%.   BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12220 10.30536/j.jtd.2019.v17.a3037 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 29-40 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12220/9534 Copyright (c) 2019 Fajar Ari Wandono, Mohammad Adhitya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12221 2025-10-03T07:30:25Z ijoa:ART

EFFECT OF FLAT AND HEMISPHERICALLY ENDED CYLINDER BIRD MODEL WITH FINITE ELEMENT MODELLING OF BIRD STRIKE Yuniarti, Endah Sitompul, Sahril Afandi Bird-strike bird-models finite-element This research studies influence of bird model on impact pressures during bird strike, namely Hugoniot and Stagnation pressure through initial modelling by numerical simulations using finite element method. Finite element simulation of bird strike have primarily modelled the bird as either a flat or hemispherically ended cylinder. The geometry is simulated with different L/D ratio, 1.4, 1.6, 1.8 and 2.0. Elastic-plastic hydrodynamic material model is used in simulation. Bird model simulation are using lagrangian method and initial velocities are 100, 200 and 300 m/s. Simulation results of hemispherically ended cylinder bird models show variation of L/D ratio provide Hugoniot pressure 10-19 times higher than stagnation pressure in L/D = 1.4, 8-18 times in L/D = 1.6, 9-17 times in L/D = 1.8 and 4-16 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2. As for cylindrical bird model show variation of L/D ratio provide Hugoniot pressure 35-38 times higher than stagnation pressure in L/D = 1.4, 30-47 times in L/D = 1.6, 31-52 times in L/D = 1.8 and 28-48 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.4 and 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2.   BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12221 10.30536/j.jtd.2019.v17.a3061 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 41-56 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12221/9535 Copyright (c) 2019 Endah Yuniarti, Sahril Afandi Sitompul https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12222 2025-10-03T07:30:25Z ijoa:ART

ANALYSIS OF ELECTRICAL LOAD ASSESSMENT LSU (LAPAN SURVEILLANCE UAV) 03 Setyadewi, Imas Tri Sumarna, Encung Prabowo, Yanuar LSU 03 Eletrical Load Assesment LSU 03 Aircraft was used for LSU MISI with capability cruise up to 340 km. LSU 03 has an operation for marine safety from illegal fishing. To support the monitoring mission of illegal fishing with operation range up to 250 km or 3 hours flight, several required system are needed such as autopilot system, datalink, propulsion, and payload. All of system then analysed by an ELA (Electrical Load Assessment) of the aircraft system to know the necessary power required to conduct the initial mission of the aircraft. ELA analysis is done by calculating the power requirement from each component specification and function test of the component for validation of calculation result. From the results of the study, the amount of power consumption is 35% from the spec calculation, which is 32.43 Wh which can be accommodated by a battery system up to 4.2 hours. Whereas for ignition or aircraft engines whose source of battery uses LIPO 2S 7.4 Vdc batteries can accommodate the ignition energy requirements for more than 11 hours.   BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12222 10.30536/j.jtd.2019.v17.a3108 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 57-66 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12222/9536 Copyright (c) 2019 Imas Tri Setyadewi, Encung Sumarna, Yanuar Prabowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12223 2025-10-03T07:30:25Z ijoa:ART

PENGEMBANGAN ANTENA HELIKS QUADRIFILAR 2,22 GHZ UNTUK SATELIT MIKRO Faizal, Iwan Priyanto, Irwan Ardinal, Rifki Suhata, Suhata Bentuk dasar antena heliks quadrifilar dikembangkan oleh C. C. Kilgus dari Laboratorium Fisika Terapan, Universitas Johns Hopkins, USA. Antena ini memiliki beamwidth yang lebar sampai 2400 dengan pola radiasi berbentuk jantung, berpolarisasi sirkular dan tidak memerlukan reflektor. Antena heliks quadrifilar memiliki rasio diameter terhadap tingginya 0,66. Artinya antena ini ditempatkan di on-board satelit sebagai pemancar (Tx). Ukuran dari antena ini adalah ½ λ ½ putaran dan termasuk dalam varian putaran kecil. Tujuan dari riset ini adalah membuat prototip antena heliks quadrifilar dengan frekuensi 2,22 GHz dan selanjutnya diuji dalam skala laboratorium. Dari hasil pengujian laboratorium, besarnya RL adalah -18.55 dB, besarnya VSWR adalah 1,26, besarnya lebar pita adalah 6,04 %, besarnya lebar berkas adalah 1700 dan besarnya penguatan adalah 5,19 dB.   BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12223 10.30536/j.jtd.2019.v17.a3116 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 67-78 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12223/9537 Copyright (c) 2019 Iwan Faizal, Irwan Priyanto, Rifki Ardinal, Suhata https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12224 2025-10-03T07:30:25Z ijoa:ART

METODA COROTATIONAL BEAM 2D UNTUK ANALISIS STATIK STRUKTUR NONLINIER GEOMETRIK Andria, Novi Zuhal, Lavi R. Gunawan, Leonardo Muhammad, Hari corotational beam CBM 2D nonlinear geometrik analisis statik stuktur Makalah ini membahas sebuah metoda corotational beam dua dimensi (CBM 2D) yang dapat digunakan untuk analisis statik struktur yang nonlinier secara geometri. Kombinasi antara formulasi corotational beam dan Euler-Bernouli beam Theory (EBT) membuat implementasi numerik metoda ini menjadi sangat sederhana dengan beban komputasi yang rendah sehingga sangat praktis untuk diaplikasikan. Akurasi dan efisiensi metoda ini terverifikasi melalui beberapa uji numerik yang dilakukan pada beberapa model uji yang terdapat pada literatur. Metoda ini pun mampu memberikan hasil yang akurat untuk kasus extensible beam dan struktur beam yang dibebani follower load. Hasil penelitian ini memverifikasi validitas, efisiensi, dan kepraktisan dari metoda yang dikembangkan.   BRIN Publishing 2019-06-21 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12224 10.30536/j.jtd.2019.v17.a3117 Indonesian Journal of Aerospace; Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara; 79-90 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12224/9538 Copyright (c) 2019 Novi Andria, Lavi R. Zuhal, Leonardo Gunawan, Hari Muhammad https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12229 2025-10-03T07:30:25Z ijoa:FP

Front Pages JTD Vol 15 No 2 Desember 2017 Jurnal, Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion https://ejournal.brin.go.id/ijoa/article/view/12229 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara 3032-0895 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12230 2025-10-03T07:30:25Z ijoa:ART

PERANCANGAN AUTOPILOT LATERAL-DIREKSIONAL PESAWAT NIRAWAK LSU-05 (THE DESIGN OF THE LATERAL-DIRECTIONAL AUTOPILOT FOR THE LSU-05 UNMANNED AERIAL VEHICLE) Fajar, Muhammad Ariffianto, Ony lateral-direksional autopilot PID Autopilot pada pesawat dikembangkan berdasarkan pada modus gerak pesawat yaitu modus gerak longitudinal dan lateral-directional. Pada makalah ini, dirancang autopilot pada modus gerak lateral-directional untuk pesawat LSU-05. Autopilot dirancang pada range kecepatan operasi pesawat yaitu 15 m/dtk, 20 m/dtk, 25 m/dtk, dan 30 m/dtk dengan ketinggian 1000 m. Autopilot yang dirancang adalah Roll Attitude Hold, Heading Hold dan Waypoint Following. Autopilot dirancang berdasarkan model linier dalam bentuk state-space. Pengendali yang digunakan adalah pengendali Proportional-Integral-Derivative (PID). Hasil simulasi menunjukan nilai overshoot/undershoot tidak melebihi 5% dan settling time kurang dari 30 detik jika diberikan perintah step. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12230 10.30536/j.jtd.2017.v0.a2760 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 93-104 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12230/9539 Copyright (c) 2025 Muhammad Fajar, Ony Ariffianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12231 2025-10-03T07:30:26Z ijoa:ART

PENGARUH KOMPOSISI AP TERHADAP PROSESIBILITAS SLURRY PROPELAN DENGAN KANDUNGAN ALUMINIUM TINGGI (EFFECTS OF AMMONIUM PERCHLORATE COMPOSITION ON HIGH CONTENT ALUMINIUM PROPELLANT SLURRY) Restasari, Afni Suwana Budi, Rika Hartaya, Kendra Slurry propelan pseudoplastisitas viskositas pot life Sebagai padatan pengisi propelan, Ammonium perklorat (AP) dapat mempengaruhi sifat fluida dari slurry propelan yang penting dalam pencetakan untuk menghasilkan propelan yang homogen. Oleh karena itu, penelitian ini bertujuan untuk menemukan pengaruh komposisi AP (AP halus (APh): AP kasar(APk)) terhadap sifat fluida slurry yang meliputi viskositas, pot life dan indeks pseudoplastisitas. Dalam penelitian ini, dibuat slurry propelan A (APh : APk 1:2), propelan B (APh : APk 1:1), propelan C (APh : APk 3:2) dan propelan D (APh : APk 2:1). Metode yang digunakan meliputi pengukuran viskositas dengan viskometer Brookfield RVT spindle 07 pada 0,3 rpm setiap 15 menit. Sementara, di menit ke-35, viskositas pada 0,3; 0,5 dan 0,6 rpm diukur. Berdasarkan data tersebut, grafik ln viskositas vs waktu serta viskositas vs shear rate dibuat untuk menentukan persamaan viscosity build-up dan Power Law. Diketahui, nilai viskositas awal propelan dalam jangkauan 11.493 – 52945 P, dengan viskositas terendah dan pot life (13,12 menit) dimiliki oleh propelan A. Sementara, nilai indeks pseudoplastisitas propelan yang jangkauan 0,655 – 0,991, nilai terendahnya ditunjukkan oleh propelan D dan tertingginya ditunjukkan oleh propelan B, yang mana propelan A diketahui tidak sesuai untuk pencetakan dengan teknik vakum. Pada sisi lain, propelan C relatif baik untuk dikembangkan karena memiliki viskositas (17.506 P) dan laju kenaikan viskositasnya (247 P/menit) yang tidak berbeda jauh dengan propelan A, serta indeks pseudoplastisitas (0,972) sesuai untuk pencetakan dengan vakum. Disimpulkan, hubungan antara rasio APh : APk dengan sifat fluida propelan (viskositas, pot life dan pseudoplastisitas beragam oleh karena faktor packing dari partikel – partikel penyusun propelan. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12231 10.30536/j.jtd.2017.v0.a2509 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 105-114 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12231/9540 Copyright (c) 2025 Afni Restasari, Rika Suwana Budi, Kendra Hartaya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12232 2025-10-03T07:30:26Z ijoa:ART

EVALUASI KINETIKA DEKOMPOSISI TERMAL PROPELAN KOMPOSIT AP/HTPB DENGAN METODE KISSINGER, FLYNN WALL OZAWA DAN COATS - REDFREN Dew, Wiwiek Utami Decomposition Propellants DTA TGA DTG dekomposisi propelan Mekanisme dan kinetika dekomposisi propelan telah diinvestigasi menggunakan DTG/TA dengan tiga jenis metode yang berbeda yaitu Kissinger, Flynn Wall Ozawa dan Coats & Redfern. Penelitian ini bertujuan untuk mengetahui parameter kinetika dekomposisi propelan LAPAN. Propelan yang digunakan memiliki perbedaan komposisi Al dan jenis moda AP. Propelan RUM adalah propelan AP/HTPB. RX 450 adalah AP/HTPB/ Al (bimoda). Sementara itu, RX 1220 adalah AP/HTPB/ Al (trimoda). Pengujian termal berlangsung pada suhu 30 - 400oC dan atmosfer nitrogen berlaju alir 50 ml/menit. Hasil penelitian mengungkapkan bahwa semua jenis propelan terdekomposisi dengan mekanisme F1 (nukleasi acak dengan satu nukleus pada partikel individu). Energi aktivasi propelan berkisar antara 100,876 – 155,156 kJ/mol sementara faktor pre-eksponensial berkisar antara 4,57 x 107 â€“ 3,46 x 1012/min. Energi aktivasi (E) dan faktor pre-eksponensial (A) RX 1220 adalah terendah dari ketiga sampel. Penggunaan jenis AP trimodul menciptakan efek katalitik yang menurunkan besarnya energi aktivasi. Propelan RX 1220 lebih mudah terdekomposisi (lebih mudah bereaksi) daripada propelan RUM dan RX 450.  BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12232 10.30536/j.jtd.2017.v0.a2635 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 115-132 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12232/9541 Copyright (c) 2025 Wiwiek Utami Dew https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12233 2025-10-03T07:30:26Z ijoa:ART

PENELITIAN TRANSMISIBILITAS ALAT PEREDAM GETARAN PADA MUATAN ROKET RX 550 LAPAN (RESEARCH TRANSMISSIBILITY OF VIBRATION DAMPERS EQUIPMENTS ON ROCKET RX 550 LAPAN) Djatmiko , Agus Budi Peredam Getaran Transmisibilitas muatan roket vibration damper transmissibility rocket payload Setiap struktur rekayasa seperti halnya pada muatan roket, mempunyai massa dan elastisitas, maka struktur tersebut mempunyai potensi untuk menimbulkan getaran. Pada umumnya terjadinya getaran pada struktur rekayasa adalah tidak diinginkan, oleh karena itu sedapat mungkin getaran tersebut diusahakan untuk diredam. Percepatan pengganggu yang ditimbulkan oleh proses pembakaran pada roket dapat menyebabkan getaran dengan amplitudo yang besar yang mengakibatkan kerusakan  pada struktur mutan roket dan alat elektronik yang ada pada muatan roket sehingga tidak dapat bekerja seperti yang diinginkan. Berdasarkan pengalaman, alat elektronik akan mengalami kerusakan jika percepatan pengganggu sebesar 10 g yang bekerja pada roket tidak direduksi. Untuk itu dirancang suatu alat peredam getaran, peralatan tersebut terdiri dari pegas dan damper atau peredam yang disusun sedemikian rupa sehingga muncul efek redaman terhadap getaran. Pada penelitian ini digunakan pegas dengan kekakuan k = 120.000 N/m, faktor redaman  = 0,0503 dan massa muatan (m) = 10,5 kg, dengan percepatan sebesar 1 G dan frekuensi kerja dari 0 sampai dengan 2000 Hz. Tujuan penelitian transmisibilitas pada alat peredam getaran ini adalah untuk mengetahui besarnya percepatan yang ditransmisikan ke muatan roket. Hasil penelitian alat peredam, pada saat awal percepatan pengganggu atau G force yang ditransmisikan ke muatan roket sebesar 1 g atau TR = 1, tetapi setelah melewati resonansi atau  didapat G force yang ditransmisikan ke muatan roket sebesar  0,1 g atau TR = 0,1 (alat cukup baik). Dari hasil penelitian ini  dapat  dikatakan bahwa alat peredam dapat digunakan untuk meredam  getaran pada muatan roket RX 550. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12233 10.30536/j.jtd.2017.v0.a2497 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 133-142 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12233/9542 Copyright (c) 2025 Agus Budi Djatmiko https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12234 2025-10-03T07:30:26Z ijoa:ART

PENGARUH KETEBALAN DI TENGAH TABUNG MOTOR ROKET RX 122 YANG PANJANG (THE EFFECT OF THICKNESS IN THE MIDDLE OF RX 122 LONG ROCKET MOTOR TUBE) Ediwan, Ediwan tabung roket pengaruh tekanan rocket tube pressure effect Pada perhitungan tabung roket akibat pengaruh tekanan dan temperatur, bila perbandingan antara panjang dan diameter cukup besar, perlu memperhitungkan terjadinya tegangan bending akibat berat dan tegangan buckling akibat ketebalan. Untuk menghindari tegangan tersebut maka bagian tengah tabung harus lebih tebal agar tegangan bagian tengah berkurang, tetapi tidak menimbulkan tegangan yang lebih besar lagi. Analisis yang lebih mendalam tentang tabung dilakukan pada tabung yang cukup panjang yaitu 2000 mm dan diameter 122 mm. Analisis yang dilakukan hanya dari pengaruh tekanan saja pada tabung yang tebalnya sama dan tabung yang tengahnya dipertebal, dengan tujuan untuk melihat pengaruh penebalan bagian tengah tabung tersebut dan sampai ketebalan berapa tabung bagian tengah diizinkan sehingga akibat terjadinya bending dan buckling dapat diabaikan. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12234 10.30536/j.jtd.2017.v0.a2503 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 143-150 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12234/9543 Copyright (c) 2025 Ediwan Ediwan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12235 2025-10-03T07:30:26Z ijoa:ART

KARAKTERISTIK RAW MATERIAL EPOXY RESIN TIPE BQTN-EX 157 YANG DIGUNAKAN SEBAGAI MATRIK PADA KOMPOSIT (THE CHARACTERISTICS OF RAW MATERIAL BQTN-EX 157 EPOXY RESIN USED AS COMPOSITES MATRIX) Rahayu, Sri Siahaan, Mabe epoxy resin hardener fraksi volume ultimate tensile streght densitas Tujuan dari penelitian adalah mendapatkan karakterisasi raw material resin yang digunakan sebagai matrik pada komposit. Resin adalah material polimer yang kaku atau semi kaku pada suhu kamar, sedangkan epoxy resin adalah kelas sistem ikatan kimia organik yang digunakan dalam preparat lapisan khusus atau perekat. Penelitian ini melaporkan pengaruh komposisi resin epoxy BQTN-EX 157 dengan hardener terhadap sifat mekanik, fisis, dan kimia. Untuk itu, sampel dibuat dengan variasi komposisi campuran (fraksi volume) antara epoxy resin dengan hardener 2:1/4, 2:1/2, 2:3/4, dan 2:1. Kemudian campuran dicetak menjadi lembaran plat selama 7 hari, setelah itu lembaran plat dibentuk menjadi spesimen uji. Selanjutnya spesimen diuji kuat tariknya (σu) dengan Universal Testing Machines (UTM) seri AND RTF-2410, densitasnya (Ï) dengan densitometer seri FH-MD200, dan group molekulernya dengan FTIR seri IRPrestige-21. Secara berturut-turut, nilai rata-rata kuat tarik terendah dan tertinggi adalah 16.4872 dan 57.9254 MPa yang dihasilkan pada komposisi campuran 2 : 1/4 dan 2 : 1,  nilai  rata-rata densitas terendah 1.1065 g/cc dan tertinggi 1.1430 g/cc pada komposisi campuran 2 :1 dan 2 : 1/4. Selanjutnya nilai frekuensi penyerapan terjadi pada 1050 ~ 1700 cm-1 dan pada daerah frekuensi ini terjadi pembentukan peak C-O dan C=C terendah dan  tertinggi. Dengan demikian dapat disimpulkan bahwa jika jumlah fraksi volume dari hardener semakin banyak dicampur dengan resin epoxy akan meningkatkan kuat tarik; menurunkan densitas, dan menghasilkan pembentukan senyawa C-O dan C=C. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12235 10.30536/j.jtd.2017.v0.a2526 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 151-160 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12235/9565 Copyright (c) 2025 Sri Rahayu, Mabe Siahaan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12236 2025-10-03T07:30:26Z ijoa:ART

ANALISIS KETINGGIAN ORBIT SATELIT LAPAN-TUBSAT SETELAH SATU TAHUN BEROPERASI Judianto, Chusnul Tri Satelit LAPAN-TUBSAT Atmosfir Peluruhan Orbit Satelit LAPAN-TUBSAT merupakan salah satu program unggulan pengembangan satelit eksperimen berskala nasional yang dilakukan oleh LAPAN. Sejak diluncurkan tanggal 10 Januari 2007, kini telah mengorbit selama 1 tahun lamanya. Pengontrolan data status kesehatan satelit (house keeping data) terus dilakukan setiap harinya dengan mengamati semua komponen utama satelit seperti batery, solar panel, star sensor, camera sony dan kappa, gyroscope, sistem komunikasi payload S band 2220 MHz dan TTC UHF 437,325 MHz. Dari data TTC yang diperoleh ternyata setelah satu tahun mengorbit, telah terjadi perubahan ketinggian orbit satelit LAPAN-TUBSAT dari ketinggian orbitnya saat pertama diluncurkan. Peluruhan ini diakibatkan oleh pengaruh kondisi lapisan teratas atmosfir. Dalam tulisan ini akan dijelaskan fenomena peluruhan orbit satelit LAPAN-TUBSAT setelah satu tahun operasi dengan menganalisis data keplerian atau 2-line element yang digunakan. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12236 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12236/9544 Copyright (c) 2025 Chusnul Tri Judianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12238 2025-10-03T07:30:26Z ijoa:ART

ANALISIS PERUBAHAN SUHU SATELIT LAPAN-TUBSAT Prabowo, Gunawan S Saefudin, M Arief Analisa data satelit LAPAN-TUBSAT dapat digunakan untuk mengetahui sejauh mana suhu ekstrim yang terjadi, kondisi suhu sehari-hari dan perubahannya. Dari pengolahan data didapatkan bahwa temperatur yang tertinggi adalah sekitar 70ºC s.d 80ºC, temperatur rata-rata tertinggi yang ada menunjukkan harga sekitar 25ºC dan terendah menunjukkan -40ºC, dan perubahan suhu rata-rata berkisar antara 0,003ºC/detik dengan perubahan kecepatan suhu yang ekstrem sekitar 0.04ºC/detik, data ini dapat menjadi catatan bagi proses pengembangan dan manufaktur sub sistem yang sedang dikembangkan LAPAN Analisa data satelit LAPAN-TUBSAT dapat digunakan untuk mengetahui sejauh mana suhu ekstrim yang terjadi, kondisi suhu sehari-hari dan perubahannya. Dari pengolahan data didapatkan bahwa temperatur yang tertinggi adalah sekitar 70ºC s.d 80ºC, temperatur rata-rata tertinggi yang ada menunjukkan harga sekitar 25ºC dan terendah menunjukkan -40ºC, dan perubahan suhu rata-rata berkisar antara 0,003ºC/detik dengan perubahan kecepatan suhu yang ekstrem sekitar 0.04ºC/detik, data ini dapat menjadi catatan bagi proses pengembangan dan manufaktur sub sistem yang sedang dikembangkan LAPAN. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12238 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12238/9547 Copyright (c) 2025 Gunawan S Prabowo, M Arief Saefudin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12239 2025-10-03T07:30:26Z ijoa:ART

DESAIN ARSITEKTUR STRUKTUR PENAMPANG POTONG SEPANJANG BENTANG SUDU AERODINAMIK TURBIN ANGIN 50 kW Ismail, Maryono Keandalan struktur sudu turbin angin secara umum dapat diukur dari karakteristiknya, a.l; ringan, kuat terhadap beban bending, rigid terhadap beban torsi dan tahan terhadap kondisi buruk lingkungan. Keandalan sudu dapat ditingkatkan dengan mendesain;(i). spar yang berfungsi sebagai stiffeners dan (ii). konfigurasi laminates schedule sepanjang bentang sudu. Dari analisis desain dipilih; bentuk spar, karateristik laminat dan konfigurasi laminates schedule sepanjang bentang sudu turbin angin. Bentuk spar yang dipilih adalah, spar penampang U bercuping karena lebih sederhana dan lebih mudah dibuat dibandingkan dengan spar penampang segi empat. Bagian kaki dan cuping spar menempel pada permukaan cangkang sudu bawah bagian dalam serta tudungnya menempel pada permukaan cangkang sudu atas bagian dalam. Laminates schedule di sepanjang bentang sudu turbin angin, disusun dalam 5 segmen r/R airfoil blade (0,1~1,0), 1 segmen r/R root blade (0,0~0,1) dan segmen spar sepanjang bentang sudu, dengan pilihan varian laminat [(0º/90º)/(±45º)/(0º/90º)]n. Direkomendasikan untuk memakai komposit hibrid CFRP (epoksi) dan GFRP (epoksi/poliester). Secara kualitatif, metode desain ini dapat diterapkan untuk arsitektur struktur penampang potong sudu turbin angin skala menengah 50 kW yang dikembangkan LAPAN dan untuk sudu turbin angin kapasitas 10~100 kW. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12239 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12239/9548 Copyright (c) 2025 Maryono Ismail https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12240 2025-10-03T07:30:26Z ijoa:ART

PEMBUATAN KODE DESAIN DAN ANALISIS TURBIN ANGIN SUMBU VERTIKAL DARRIEUS TIPE-H Arsad, Agus Muhamad Hartono, Firman Turbin angin Darrieus Single streamtube model Makalah ini menjelaskan tentang pembuatan kode desain dan analisis turbin angin sumbu vertikal Darrieus. Dalam kode yang dikembangkan ini, turbin angin dimodelkan sebagai airfoil dua dimensi yang berputar sementara gaya sudu dihitung dengan menggunakan model tabung aliran tunggal dengan mengasumsikan distribusi kecepatan free stream sepanjang arah aksial turbin bervariasi linier. Teori elemen sudu dan teori momentum digunakan untuk mencari hubungan antara nilai parameter turbin dengan performa turbin angin. Pada kode ini, jumlah sudu dapat divariasikan antara 2 sampai dengan 10 buah. Tipe airfoil sudu dapat disesuaikan, namun kode ini menyediakan 5 tipe airfoil yang dapat dipilih yaitu NACA 0012, 0015, 0018, 0021 dan 0025. Dibandingkan dengan referensi, hasil analisis menunjukkan bahwa secara kualitatif kode ini cukup baik. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12240 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12240/9551 Copyright (c) 2025 Agus Muhamad Arsad, Firman Hartono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12244 2025-10-03T07:30:26Z ijoa:ART

RANCANG BANGUN ROTOR TURBIN ANGIN 10 KW UNTUK MEMPEROLEH DAYA OPTIMUM PADA VARIASI JUMLAH DAN DIAMETER SUDU Atmadi, Sulistyo Fitroh, Ahmad Jamaludin SKEA 10 kW Jumlah sudu Diameter rotor Penelitian ini merupakan bagian dari kegiatan penelitian untuk mendapatkan rancangan baru sudu rotor Turbin Angin 10 kW. Putaran rotor disesuaikan dengan putaran rancangan generator, yaitu 270 rpm. Pada kecepatan angin 10 m/det, rotor diharapkan mampu menghasilkan daya sekitar 12 kW. Penelitian dilakukan dengan memvariasikan jumlah sudu dan diameter rotor. Dengan menggunakan Computational Fluid Dynamic serta memperhitungkan pengaruh jumlah sudu dan diameter sudu, hasil perhitungan menunjukkan bahwa semakin banyak jumlah sudu, maka daya maksimum yang dapat dihasilkan rotor akan semakin kecil. Selain itu penambahan diameter rotor tidak selalu menghasilkan kenaikan daya. Pada jumlah sudu tertentu terdapat diameter optimal yang menghasilkan daya maksimum. Penelitian ini memberikan kesimpulan bahwa rotor akan menghasilkan daya lebih besar dari 12 kW bila menggunakan jumlah sudu sama dengan dua dengan diameter rotor antara 9,2 hingga 11,2 m. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12244 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12244/9552 Copyright (c) 2025 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12246 2025-10-03T07:30:26Z ijoa:ART

ANALISIS DEFLEKSI DAN TEGANGAN STRUKTUR ROKET RX-320 PADA WAKTU HANDLING DENGAN METODE ELEMEN HINGGA (FEM) Sugiarmadji HPS Setiadi Tegangan dan lendutan Handling roket Metode Elemen Hingga Analisis kekuatan struktur pada waktu handling roket perlu dilakukan, seperti ketika akan menjalani penimbangan untuk mencari letak c.g (center of gravity) roket ataupun ketika roket diletakkan di atas launcher. Roket biasanya diangkat dengan menggunakan katrol yang dilengkapi dua buah clamp. Analisis defleksi dan tegangan yang terjadi akan dilakukan dengan menggunakan bantuan perangkat lunak berbasis Metoda Elemen Hingga (Finite Element Methods/FEM). Hasil analisis defleksi dan tegangan struktur roket RX-320, menunjukkan terjadinya tegangan geser maksimum sebesar maks = 85.188,71 Pa. Oleh karena itu bahan tabung masih aman sekali terhadap beban yang bekerja. Tegangan geser ini dapat mempengaruhi lapisan liner dan propelan roket. Besarnya defleksi maksimum pada struktur roket adalah sebesar 5.1903E-3 mm yang terjadi pada nodal no. 25373. Lokasi ini berada di ujung struktur nose cone. Besarnya defleksi di daerah struktur tabung, harganya relatif kecil. Oleh karena itu, pengaruh terjadinya defleksi terhadap propelan dan liner masih bisa diabaikan. Namun demikian, selama menjalani handling, roket harus diperlakukan dengan hati-hati, sehingga propelan dan liner tidak mengalami keretakan. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12246 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12246/9555 Copyright (c) 2025 Sugiarmadji HPS, Setiadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12248 2025-10-03T07:30:26Z ijoa:ART

DESAIN DAN PEMBUATAN NOSEL DENGAN BLAST TUBE DENGAN METODE SHRINK-FIT Robertus Heru T Mariani, Lilis Roket Desain Struktur Termal Makalah ini membahas tentang desain struktur, pembuatan dan pengujian nosel roket yang menggunakan blast tube. Blast tube ditempatkan pada nosel motor roket untuk memberikan ruang yang aman bagi komponen elektronik kendali yang berada di ekor roket. Karena geometrinya kompleks, komponen-komponen struktur dari nosel dibagi menjadi beberapa bagian. Grafit dipilih sebagai bahan ablatif untuk blast tube dan nosel. Metode shrink-fit digunakan untuk menyatukan grafit dengan struktur logamnya. Anyaman serat kaca digunakan untuk bahan insulasi pada bagian luar blast tube dan nosel, karena diperkirakan suhunya masih terlalu panas untuk komponen elektronik sistem kendali yang terbuat dari plastik. Uji tekanan hidrostatis dilakukan untuk melihat tekanan maksimum yang bisa ditahan blast tube. Uji penyalaan statik dilakukan untuk memvalidasi desain propulsi dan melihat apakah struktur nosel dapat bertahan seperti prediksi. Hasil test menunjukkan bahwa blast tube dapat menahan tekanan dan suhu selama penyalaan. Namun, modifikasi perlu dilakukan di bagian divergen untuk menghindari terlepasnya grafit, seperti yang terjadi saat uji statik. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12248 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12248/9556 Copyright (c) 2025 Robertus Heru T, Lilis Mariani https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12249 2025-10-03T07:30:26Z ijoa:ART

ANALISIS LAPISAN BATAS ALIRAN DALAM NOSEL STUDI KASUS: NOSEL RX 122 Fitroh, Ahmad Jamaludin Saeri Lapisan batas Nosel Telah dilakukan simulasi dan perhitungan lapisan batas permukaan dinding bagian dalam nosel. Studi kasusnya adalah nosel RX 122. Nosel mempunyai diameter inlet, throat, dan exit masing-masing 100, 34, dan 96 mm. Simulasi dan analisis lapisan batas dilakukan dengan kondisi batas tekanan dan temperatur ruang bakar masing - masing 59 bar dan 3.000 K. Hasil simulasi menunjukkan bahwa lapisan batas tetap terjadi mulai dari nosel bagian depan (up stream throat) hingga ke belakang (down stream throat). Lapisan batas semakin menebal pada posisi mendekati inlet dan exit. Tebal lapisan batas di dekat inlet dan di dekat exit masing-masing adalah 0,28dan 0,67 mm.   BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12249 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12249/9557 Copyright (c) 2025 Ahmad Jamaludin Fitroh, Saeri https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12250 2025-10-03T07:30:26Z ijoa:ART

PERANCANGAN SISTEM PROPULSI FFAR DENGAN NOSEL TUNGGAL Samosir, Ganda Nuryanto, Agus FFAR Roket taktis Nosel jamak Nosel Tunggal Komposit Double base Roket FFAR (Folding Fin Aerial Rocket), merupakan roket taktis dengan diameter dan panjang, berturut-turut 70 mm dan 680 mm. Roket ini dapat digunakan, baik dari darat ke darat, udara ke udara, dan bahkan dari udara ke darat. Roket FFAR 2.75”, mempunyai 4 (empat) buah nosel kecil-kecil sejenis (Multi Nosel) yang pemasangannya diatur sedemikian rupa, sehingga satu dengan lainnya membentuk sudut tertentu. Dengan posisi nosel-nosel seperti ini, dapat menghasilkan efek puntir (sebagai mana gerak laju peluru) pada saat terbang, sehingga roket ini mempunyai jangkauan horizontal sekitar 8 km pada sudut elevasi 40º. Roket substitusi FFAR (RX-70) mempunyai 1 (satu) nosel (Nosel Tunggal), berbahan bakar propelan padat jenis komposit, sementara FFAR asli menggunakan tipe double base. Paper ini membahas simulasi perancangan sistem propulsi, pembuatan dan pengujian (statik maupun terbang) roket RX-70 dengan nosel tunggal sebagai pengganti FFAR nosel jamak. Dari hasil uji terbang yang telah dilaksanakan mulai tahun 2004 di Pandanwangi-Jawa Timur dan dilanjutkan di Pameugpeuk-Jawa Barat, diketahui bahwa roket RX-70 mempunyai jangkauan horizontal 7,8 km pada sudut elevasi 40°, terjadi penyimpangan 2,5 % dari rancangan. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12250 Indonesian Journal of Aerospace; Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12250/9559 Copyright (c) 2025 Ganda Samosir, Agus Nuryanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12252 2025-10-03T07:30:26Z ijoa:ART

ANALISIS STRUKTUR NOSEL RX 320 DENGAN MENGGUNAKAN BAHAN S45C Edwan Roket Nosel Statik Pada bulan Mei 2008 serta bulan Juli 2008 telah dilakukan uji terbang roket RX 320. Walaupun hasil uji terbang yang telah dilakukan cukup baik, namun masih diperlukan perbaikan, baik desain maupun proses pembuatannya agar lebih ringan serta lebih mudah proses pemasangannya. Pada bagian sisi masuk, hanya menerima beban tekanan saja karena bagian tersebut dilindungi dengan grafit, sedangkan bagian divergen hanya menerima beban temperatur saja, sehingga analisis yang dilakukan disesuaikan dengan beban yang diterima struktur nosel tersebut. Dari simulasi beban tersebut diperoleh tegangan yang terjadi pada kedua bagian nosel tersebut, faktor keamanan bagian konvergen akibat pengaruh tekanan sebesar 4 atm sedangkan bagian divergen yang menerima beban temperatur sebesar 1.7, sehingga tegangan terbesar sesuai dimensi roket yang dibuat adalah pada bagian divergen akibat pengaruh temperatur. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12252 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12252/9561 Copyright (c) 2025 Edwan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12253 2025-10-03T07:30:26Z ijoa:ART

PENELITIAN PRESTASI TERBANG ROKET SONDA SATU TINGKAT RX-320 Sembiring, Turah Prestasi terbang Roket sonda Penelitian prestasi terbang roket telah dilakukan terhadap roket RX-320 dengan sudut elevasi bervariasi dari 50º sampai dengan 80º. Bahan pendorong yang dipakai adalah jenis propelan HTPB. Uji statik roket berbobot 598 kg, berat propelan 254 kg menghasilkan gaya dorong 3500 kgf dan waktu pembakaran 13 detik. Dengan uji penerbangan telah dihitung presentasi terbang roket maksimum untuk berbagai sudut elevasi. Jarak jangkauan maksimum yang dicapai adalah 45,223 km dengan sudut elevasi 65º, tinggi maksimum yang dicapai adalah 27,595 km dengan sudut elevasi 80º, kecepatan maksimum yang dicapai adalah 2,531 mach dengan sudut elevasi 50º dan waktu terbang maksimum yang dicapai adalah 160 detik dengan sudut elevasi 80º. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12253 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12253/9562 Copyright (c) 2025 Turah Sembiring https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12254 2025-10-03T07:30:26Z ijoa:ART

THE DESIGN OF G2-SAT OPERATION SCENARIO FOR DATA ACQUISITION AND TRANSMISSION Fitrianingsih, Ery C2-SAT Mission concept Mission design Konsep misi satelit LAPAN generasi II (G2-SAT) dirancang berdasarkan muatan yang akan dibawa oleh G2-SAT yaitu sistem imager dengan empat kanal sebagai alat untuk menghasilkan citra yang dapat dimanfaatkan untuk program ketahanan pangan. Perancangan konsep ini dilakukan dengan menggabungkan hasil analisa orbit, data spesifikasi muatan yang telah diolah, akses satelit ke stasiun bumi serta dengan menerapkan batasan-batasan misi. Paper ini membahas tentang perancangan skenario operasi yang dapat diterapkan pada G2-SAT sebagai bagian dari sebuah konsep misi. Skenario operasi menjelaskan bagaimana data/citra di ambil oleh satelit dan dikirimkan dari satelit ke stasiun bumi sehingga tujuan misi yang direncanakan dapat dicapai. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12254 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12254/9563 Copyright (c) 2025 Ery Fitrianingsih https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12255 2025-10-03T07:30:26Z ijoa:ART

ANALISIS PENGUKURAN KETIDAKSTABILAN BIAS DARI SENSOR GYRO FORS-4 SATELIT LAPAN-A2 Mayditia, Hasan Prabowo, Gunawan S Bias drift Rotasi bumi Resolusi data Akuisisi data Bias instability (drift atau offset) merupakan salah satu jenis deviasi (error) pengukuran yang pasti ditemukan di dalam sensor-sensor inersial seperti halnya rategyro. Nilai error ini berbeda untuk setiap unit sensor, sehingga pengukuran nilai bias untuk masing-masing unit harus dilakukan. Ini dilakukan untuk memperoleh unitunit sensor dengan performa yang terbaik. Pengukuran nilai error bias (drift) telah dilakukan pada keenam unit sensor gyro (tipe ï­FORS-4) dengan memanfaatkan pergerakan rotasi bumi sebagai nilai referensi. Empat dari enam unit sensor gyro telah dipilih untuk selanjutnya digunakan dan diterbangkan pada satelit LAPAN-A2. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12255 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12255/9564 Copyright (c) 2025 Hasan Mayditia, Gunawan S Prabowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12256 2025-10-03T07:30:26Z ijoa:ART

ANALISIS DAN PERANCANGAN TOLERANSI KESALAHAN PADA ON BOARD DATA HANDLING SATELIT LAPAN A2 Karim, Abdul Prabowo, Gunawan S OBDH Toleransi kesalahan Satelit Redudansi Satelit Lapan A2 adalah satelit mikro LAPAN generasi ke-2 yang dibangun melalui kerjasama antara LAPAN dan Technisce Universitat Berlin. Dalam generasi ke-2 ini akan dilakukan pengembangan di dalam subsistem, khususnya subsistem OBDH (On Board Data Handling). OBDH mempunyai dua fungsi utama, pertama adalah menerima, memvalidasi, mendekode, dan mendistribusikan komando ke subsistem lain dalam sistem satelit, dan yang kedua mengumpulkan memproses data housekeeping serta data misi untuk dikirim ke stasiun bumi atau digunakan oleh On Board Computer. Hasil analisa sistem toleransi kesalahan (fault tolerance) yang akan diimplementasikan dalam perancangan OBDH akan dilihat dari tiga sisi yaitu redundansi perangkat keras, redundansi perangkat lunak, dan redundansi informasi. Penggunaan redundansi perangkat keras dengan menggandakan prosesor dan memory storage. Sedangkan redundansi perangkat lunak menggunakan metode single version check point and restart dan program boot strap sebagai cadangan sistem operasi dan program. Metode hamming code untuk error detection dan corection serta metode mirroring data akan digunakan sebagai redundansi informasi. Pemilihan redundansi tersebut telah mempertimbangkan keterbatasan dari konsumsi daya dan ukuran yang dibatasi oleh sistem satelit secara keseluruhan. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12256 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12256/9566 Copyright (c) 2025 Abdul Karim, Gunawan S Prabowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12257 2025-10-03T07:30:26Z ijoa:ART

VERIFICATION OF SCHRENK METHOD FOR WING LOADING ANALYSIS OF SMALL UNMANNED AIRCRAFT USING NAVIERSTOKES BASED CFD SIMULATION Soemaryanto, Arifin Rasyadi Rosid , Nurhayyan H aerodynamic loads CFD unmanned aircraft beban aerodinamis pesawat udara tanpa awak Prediksi dari beban aerodinamika yang terjadi pada sayap menjadi salah satu tahap yang penting dalam analisis struktur perancangan pesawat. Beberapa metode telah digunakan untuk mengestimasi besarnya beban aerodinamika pada sayap. Metode Schrenk umum digunakan untuk estimasi cepat perhitungan besar distribusi gaya angkat di sepanjang sayap. Guna mencapai tingkat akurasi yang tinggi dari prediksi aerodinamika, simulasi Computational Fluid Dynamics (CFD) dengan berbasis persamaan Navier-Stokes dapat digunakan. Pesawat nirawak LSU dipilih untuk merepresentasikan analisis aerodinamika pada pesawat nirawak dengan konfigurasi twin-tailboom pusher. Fokus dari studi yang dilakukan adalah untuk memverifikasi dari metode pendekatan dari Schrenk dengan menggunakan metode yang memiliki akurasi tinggi seperti simulasi CFD. Tujuan dari studi adalah untuk menghitung distribusi gaya angkat sepanjang sayap dan menentukan seberapa besar error dari kedua metode. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12257 10.30536/j.jtd.2017.v15.a2747 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 161-166 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12257/9568 Copyright (c) 2025 Arifin Rasyadi Soemaryanto, Nurhayyan H Rosid https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12258 2025-10-03T07:30:26Z ijoa:ART

RANCANGAN DAN ANALISIS AERODINAMIKA SUDU TURBIN ANGIN KAPASITAS 300 KW Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Turfcin Angin 300 kW Penelitian ini merupakan bagian dari kegiatan Perancangan SKEA 300 kW. Rotor dirancang dengan diameter 45 m dengan jumlah sudu tiga buah. Penampang sudu berbentuk airfoil NACA 4424, 4418, dan 4412 berurutan dari pangkal hingga ujung. Prestasi airfoil dihitung dengan simulasi secara CFD dengan mempertimbangkan efek bilangan Reynolds dan bilangan Mach. Geometri sudu mempunyai puntiran sebesar 15º. Dengan memperhitungkan rugi-rugi antara rotor dan generator, maka sudu akan mampu menghasilkan 350 kW pada kecepatan angin nominal 10 m/det dengan sudut pasang sudu sebesar 2º pada putaran 35 rpm dan tip speed ratio λ = 8,24. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12258 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12258/9567 Copyright (c) 2025 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12259 2025-10-03T07:30:26Z ijoa:ART

PENGEMBANGAN DETEKTOR SIGNAL RADIO MULTI CHANNEL UNTUK RADIO TRACKING ROKET MENGGUNAKAN LOGARITMIK AMPLIFIER Zain, Satria G. Susanto, Adi Widodo, Thomas Sri Widada, Wahyu Kliwati, Sri Pengukuran kuat signal radio telemetri roket sangat penting dilakukan untuk mengetahui hubungan kualitas signal dan data yang diterima. Power meter ini juga dapat diaplikasikan untuk deteksi perubahan sudut elevasi dan azimuth trayektori roket dengan menggunakan array antena yagi yang telah dikembangkan metodenya. Power meter radio mempunyai rentang pengukuran yang sempit, sehingga terjadi saturasi untuk pengukuran radio dengan power yang cukup besar. Tulisan ini membahas desain dan pengembangan power detektor untuk mendeteksi signal radio pada sistem telemetri roket dengan maksimum pengukutan 1 watt dan dapat diubah sesuai dengan kebutuhan. Signal power meter ini berbasis logarithmic amplifier dengan lebar band sampai dengan 100 db dengan ketelitian 0.02 dB. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12259 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12259/9570 Copyright (c) 2025 Satria G. Zain, Adi Susanto, Thomas Sri Widodo, Wahyu Widada, Sri Kliwati https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12260 2025-10-03T07:30:26Z ijoa:ART

APLIKASI PERANGKAT LUNAK SISTEM AKUISISI KECEPATAN REACTION WHEEL (SOFTWARE APPLICATION OF REACTION WHEEL SPEED ACQUISITION SYSTEM) Septanto, Harry perangkat lunak sistem akuisisi data reaction wheel respon transien software data acquisition system transient response Kegiatan alih teknologi melalui reverse engineering merupakan upaya yang dilakukan oleh negara berkembang dalam rangka memperkecil jarak ketimpangan dari negara maju dalam hal teknologi, termasuk teknologi satelit. Melakukan pengukuran dan akuisisi data dalam rangka mengurai informasi desain suatu komponen satelit adalah tahap pertama proses reverse engineering. Makalah ini melaporkan hasil penelitian mengenai pengembangan perangkat lunak sistem akuisisi data kecepatan wheel dari sebuah aktuator satelit yang disebut reaction wheel unit. Dalam aspek fase pengembangan satelit, sistem akuisisi data ini dapat digunakan sebagai perangkat pengujian untuk verifikasi di tingkat komponen. Data kecepatan wheel, yang diperoleh dari eksperimen yang dilakukan, ditampilkan dengan grafik respon transien. Berdasarkan analisis atas data tersebut, sistem akusisi data yang dikembangkan menjanjikan untuk digunakan dalam rangka pengukuran karakteristik dinamik reaction wheel sebagai upaya mengurai informasi desainnya. Selain itu, analisis yang telah dilakukan merepresentasikan bagian dasar dari tahap verifikasi di tingkat komponen. Hal ini menunjukkan bahwa sistem akusisi data ini menjanjikan untuk digunakan sebagai perangkat pengujian di dalam fase pengembangan satelit. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12260 10.30536/j.jtd.2017.v0.a2870 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara; 167-178 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12260/9569 Copyright (c) 2025 Harry Septanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12261 2025-10-03T07:30:26Z ijoa:BP

Back Pages JTD Vol 15 No 2 Desember 2017 Jurnal, Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12261 Indonesian Journal of Aerospace; Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12261/9571 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12262 2025-10-03T07:30:26Z ijoa:ART

TINJAUAN ASPEK KESELAMATAN UJI STATIK ROKET DENGAN PROPELAN KEROSEN–ASAM NITRAT TERHADAP MANUSIA DAN LINGKUNGAN Hakim , Afif Nur Trianto, Azis Widiatmoko, Pramujo Darmawan, Risky Uji Statik Keselamatan Analisis dampak Roket berpropelan cair Roket propelan cair memiliki beberapa kelebihan bila dibandingkan dengan roket propelan padat. Jumlah dan perbandingan bahan bakar terhadap oksidator dapat diatur untuk menghasilkan gaya dorong yang diinginkan. Salah satu propelan yang digunakan saat ini adalah pasangan kerosen dan asam nitrat. Namun, penggunaan propelan ini memunculkan masalah akibat karakter propelannya. Asam nitrat adalah cairan yang sangat korosif dan dapat menyebabkan efek yang serius terhadap tubuh manusia. Tinjauan terhadap keselamatan dalam uji statik roket cair telah dilakukan. Pada uji statik, kerosen dan asam nitrat akan diinjeksi ke dalam ruang bakar dan bereaksi sehingga menghasilkan gas bertekanan dan bertemperatur tinggi yang kemudian disemburkan melalui nosel untuk menghasilkan gaya dorong. Dari hasil kajian, daerah pengujian dibagi menjadi 5 zona. Zona 1, daerah yang paling berbahaya berjarak 0 – 3 m, dan zona 2, 3 – 40 m, adalah daerah yang masih dipengaruhi oleh gas-gas berbahaya. Pengamatan langsung dapat dilakukan pada jarak 50 m dengan perlindungan bangunan. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12262 Indonesian Journal of Aerospace; Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12262/9572 Copyright (c) 2025 Afif Nur Hakim , Azis Trianto, Pramujo Widiatmoko, Risky Darmawan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12264 2025-10-03T07:30:26Z ijoa:ART

ANALISIS SISTEM PAYLOAD UNTUK SATELIT IMAGER LAPAN Prabowo, Gunawan S Fitrianingsih, Ery Ketahanan pangan Satelit imager Muatan utama Berbasis pada informasi persyaratan misi dan berbagai masukan tentang kebutuhan satelit untuk mendukung program ketahanan pangan, serta dikaitkan dengan program LAPAN dalam proses penguasaan teknologi sistem satelit mikro, maka dibuatlah sebuah konsep pengembangan satelit yang memadukan penguasaan teknologi dan aplikasi riel untuk remote sensing. Dalam paper ini akan disampaikan analisa beberapa sistem muatan untuk mendukung program ketahanan pangan, dianalisis 3 buah sistem kamera yang akan dipergunakan sebagai muatan pokok dari satelit Imager LAPAN. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12264 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12264/9573 Copyright (c) 2025 Gunawan S Prabowo, Ery Fitrianingsih https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12265 2025-10-03T07:30:26Z ijoa:ART

ORBITAL HEATING RATES ANALYZING ON G2-SAT MATERIAL Arifin, Bustanul Thermal Orbital Heating rates Pendekatan Monte Carlo Telah dianalisa orbital heating rates pada material body G2-SAT, salah satu program pengembangan satelit di bidang Mekatronika LAPAN Rancabungur. Analisa ini dilakukan untuk mengetahui apakah material body pada G2-SAT memerlukan kontrol lebih lanjut seperti pemakaian material pelindung dalam hal ini MLI (Multy Layer Insulation dan penggunaan whitepaint pada solar array) jika G2-SAT mengalami pemanasan di orbitnya. Peralatan yang dipakai untuk menganalisa orbital heating rates ini adalah perangkat lunak Thermal Desktop 5.0 dengan menggunakan pendekatan Monte Carlo yang terdapat di dalamnya serta dengan mempertimbangkan semua data yang berhubungan dengan properties material, power dan orbit. Dalam pendekatan Monte Carlo ini berkas cahaya (array) dipancarkan dari permukaan sedangkan hal yang harus dilakukan adalah mencari permukaan mana yang terkena berkas cahaya. Selain itu, analisis tersebut dilakukan dengan berpijak dari konsep awal sistem thermal satelit yang telah ditentukan serta sumber radiasi panas yang terjadi pada G2-SAT. Hasil yang diperoleh berupa grafik yang menggambarkan besaran distribusi total absorbed flux yang terjadi pada G2-SAT body selama mengalami heating rates di orbitnya. Dari hasil analisa diketahui, sampai di orbit material tersebut memerlukan kontrol thermal lebih lanjut. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12265 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12265/9574 Copyright (c) 2025 Bustanul Arifin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12266 2025-10-03T07:30:26Z ijoa:ART

PENENTUAN POTENSIAL SEL TEORITIS PROSES ELEKTROLISIS NATRIUM KLORIDA MENJADI NATRIUM PERKLORAT Bayu Prianto Prianto, Bayu Potensial sel teoritis Elektrolisis Natrium klorida Natrium perklorat Natrium klorida (NaCl) dapat dioksidasi menjadi natrium perklorat (NaClO4) dengan menggunakan metode elektrokimia. Penelitian ini bertujuan untuk menentukan potensial sel teoritis proses elektrolisis NaCl hingga menjadi NaClO4. Proses elektrolis dibagi dalam empat (4) tahapan reaksi pembentukan, yaitu pembentukan : 1) natrium hipoklorit (NaClO), 2) natrium klorit (NaClO2), 3) natrium klorat (NaClO3) dan 4) natrium perklorat (NaClO4). Potensial sel teoritis dipelajari dengan menggunakan metode komputasi dengan perhitungan mekanika kuantum. Dalam penelitian ini digunakan himpunan dasar B3LYP/6-31++G(3df,3pd) dan B3LYP/6-311+G(2d,p) untuk mencari nilai potensial sel teoritis yang mendekati nilai sebenarnya. Hasil penelitian ini menunjukkan bahwa himpunan dasar B3LYP/6-31++G(3df,3pd) lebih akurat untuk menentukan potensial reduksi standar reaksi 2Cl Cl2  2e dibandingkan dengan himpunan dasar B3LYP/6-311+G(2d,p), dengan nilai potensial sel teoritis yang diperlukan untuk proses elektrolisis NaCl hingga menjadi NaClO4 adalah 2,362 Volt sampai dengan 2,918 Volt. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12266 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12266/9575 Copyright (c) 2025 Bayu Prianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12267 2025-10-03T07:30:27Z ijoa:ART

ANALISIS SISTEM DINAMIKA TERBANG (FLIGHT DYNAMICS) SATELIT LAPAN TUBSAT Rahman, Abdul Nuryanto, Agus LEOP Dinamika Terang (flight dynamics) LAPAN-TUBSAT Satellite Phase peluncuran dan awal orbit (Launch and Early Orbit Phase – LEOP) merupakan tahapan kritis dalam siklus pengoperasian sebuah satelit. Aktivitas utama dalam phase peluncuran dan awal orbit satelit terdiri dari pelacakan, pengecekan sistem satelit, pengendalian sikap dan pengujian muatan. Dalam makalah ini akan diulas tahapan-tahapan tersebut terkait dengan sistem dinamika terbang (Flight Dynamics) Satelit LAPAN-TUBSAT atau Satelit LAPAN-A1. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12267 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12267/9576 Copyright (c) 2025 Abdul Rahman, Agus Nuryanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12268 2025-10-03T07:30:27Z ijoa:ART

PENGEMBANGAN METODE PARAMETER AWAL ROTOR TURBIN ANGIN SUMBU VERTIKAL TIPE SAVONIUS Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Turbin angin Savonius Parameter awal Telah dikembangkan metode penentuan parameter awal rotor turbin angin sumbu vertikal tipe Savonius. Dengan daya dan kecepatan angin tertentu, maka kisaran luas, diameter, tinggi, dan kecepatan putar rotor dapat diketahui. Luas rotor sangat dipengaruhi oleh koefisien daya, cP. Kecepatan putar rotor rancangan dapat dihitung setelah diameter rotor dihitung dan Tip Speed Ratio ditentukan. Penelitian ini menggunakan harga koefisien daya (cP), Tip Speed Ratio (TSR), dan rasio diameter terhadap tinggi rotor (D/t) masing – masing 0,1 ; 0,8 ; dan 0,8. Hasil metode ini berupa tabel daya, kecepatan angin, luas rotor, diameter, tinggi serta kecepatan putar, dapat digunakan sebagai rancangan awal turbin angin Savonius bagi para pemula maupun bagi yang awam tentang turbin angin namun ingin membuat, karena turbin angin Savonius dapat dibuat secara sederhana. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12268 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12268/9577 Copyright (c) 2025 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12269 2025-10-03T07:30:27Z ijoa:ART

RANCANGAN DAN ANALISA SISTEM ORIENTASI TURBIN ANGIN KAPASITAS 2,5 KW Utama, Agus Bayu Turbin angin skala kecil Sistem orientasi Telah dirancang satu sistem orientasi dengan rotor eksentrik dan ekor pengarah dengan hinge (sumbu gantung) untuk turbin angin skala kecil kapasitas 2.5 kW, kemudian dilakukan analisa statis rumusan matematis berdasarkan teori kesetimbangan momen pada sumbu menara pada 2 kondisi kecepatan angin yaitu kecepatan angin sampai kecepatan angin rancagan (V ≤ Vdisain) dan kecepatan angin di atas kecepatan angin rancangan (V > Vdisain). Dengan kecepatan angin rancangan Vdisain = 10 m/s, maka nilai γo (sudut serang angin terhadap daun ekor) pada kondisi V ≤ Vdisain , adalah 6.16°. Nilai berat ekor G yang tadinya 250 N harus diturunkan menjadi 209 N, yaitu dengan mengubah nilai berat batang ekor menjadi m1=12.5kg dan nilai berat daun ekor menjadi m2=8.4 kg. Pada kondisi V > Vdisain rotor mulai berputar dengan sudut serang angin terhadap rotor δ. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12269 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12269/9578 Copyright (c) 2025 Agus Bayu Utama https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12270 2025-10-03T07:30:27Z ijoa:ART

PEREDAM KEJUT DAN GETARAN BAGI MUATAN RX-250 Triharjanto, Robertus Heru Makalah ini membahas perancangan dan pengujian sistem peredam kejut bagi payload RX-250. Sistem propulsi dari roket ini memberikan percepatan 12 g selama 12 detik, yang timbul (dan hilang) dalam tempo per-seribu detik. Beban tersebut, bersama dengan getaran yang timbul dari reaksi struktur roket terhadap beban aerodinamis dan stabilitas pembakaran, dapat mengakibatkan terjadinya kejut (shock) dan getaran yang merusak bagian sensitif dari payload elektronik. Untuk mencegah kerusakan pada payload elektronik, maka peredam kejut dan getaran yang terbuat dari pegas baja (wire type) dipasang antara roket dengan payload. Makalah ini membahas implementasi teknis perancangan yang meliputi uji darat dan uji terbang dari peredam tersebut yang pertama kali diadakan pada bulan Desember 2006. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12270 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12270/9579 Copyright (c) 2025 Robertus Heru Triharjanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12271 2025-10-03T07:30:27Z ijoa:ART

ANALISIS NOSEL MOTOR ROKET RX - 122 LAPAN SETELAH DILAKUKAN PEMOTONGAN PANJANG DAN DIAMETER Fitroh, Ahmad Jamaludin Saeri Nosel motor roket 122 Simulasi numerik Pemotongan panjang nosel Telah dilakukan penelitian dan analisis ulang nosel motor roket RX - 122 milik LAPAN. Nosel tersebut didesain untuk tekanan ruang bakar 70 bar. Hasil perhitungan secara analitis menunjukkan bahwa gaya dorong yang dihasilkan seharusnya sebesar 18,6 kN. Hasil simulasi numerik memberikan gaya dorong yang lebih kecil, yaitu sebesar 18,0 kN. Perbedaan tersebut dikarenakan adanya gesekan antara aliran gas dengan permukaan bagian dalam nosel yang mana ditandai dengan penurunan tekanan total sebesar 13%. Diameter awal nosel adalah 130 mm. Oleh karena keterbatasan dimensi motor roket, maka diameter nosel harus dibatasi maksimum 100 mm. Pengurangan diameter nosel dilakukan dengan cara memotong nosel sepanjang 85 mm. Pemotongan tersebut mengakibatkan penurunan prestasi nosel. Perhitungan secara analitis dan simulasi numerik memberikan gaya dorong masing – masing 18,1 kN dan 17,7 kN. Akibat pemotongan panjang nosel tersebut, maka gaya dorong yang dihasilkan nosel berkurang hanya sekitar 2%. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12271 Indonesian Journal of Aerospace; Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12271/9580 Copyright (c) 2025 Ahmad Jamaludin Fitroh, Saeri https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12279 2025-10-03T07:30:27Z ijoa:FP

Front Pages JTD Vol 15 No 1 Juni 2017 Jurnal, Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion https://ejournal.brin.go.id/ijoa/article/view/12279 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara 3032-0895 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12282 2025-10-03T07:30:27Z ijoa:ART

INVESTIGASI GAYA KONTAK/IMPAK PADA MAIN LANDING GEAR PESAWAT KOMUTER DENGAN PENDEKATAN MULTI-BODY SIMULATION (MBS) RIGID MODELS Hidayat, Dony Istiyanto, Jos Sumarsono, Danardono Agus Marta, Aryandi Gaya kontak/impak landing gear drop test multi-body simulation rigid body contact/impact force Pengujian landing gear yang bertujuan untuk mengetahui karakteristik gaya kontak/impak yang terjadi saat touchdown landing telah dilakukan. Pengujian eksperimental menggunakan apparatus membutuhkan waktu yang lama dan biaya yang besar. Vitual Landing Gear Drop Test (vLGDT) menggunakan perangkat lunak MSC ADAMS merupakan salah satu alternatif untuk pengujian tahap awal landing gear. Dari simulasi menggunakan vLGDT diperoleh nilai k = 5.0e5 N/m dan cmax = 1600 N.detik/m. Gaya kontak/impak yang terjadi pada simulasi menggunakan vLGDT sebesar 75996 N, sedangkan dari eksperimental sebesar 73612 N. Hasil vLGDT lebih besar 3.14% dibandingkan eksperimental. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12282 10.30536/j.jtd.2017.v15.a2529 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 1-10 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12282/9590 Copyright (c) 2025 Dony Hidayat, Jos Istiyanto, Danardono Agus Sumarsono; Aryandi Marta https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12283 2025-10-03T07:30:27Z ijoa:FP

Front Pages JTD Vol 16 No.1 Juni 2018 Jurnal, Redaksi - BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12283 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12283/9589 Copyright (c) 2018 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12284 2025-10-03T07:30:27Z ijoa:ART

EVALUASI TEKNIK PENIMBANGAN HIDROSTATIK PADA PENGUKURAN DENSITAS PROPELAN PADAT KOMPOSIT Abdillah, Luthfia Hajar Restasari, Afni Hartaya, Kendra Puspitasari, Ratna Rizky Densitas propelan penyimpangan teknik penimbangan hidrostatik Densitas menjadi salah satu data karakteristik propelan padat komposit yang penting. Data nilai densitas propelan ini digunakan dalam proses simulasi dan perancangan motor roket untuk mendapatkan performa roket yang diinginkan. Pengukuran densitas yang dilakukan selama ini menggunakan teknik penimbangan hidrostatik yang melibatkan pengukuran berat sampel di dalam air, sehingga dimungkinkan terjadi penyimpangan hasil pengukuran. Untuk itu tujuan dari penelitian ini adalah untuk mengetahui besarnya penyimpangan nilai densitas propelan yang terjadi dan mengetahui cara pengukuran yang tepat melalui teknik penimbangan hidrostatik sehingga menghasilkan nilai densitas yang lebih sesuai. Beberapa sampel propelan diukur densitasnya menggunakan dua instrumen densitometer untuk melihat adanya penyimpangan hasil pengukuran. Dari hasil penelitian diperoleh bahwa penyimpangan nilai densitas propelan yang terjadi berkisar antara 2,08% hingga 5,58% dengan adanya “delay†pembacaan berat sampel di air.   BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12284 10.30536/j.jtd.2018.v16.a2868 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 1-8 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12284/9591 Copyright (c) 2018 Luthfia Hajar Abdillah, Afni Restasari, Kendra Hartaya, Ratna Rizky Puspitasari https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12285 2025-10-03T07:30:27Z ijoa:ART

PICO-SATELLITE DETUMBLING SIMULATION USING MAGNETIC ATITUDE ACTUATOR (SIMULASI DETUMBLING PADA SATELIT PIKO MENGGUNAKAN AKTUATOR SIKAP MAGNETIK) Muksin, Ali Poetro, Ridanto Eko Triharjanto, Robertus Heru Kendali sikap cubesat Aktuator magnetik Kendali b-dot Simulator satelit Salah satu cara untuk mengendalikan sikap satelit nano/piko adalah dengan menggunakan magneto-torquer sebagai aktuator. Saat ini ITB tengah mewacanakan pengembangan cubesat, sehinggga tujuan dari penelitian ini adalah untuk mengevaluasi kinerja sistem kendali sikap berdasarkan medan magnet Bumi pada cubesat kelas 3U. Penelitian ini menggunakan simulator satelit berbasis MATLAB/simulink yang dikembangkan oleh LAPAN dan ITB, moda kendalinya berbasis hukum kendali b-dot. Keuntungan dari sistem kendali ini adalah ukuran dan beratnya yang kecil, dibandingkan dengan moda kendali lain, seperti momentum wheel atau reaction wheel. Sementara kerugiannya adalah hanya bisa menghasilkan torsi saat aktuator mempunyai sudut tidak nol dengan medan magnet Bumi. Hasil menunjukkan bahwa moda kendali tersebut dapat melakukan manuver de-tumbling, dengan waktu transient terbaik mendekati dua periode orbit. Juga ditunjukkan bahwa variasi waktu transient dan ketidakstabilan dapat diperoleh dengan memvariasikan parameter gain pada kontroler.  BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12285 10.30536/j.jtd.2017.v15.a2524 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 11-20 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12285/9592 Copyright (c) 2025 Ali Muksin, Ridanto Eko Poetro, Robertus Heru Triharjanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12286 2025-10-03T07:30:27Z ijoa:ART

PERANCANGAN DAN ANALISIS INTEGRASI HYPERSONIC WAVERIDER–INLET SCRAMJET (DESIGN AND ANALYSIS OF HYPERSONIC WAVERIDER– SCRAMJET INLET INTEGRATION) Malik, Deden Ridwan Bura, Romie Oktovianus General wedge-derived waverider Scramjet inlet Exergy destruction rate Design and integration Nowadays, several hypersonic vehicle designs have existed and waverider is one of them. Waverider has been introduced for more than 50 years yet only a few have been operated. This is due to several difficulties in design processes dan propulsion system integration. The present research was conducted by designing general wedgederived waverider and integrating it with scramjet inlet. The waverider design process is based on one-dimensional flowfield analysis, while the scramjet inlet integration is based on exergy analysis. Through this investigation, a design variable – Exergy Destruction Rate (EDR) - would be obtained to correlate the waverider design with the integration of scramjet inlet BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12286 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 19-26 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12286/9593 Copyright (c) 2014 Deden Ridwan Malik, Romie Oktovianus Bura https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12287 2025-10-03T07:30:27Z ijoa:ART

ANALISIS KINERJA ENJIN ROKET CAIR ECX1000H2-3 Hakim, Arif Nur Tahdi, Hudoro Rochman, Taufiqur Enjin roket cair ECX1000H2-3 telah dikembangkan dengan mengadopsi  injektor konfigurasi baru untuk meningkatkan gaya dorong yang telah dicapai enjin sebelumnya.  Injektor baru mempunyai jumlah lubang fuel dan oksidator masing-masing sebanyak 54 dan 156 dengan diameter sebesar 1 mm. Bentuk elemen injektor telah dimodifikasi untuk meningkatkan debit propelan.  Uji static telah dilakukan untuk menguji kinerja sistem enjin secara keseluruhan.  Hasil pengujian mencatat gaya dorong dan tekanan rata-rata sebesar 730 kgf dan 22,6 bar atau meningkat 19,7% dari hasil enjin sebelumnya, namun masih 84 % lebih rendah dari prediksi berdasarkan hasil uji injector dikarenakan kinerja sistem pengumpan yang tidak optimal.  Selain itu,  terjadi ledakan kecil saat penyalaan karena akumulasi propelan yang tidak terbakar akibat terbatasnya area kontak api penyalaan dengan propelan.   BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12287 10.30536/j.jtd.2018.v16.a2973 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 9-22 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12287/9821 Copyright (c) 2018 Arif Nur Hakim, Hudoro Tahdi, Taufiqur Rochman https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12288 2025-10-03T07:30:27Z ijoa:ART

SISTEM PENGAMAN POWER SHAPE-CHARGE PADA FLIGHT TERMINATION SYSTEM (POWER SHAPE CHARGE SECURITY SYSTEM ON FLIGHT TERMINATION SYSTEM) Arisandi, Effendi Dodi smart system FTS module rela shape-charge power Baterai adalah sumber energi listrik yang dapat digunakan secara berulang-ulang.  Dengan demikian, baterai dapat digunakan sebagai sumber energi listrik untuk berbagai macam peralatan elektronika. Modul Flight Termination System (FTS ) juga menggunakan baterai sebagai sumber energi listrik. Modul FTS yang telah terintegrasi dalam sistem roket harus dikontrol secara ketat agar tidak terjadi kecelakaan yang dapat ditimbulkan oleh penyalaan power modul. Hal ini disebabkan, pada saat power modul FTS dinyalakan maka akan menimbulkan logika high pada mikrokontroller yang dapat memicu aktifnya komponen elektronika. Penelitian ini fokus pada sistem proteksi sumber daya baterai sebagai pemicu sistem shape-charge pada modul FTS. Smart system yang menjadi fokus pada penelitian ini terdiri dari komponen mikrokontroller, inverter, relay, resistor, dan thyristor. Dari hasil penelitian diperoleh bahwa penggunaan smart system dapat menghambat aktifnya relay yang diakibatkan oleh penyalaan power modul FTS. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12288 10.30536/j.jtd.2017.v15.a2484 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 21-28 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12288/9596 Copyright (c) 2025 Effendi Dodi Arisandi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12289 2025-10-03T07:30:27Z ijoa:ART

OPTIMASI SISTEM LINING MOTOR ROKET PADAT RX1220 MELALUI PERUBAHAN KOMPOSISI MATERIAL LINER DAN METODE LINING (OPTIMIZATION OF LINING SYSTEM FOR RX1220 SOLID ROCKET MOTOR THROUGH IMPROVEMENT OF LINER MATERIAL COMPOSITION AND LINING METHOD) Dewi, Wiwiek Utami Liner material Lining method Solid rocket motor RX1220 In 2013, as many as 21.42% of the RX1220 rocket motor production did not pass the radiographic testing due to air bubble presences within the liner layer (liner defects). In 2014, there are dimensional changes in the inside diameter of the rocket motor tube (107.5 mm to 107.1 mm). Lining process by using gravity casting method becomes more difficult to apply. Liner viscosity is considerably high for the lining method. The efforts to lower its viscosity had been done yet the result did not reach the expectation. The changes in liner composition and lining method were conducted to optimize the RX1220 lining process. The result was good. After the new compositionand improved method applied, no more liner defects in RX1220. All of RX1220 rocket motors were labeled QC pass from the radiographic testing. BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12289 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 27-35 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12289/9599 Copyright (c) 2014 Wiwiek Utami Dewi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12291 2025-10-03T07:30:27Z ijoa:ART

PEMROGRAMAN CAD UNTUK PEMODELAN BENTUK PERMUKAAN SAYAP BURUNG (CAD PROGRAMING FOR MODELING THE SHAPE OF BIRD WING SURFACES) Zain, Rais Atmadi, Sulistyo Pamungkas, Iqbal Suryono, Fajar Kemampuan terbang sayap burung sudah sejak lama dipelajari untuk pengembangan teknologi penerbangan dan masih terus dipelajari sampai saat ini. Jenis burung soaring seperti Albatros, secara alamiah sayapnya mempunyai bentuk yang sangat komplek. Sekalipun pada saat terbang melayang, bentuk sayapnya memiliki banyak parameter yang bervariasi secara halus dengan bentuk yang berkelok mulai dari pangkal sampai ke ujung sayapnya. Pada paper ini keindahan bentuk permukaan sayap burung dipelajari yang kemudian secara sistematik dikembangkan suatu teknik untuk merepresentasikan variasi parameter bentuk sayap seperti;bentuk potongan sayap, sudut swept, sudut dihedral, sudut twist, dan panjang chord. Pemrograman CAD diterapkan pada pembuatan model permukaan sayap dimana CATIA V5 dipilih karena kemampuannya yang andal dalam memodelkan bentuk permukaan dengan akurasi yang tinggi. Sejumlah fungsi dan obyek milik Catia diakses melalui sarana Component Object Models (COMs) dengan menggunakan Microsoft Visual Basic.Net. Studi ini menghasilkan suatu program komputer yang mampu merepresentasikan bentuk permukaan sayap burung secara otomatis dan dilengkapi dengan kemampuan pengaturan parameternya. Program komputer ini dapat dipakai sebagai alat bantu untuk desain sayap burung. Bahkan dapat digunakan sebagai referensi untuk keperluan analisa aerodinamika dan struktur sayap.Kata kunci: Permukaan Sayap Burung, Pemrograman CAD, Catia V5, Visual Basic BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12291 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 37-44 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12291/9602 Copyright (c) 2014 Rais Zain, Sulistyo Atmadi, Iqbal Pamungkas, Fajar Suryono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12292 2025-10-03T07:30:27Z ijoa:ART

Time Optimization for Lossy Decompression of the LISA Sensor Data on LAPAN A3 Satellite Using a Grouping Method of HUFFMAN Code Bit Number Suhermanto, Suhermanto Arief, Rahmat Time optimization lossy decompression Huffman code LISA LAPAN A3 The LAPAN-A3 satellite provides compressed multispectral data from LISA sensor using real-time lossy compression. The compression of the multispectral data of radiometric resolution 12bit/pixel is built from the Fourier transform and the use of Huffman decoder 514 binary length code. A problem arised in the data extraction process, that decompression performance is very slow because the search method of code value in Hufman table was done sequentially from one bit to the next bit in one block of data along 4000 pixels. The data extraction time for one scene in 12 minutes acquisition duration (one full path) takes up to 20 hours. This paper proposes a method of improving the LISA real-time lossy data decompression algorithm using the grouping method of bit code on the Huffman decoding algorithm and using pointer for reading data in the buffer memory. Using this method, the searching process of bit code for all characters in the Huffman decoder algorithm is done regularly, so the search processing time is significantly reduced. The performance test used 6 data samples. The result showed that extraction time has an average of 14 times faster. The lossy compression ratio is still in accordance with the design specification of LISA sensor that is less than 4 times and the appearance of the special character is very small i.e. less than 0.5%. BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12292 10.30536/j.jtd.2018.v16.a2960 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 23-34 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12292/9601 Copyright (c) 2018 Suhermanto, Rahmat Arief https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12293 2025-10-03T07:30:27Z ijoa:ART

ANALISIS CFD KARAKTERISTIK AERODINAMIKA PADA SAYAP PESAWAT LSU-05 DENGAN PENAMBAHAN VORTEX GENERATOR (ANALYSIS OF CFD AERODYNAMIC CHARACTERISTICS AT THE WING OF AIRCRAFT LSU-05 WITH THE ADDITION OF VORTEX GENERATOR) Romadhon, Awalu Herdiana, Dana vortex generator LSU-05 karakteristik aerodinamika CFD aerodynamic characteristics Pesawat LSU-05 adalah salah satu pesawat tanpa awak (UAV) yang sedang dikembangkan oleh Pusat Teknologi Penerbangan LAPAN, yang mempunyai misi untuk kegiatan penelitian, observasi, patroli, pengawasan perbatasan wilayah, dan investigasi bencana alam. Penelitian ini bertujuan untuk mengetahui pengaruh penambahan vortex generator terhadap karakteristik aerodinamika dari sayap Pesawat Tanpa Awak LSU-05. Metode yang digunakan adalah analisis numerik dengan simulasi CFD untuk memprediksi karakteristik aerodinamika dan fenomena aliran yang terjadi. Model yang digunakan adalah sayap pesawat LSU-05 tanpa vortex generator dan dengan vortex generator yang didesain dengan software CATIA. Simulasi menggunakan software ANSYS Fluent untuk mengetahui perubahan karakteristik aerodinamika sayap setelah penambahan vortex generator seperti koefisien lift dan koefisien drag. Hasil yang diperoleh dari penelitian penambahan vortex generator pada sayap Pesawat LSU-05 adalah peningkatan nilai koefisien lift maksimum sayap dari 1,26450 menjadi 1,34840 atau naik sebesar 0,0839 (6,63%), peningkatan nilai koefisien drag pada sudut serang -9â° s/d 11â°, penurunan nilai koefisien drag pada sudut serang 12â° s.d 15â° dan peningkatan sudut stall sayap dari 11â° menjadi 14â° atau naik sebesar 3â° (27,7 %). BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12293 10.30536/j.jtd.2017.v15.a2518 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 45-58 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12293/9603 Copyright (c) 2025 Awalu Romadhon, Dana Herdiana https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12294 2025-10-03T07:30:27Z ijoa:ART

ANALISIS PENGGUNAAN DATA KAMERA VIDEO UNTUK MENINGKATKAN KUALITAS KOREKSI GEOMETRI PADA CITRA IMAGER PUSHBROOM (ANALYSIS OF VIDEO CAMERA DATA USAGE TO IMPROVE GEOMETRY CORRECTION QUALITY ON PUSHBROOM IMAGER IMAGE) Hakim, Patria Rachman Syafrudin, A. Hadi Hasbi, Wahyudi Rahman, Abdul Citra yang dihasilkan imager pushbroom pada umumnya memiliki distorsi geometri yang cukup signifikan yang diakibatkan oleh ketidakstabilan attitude satelit pembawanya. Untuk dapat menghasilkan citra terkoreksi yang baik untuk berbagai kondisi pengamatan maka dibutuhkan data attitude satelit dengan frekuensi yang cukup tinggi. Penelitian ini menganalisis penggunaan kamera video untuk menghasilkan data attitude dengan frekuensi tinggi yang akan digunakan dalam koreksi geometri sistematik. Pada dasarnya, data attitude satelit dapat dihasilkan dari data video dengan menggunakan konsep geometri epipolar. Beberapa perangkat lunak pelacak video telah tersedia untuk mengekstrak data attitude dari data video, dimana frekuensi data attitude yang dihasilkan akan sama dengan frame rate kamera video yang digunakan, yang umumnya bernilai 20-30 Hz. Data attitude ini kemudian diintegrasikan dengan data attitude yang berasal dari star sensor dan selanjutnya digunakan dalam algoritma koreksi geometri sistematik citra. Hasil simulasi menunjukkan bahwa pada pergerakan yang tidak stabil, data attitude video dapat meningkatkan kualitas citra terkoreksi secara signifikan; sedangkan untuk pergerakan stabil sebaiknya hanya menggunakan data attitude dari star sensor. Selain itu, untuk dapat menghasilkan data estimasi attitude yang baik maka disarankan menggunakan kamera video dengan resolusi tinggi dan lebar field of view (FoV) yang luas.Kata kunci: Koreksi geometri sistematik, Imager pushbroom, Kamera video, Epipolar. BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12294 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 45-58 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12294/9604 Copyright (c) 2014 Patria Rachman Hakim, A. Hadi Syafrudin, Wahyudi Hasbi, Abdul Rahman https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12295 2025-10-03T07:30:27Z ijoa:ART

PENGGUNAAN BINDER HTPB BERENERGI TINGGI UNTUK MENINGKATKAN ENERGETIK PROPELAN KOMPOSIT Abdillah, Luthfia Hajar Wibowo, Heri Budi Hartaya , Kendra HTPB nitro-HTPB binder energetik propelan Untuk mendapatkan performa propelan yang lebih energetik, penelitian terbaru menunjukkan bahwa diperlukan penggunaan material-material yang bersifat lebih energetik, misalnya penggunaan binder energetik. Pengawasan yang ketat atas peredaran material energetik seperti ini cukup menyulitkan untuk mendapatkan material-material tersebut. Oleh karena itu kemandirian untuk memiliki material tersebut sudah seharusnya menjadi perhatian. Binder propelan  komposit yang paling banyak digunakan saat ini adalah HTPB yang bersifat non-energetik. Untuk membuatnya lebih berenergi tinggi dapat dilakukan dengan menambahkan gugus yang bersifat energetik seperti gugus nitro, namun tetap aman digunakan (bersifat stabil). Tulisan ini mengkaji  potensi konversi binder HTPB menjadi nitro-HTPB yang bersifat energetik, meliputi material, peralatan, dan metode yang dapat diaplikasikan di Indonesia. Prosesnya adalah nitrasi HTPB menjadi nitro-HTPB.  Berdasarkan kajian energetiknya, nitro-HTPB memiliki potensi untuk meningkatkan sifat energetik propelan padat komposit. Metode proses pembuatan nitro-HTPB yang paling efektif dan optimal adalah proses nitrasi dengan menggunakan bahan sodium nitrit pada suhu rendah (0oC). BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12295 10.30536/j.jtd.2018.v16.a2974 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 35-44 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12295/9607 Copyright (c) 2018 Luthfia Hajar Abdillah, Heri Budi Wibowo, Kendra Hartaya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12296 2025-10-03T07:30:28Z ijoa:ART

DESAIN DAN IMPLEMENTASI GROUND MODEL SATELIT NANO DENGAN SUBSISTEM KOMUNIKASI PADA FREKUENSI S-BAND (DESIGN AND IMPLEMENTATION OF GROUND MODEL NANO-SATELLITE WITH S-BAND FREQUENCY COMMUNICATION SUBSYSTEM) Khaznasari, Fitrenna Suryana , Joko Ground model nano satelit frekuensi 2,4 GHz antena Seeeduino XBee baterai solar panel ukuran massa daya link budget Makalah ini berisi desain dari ground model nano-satelit pengamat Bumi yang subsistem komunikasinya bekerja pada frekuensi S-Band. Ground model yang dibuat mengacu pada satelit GOLIAT yang memiliki ukuran sebesar 10 x 10 x 10 cm, berat satu kilogram, payload yang dibawa berupa kamera, dan daya yang dipancarkan sebesar 1 watt. Ground model satelit nano yang dibuat memiliki antena untuk transmisi berupa antena mikrostrip dengan ukuran 9,5 x 9,5 cm, frekuensi kerja 2,4 GHz, nilai parameter S11 sebesar -18,506 dB, VSWR sebesar 1,2695, dan gain sebesar 6,42 dB. Ground model yang dibuat menggunakan Seeeduino sebagai on-board computer, modul XBee untuk berkomunikasi, kamera VC0706, baterai lithium ion, solar panel, dan berbagai macam sensor. Perhitungan link budget pada jarak 300 km untuk ground model satelit nano yang dibuat yaitu Effective Isotropic Radiated Power (EIRP) yang dimilikinya sebesar 36,42 dBm, daya terima -101,18 dBm, receive power dan noise ratio (  sebesar 107 dBHz, dan energy bit dan noise ratio sebesar 55,02 dB, sementara untuk satelit GOLIAT memiliki EIRP sebesar 32,2 dBm, daya terimanya sebesar -82 dBm, receive power dan noise ratio sebesar 126,18 dBHz, dan energy bit dan noise ratio sebesar 86,357 dB. Sehingga dapat disimpulkan bahwa desain dan implementasi ground model satelit nano dengan subsistem komunikasi S-band berhasil dilakukan, bahkan kinerjanya lebih baik dari satelit pembanding. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12296 10.30536/j.jtd.2017.v15.a2372 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 59-70 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12296/9605 Copyright (c) 2025 Fitrenna Khaznasari, Joko Suryana https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12297 2025-10-03T07:30:28Z ijoa:ART

ANALISIS POTENSI GANGGUAN INTERFERENSI MICROWAVE LINK TERHADAP OPERASI SATELIT LAPAN-A3 DI STASIUN BUMI RUMPIN (THE ANALYSIS OF POTENTIAL MICROWAVE LINK INTERFERENCE AGAINST LAPAN-A3 SATELLITE OPERATION AT RUMPIN GROUND STATION) Judianto, Chusnul Tri Wurianto, Endar Operasi Satelit Gangguan Frekuensi Lapan-A3 Penyiapan sistem stasiun bumi untuk mendukung operasi satelit Lapan-A3 yang merupakan satelit eksperimen ke tiga yang sedang dikembangkan Lapan adalah hal penting yang sedang dilakukan saat ini. Satelit Lapan-A3 merupakan satelit imager 4 kanal eksperimen pertama yang dikembangkan Lapan. Proses Assembly Integration and Test (AIT) Satelit Lapan-A3 direncanakan selesai pada awal tahun 2015 dan diluncurkan pada akhir tahun 2015. Peluncuran ini sangat mungkin dilakukan karena kesempatan peluncuran untuk satelit pada orbit polar sangat terbuka baik melalui India sesuai dengan kerjasama pemanfaatan antariksa yang telah dibangun saat ini. Lapan-A3 akan menggunakan frekuensi 8200 dan lebar BW 168 MHz. Pita frekuensi ini akan sangat berpotensi terganggu dengan adanya komunikasi microwave antar Base Transceiver Station (BTS) dan Base Station Controller (BSC) yang pada saat ini rentang frekuensinya digunakan secara bersama untuk aplikasi satelit dan terestrial sesuai peraturan Negara. Stasiun Bumi Rumpin merupakan salah satu stasiun bumi satelit Lapan yang dipersiapkan untuk kendali dan akuisisi data satelit Lapan-3 dan berada di daerah perkotaan antara Kabupaten Tangerang dan Bogor Oleh karena itu perlu antisipasi terhadap kondisi gangguan frekuensi tersebut. Beberapa pendekatan yang dapat dilakukan dalam mempersiapkan operasi satelit Lapan-A3 akan dijelaskan dalam makalah ini. BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12297 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 59-72 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12297/9606 Copyright (c) 2014 Chusnul Tri Judianto, Endar Wurianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12298 2025-10-03T07:30:28Z ijoa:ART

PREDIKSI KEKUATAN STRUKTUR ALAT UJI GETARAN ENGINE LSU SERIES MENGGUNAKAN METODE ELEMEN HINGGA (STRENGTH PREDICTION OF THE ENGINE VIBRATION TEST STAND OF LSU SERIES USING FINITE ELEMENT METHOD) Wandono, Fajar Ari Syah, Agus Harno Nurdin karakteristik getaran alat uji getaran engine material ASTM A36 engine DA-170 metode elemen hingga faktor keamanan frekuensi pribadi vibration characteristics engine vibration test stand ASTM A36 material DA-170 engine finite element method Untuk mengetahui karakteristik getaran dari kombinasi engine dan propeller yang digunakan pada LAPAN Surveillance UAV (LSU) series maka diperlukan sebuah alat uji yang disebut alat uji getaran engine (AUGE). Struktur AUGE harus dibuat kuat dan kaku untuk mendapatkan hasil uji getaran engine yang baik. Sebagai langkah awal telah dibuat sebuah AUGE yang terbuat dari material ASTM A36 yang berbentuk H setinggi 1 meter dengan bagian bawahnya dibaut ke sebuah lantai yang sudah diperkuat. Dengan menggunakan software metode elemen hingga dan memasukkan parameter engine DA-170 serta sifat mekanik ASTM A36 didapatkan bahwa struktur AUGE tersebut memiliki nilai faktor keamanan sebesar 26,24. Adapun lima nilai pertama frekuensi pribadi dari struktur tersebut adalah 61,94 Hz, 77,18 Hz, 93,79 Hz, 212,23 Hz dan 286,24 Hz. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12298 10.30536/j.jtd.2017.v15.a2505 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 71-80 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12298/9609 Copyright (c) 2025 Fajar Ari Wandono, Agus Harno Nurdin Syah https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12299 2025-10-03T07:30:28Z ijoa:ART

RANCANG BANGUN SISTEM ADJUSTABLE ELECTRONIC FUSE UNTUK PLATFORM MICROSATELLITE (ADJUSTABLE ELECTRONIC FUSE SYSTEM DESIGN FOR MICROSATELLITE PLATFORM) Karim, Abdul Hasbi , Wahyudi Satelite Pembatas Arus Pembangkit Subsistem power satelit terdiri dari tiga komponen dasar: pembangkit daya (power generator), penyimpan daya (power storage), dan kontrol daya (power control). Pembatas arus (fuse) adalah bagian dari kontrol daya yang berfungsi untuk mengamankan perangkat-perangkat elektronik satelit dari kerusakan akibat beban lebih (over load) atau kesalahan fungsi dari sistem luar (external) perangkat tersebut. Tulisan ini menganalisa rancangan Pembatas Arus Elektronik (elektronic fuse) untuk digunakan di dalam sistem mikrosatelit berbasis komponen yang siap di pasaran (Commercial off the Shelf) dan dirancang memiliki keluwesan (flexibillity) yang tinggi. Sistem ini diuji dengan menggunakan resistor variabel sebagai beban perangkat satelit sehingga konsumsi power dapat dibaca dan dianalisis melalui catu daya (power supply). Rekayasa ini menggunakan studi kasus Lapan-A2 untuk mengambil dua buah kasus sebagai referensi perangkat elektronik yang digunakan. Hasil rancangan menunjukkan bahwa rangkaian pembatas arus dapat membatasi arus masing-masing perangkat sebesar 0,834 dan 1.833 Ampere dengan nilai total Mean Time Between Failures (MTBF) 3444475,062 Jam. BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12299 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 73-81 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12299/9608 Copyright (c) 2014 Abdul Karim, Wahyudi Hasbi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12300 2025-10-03T07:30:28Z ijoa:ART

METODE PENGGABUNGAN BEBERAPA PENERIMA GPS UNTUK MENINGKATKAN AKURASI DAN KEANDALAN SISTEM PENJEJAK ROKET BALISTIK (METHOD OF COMBINING MULTI-GPS RECEIVERS TO IMPROVE ACCURACY AND RELIABILITY OF THE TRACKING SYSTEM OF SOUNDING ROCKET) Widada, Wahyu GPS konsumen Multipel GPS Tracking roket Mikrokontroller Kualitas GPS teknologi tingkat konsumen tidak cukup akurat untuk sistem penjejakan roket balistik. Untuk mengatasi masalah tersebut, tulisan ini membahas metode kombinasi multi receiver Global Positioning System (GPS) untuk meningkatkan akurasi dan keandalan pada sistem tracking roket balistik. Data dari masing-masing receiver GPS akan dipilih yang valid dan digabung dengan mikrokontroller. Data yang telah dikumpulkan dihitung nilai rata-ratanya kemudian dikirim menggunakan radio telemetri ke stasiun peluncuran. Hasil percobaan dengan prototipe menunjukkan terjadi penurunan Root Mean Square Error (RMSE) untuk latitude sekitar 30% dan longitude sekitar 30%, sedangkan untuk altitude sekitar 40%. Penempatan antena GPS pada posisi empat arah yang berbeda meningkatkan reliabilitas dan performa receiver. BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12300 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 1-10 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12300/9610 Copyright (c) 2014 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12301 2025-10-03T07:30:28Z ijoa:ART

KENDALI SAKELAR EMPAT ANTENNA BERSUSUN UNTUK PENJEJAKAN INTERFERENCE FREKUENSI TTC SATELIT LAPAN (SWITCH CONTROL SYSTEM FOR FOUR ARRAY ANTENNA FOR TRACKING OF LAPAN’S SATELLITE TTC INTERFERENCE FREQUENCY) Hidayat, Arif Palante, Elyas Syarif, Syafruddin satelit TTC interference kontrol antenna arduino board array antenna satellite TTC control antenna arduino board, arrray antenna Telemetry Tracking And Command (TTC) satelit LAPAN menggunakan frekuensi UHF. Frekuensi UHF rentan terhadap interference. Salah satu metode mencari pemancar interference menggunakan metode efek Doppler. Untuk mendapat nilai pergeseran frekuensi sesuai efek Doppler yang dibutuhkan, diperlukan sakelar antena yang stabil, yang berfungsi sebagai pengontrol antena array. Rangkaian sakelar RF di kontrol dengan Arduino board menghasilkan Doppler frekuensi 500 Hz. Demodulator, clock Arduino Board dan Soundcard sebagai input software pencari.  Hasil outputnya dapat dilihat dengan menggunakan software open akses sounDoppler. Sistem ini mampu mendeteksi pemancar maupun repeater yang diterima oleh perangkat. Upgrade sistem dari penelitian ini adalah proses pengolahan data dapat dilakukan secara mandiri menggunakan software Matlab sehingga lebih mudah untuk diolah dan dianalisis. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12301 10.30536/j.jtd.2017.v15.a2631 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 81-92 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12301/9613 Copyright (c) 2025 Arif Hidayat, Elyas Palante, Syafruddin Syarif https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12302 2025-10-03T07:30:28Z ijoa:ART

RX-320 Rocket Static Pressure Combustion Chamber Prediction and Validation by Using Invers Method Sofyan, Sofyan Wuwung, Vicky static pressure combustion chamber invers method static test CFD Numeca Nozzle efficiency RX-320 The static pressure data of the combustion chamber which can generally be obtained by performing direct measurements when static test is performed on the rocket is an important parameter in predicting the thrust and design of the combustion chamber of the rocket. However, there is a model rocket for flight test that is used in static test. Thus, there is no mounting for static pressure sensors (for measurement) are made. To solve the problem, then the inverse method is used as an iterative solution for the basic equations of the rocket thrust force in the nozzle by guessing the value of the static pressure of the combustion chamber firstly and calculate the iteration by including the value of the rocket thrust from static test data and the efficiency variation of the nozzle. The results of this calculation are then validated by using a 3D-CFD numerical simulation to obtain a more detailed comparison on the nozzle. In this research RX 320 LAPAN rocket nozzle with focus on maximum static thrust data of static test results is used. The 3-D numerical simulation is performed using Numeca CFD software, with k-extended wall extended turbulent model, numerical multigrid level 3 scheme, center based, and convergence criteria of 10 e-05. The result of calculation by inverse method and its comparison with numerical simulation shows that the smallest difference of the combustion chamber static pressure between inverse method and numerical simulation is 0.017%, that is achieved at 92% nozzle efficiency. At this point, the static pressure of the combustion chamber is 57.94 bar. From this point of view, the results of this comparison indicate that the inverse method can be used accurately for static pressure of the combustion chamber prediction, if the nozzle efficiency is given correctly. Furthermore, with given static pressure of the combustion chamber correctly, it will be very helpful in the design of the more optimum combustion chamber.   BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12302 10.30536/j.jtd.2018.v16.a2866 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 45-58 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12302/9611 Copyright (c) 2018 Sofyan, Vicky Wuwung https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12303 2025-10-03T07:30:28Z ijoa:ART

PENINJAUAN HOMOGENITAS PROPELAN SKALA K-ROUND BERDASARKAN VARIANS NILAI KALOR (HOMOGENEITY OBSERVATION OF PROPELLANT K-ROUND SCALE BASED ON CALORIFIC VALUE VARIANCE) Abdillah, Luthfia Hajar Ardianingsih, Retno Propelan K-round Homogenitas Nilai kalor Uji F dan uji Bartlett Varians Impuls spesifik (Isp) propelan skala K-round yang dihasilkan Lapan masih tergolong rendah yaitu di bawah 220 detik. Selain itu dari dua propelan dengan komposisi sama sering diperoleh nilai Isp yang berbeda. Terjadinya perbedaan nilai Isp ini diperkirakan bahwa kedua propelan tersebut tidak homogen yang dapat menyebabkan kesalahan ukur dalam pengujian mekanik, balistik maupun pengujian statik sehingga data yang dihasilkan menjadi tidak valid. Oleh karena itu homogenitas propelan penting untuk diketahui. Homogenitas propelan diuji dengan cara perhitungan statistik melalui keseragaman varians data nilai kalor menggunakan metode uji F dan uji Bartlett. Berdasarkan hasil pengujian diperoleh bahwa nilai kalor sangat beragam dari 2015 kal/gram hingga 5829 kal/gram. Varians nilai kalor pada satu batang propelan dinyatakan tidak seragam yang berarti produk propelan skala K-Round yang dihasilkan tidak homogen. Adapun varians nilai kalor propelan pada batch yang sama dan pada batch yang berbeda dinyatakan seragam. Hal ini menunjukkan derajat perbedaan nilai kalor pada kedua macam batch tersebut konsisten yang berarti ketidak merataan distribusi bahan pada setiap batch produksi propelan K-Round juga konsisten. BRIN Publishing 2014-11-18 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12303 Indonesian Journal of Aerospace; Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara; 11-18 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12303/9612 Copyright (c) 2014 Luthfia Hajar Abdillah, Retno Ardianingsih https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12304 2025-10-03T07:30:28Z ijoa:ART

JUSTIFIKASI CFD KEDALAMAN GROOVE BAN PADA PROSES PERAWATAN HARIAN PESAWAT B737-800 AKIBAT HYDROPLANING (B737-800 TIRE GROOVE DEPTH CFD JUSTIFICATION ON ITS DAILY MAINTENANCE PROCESS DUE TO HYDROPLANING) Wuwung, Vicky Anggreyni, Nelli Hitoyo, Valeri Maria Bintoro, Carolus B 737-800 kedalaman groove hydroplaning CFD Numeca Fine/Marine maintenance harian tyre groove depth flood runway landing daily maintenance Groove atau ‘kembang†pada ban pesawat merupakan sarana untuk mengalirkan air dari bagian depan menuju bagian belakang melalui bagian bawah ban, tanpa mengangkat ban sehingga dapat mencegah terjadinya hydroplaning. Sehingga, pengaruh nilai kedalaman groove terhadap gaya angkat pada ban pesawat B737-800 yang bergerak di landasan dengan genangan air perlu dijustifikasi dalam proses perawatan harian. Penelitian ini menyimulasikan proses mengalirnya air pada bagian bawah ban dengan menggunakan simulasi numerik (CFD Numeca Fine/Marine) 3-D unsteady sebagai metode untuk menjustifikasi pengaruh groove. Simulasi dilakukan untuk kondisi gerakan ban pesawat pada saat proses landing (V = 62,275 m/s) beberapa saat setelah touch down (setelah skidding) dengan ban pesawat dianggap rigid body sebagai kondisi batas. Selanjutnya tinggi genangan air dipilih pada saat runway dinyatakan dalam kondisi flood (tinggi genangan air = 2,54mm). Simulasi tersebut menampilkan hasil perhitungan ban pesawat Boeing 737-800, dengan hydroplaning mulai terjadi ketika kedalaman groove ban berada dibawah 0,4 inch. Hal ini menunjukkan bahwa semakin kecil kedalaman groove, maka semakin kecil luas penampang groove dan semakin besar gaya kompresi yang terjadi pada bagian bawah ban dan semakin memperbesar kemungkinan terjadinya fenomena hydroplaning. Dengan diketahuinya hasil dari simulasi tersebut, maka hasil penelitian ini dapat digunakan sebagai masukan bagi proses maintenance harian pesawat B737-800 dan mampu memberikan suatu hal baru dalam pembelajaran khususnya mengenai fenomena hydroplaning. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12304 10.30536/j.jtd.2017.v15.a2528 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara; 29-44 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12304/9619 Copyright (c) 2025 Vicky Wuwung, Nelli Anggreyni, Valeri Maria Hitoyo, Carolus Bintoro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12305 2025-10-03T07:30:28Z ijoa:ART

OPTIMALISASI AKURASI ANTENA PENJEJAK SATELIT ORBIT RENDAH MENGGUNAKAN MOTOR STEPPER HYBRID 2 FASA (OPTIMIZATION OF LOW EARTH ORBIT TRACKING ANTENNA USING STEPPER MOTOR HYBRID 2-PHASE) Herawan, Agus Judianto, Chusnul Tri Motor stepper hybrid Orbit rendah Antena penjejak satelit Untuk mendukung kinerja pemanfaatan satelit Lapan di orbit maka dibutuhkan sistem antena penerima yang handal di stasiun bumi. Kinerja sistem penerima data satelit orbit rendah ini sangat ditentukan oleh akurasi motornya disamping sistem RF Front (LNA, Feed, Cable dan Receiver) yang digunakan dalam menjejak satelit yang bergerak sangat cepat pada orbit rendah. Kecepatan pergerakan satelit pada orbit rendah pada ketinggian sekitar 630 km adalah 7.5 km/detik. Dengan kondisi tersebut sistem antena membutuhkan motor penggerak antena dengan akurasi yang tinggi agar penjejakan terhadap pergerakan satelit akan tetap terjaga dan antena selalu dalam posisi line of sight tanpa terjadi kehilangan sinyal. Agar diperoleh sistem antena yang handal dengan akurasi pergerakan motornya yang lebih baik, maka digunakan rancangan motor stepper Hybrid 2 phase. Motor stepper standar ini memiliki akurasi 1,8/step, dengan menambah rancangan gear dengan perbandingan 100:1 sehinga diperoleh akurasi motor 0.018/step. Detail Rancangan dan implementasi sistem motor stepper ini akan dibahas dalam tulisan ini. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12305 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 1-11 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12305/9615 Copyright (c) 2013 Agus Herawan, Chusnul Tri Judianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12306 2025-10-03T07:30:28Z ijoa:ART

PENGEMBANGAN TEKNIK ANALISIS BERAT MOLEKUL HTPB UNTUK ACUAN DALAM KONTROL KUALITAS Wibowo, Heri Budi Dharmawan, Widhi Cahya HTPB kontrol kualitas viskosimetri osmometri GPC berat molekul polimer Telah dilakukan pengembangan teknik analisis berat molekul rata-rata polimer HTPB (Hydroxy Terminated Polybutadiene) dalam rangka pemilihan metode analisis untuk kontrol kualitas bahan baku propelan. Bahan HTPB diuji menggunakan metode viskosimetri, osmometri, dan kromatografi filtrasi gel (GPC) menggunakan bahan polimer standar polistiren dengan berat molekul 400, 1000, 5000, dan 10.000 gram.mol-1. Bahan yang dianalisis adalah HTPB impor dari China.  Hasil penelitian menunjukkan bahwa berat molekul rata-rata HTPB dapat dianalisis dengan baik mengunakan metode viskosimetri, osmometri, dan GPC disesuaikan dengan kondisi operasional. Analisis viskosimetri sangat cepat, mobilitas tinggi, akurasi rendah, dan dapat diperoleh berat molekul rata-rata viskos (Mv), dapat digunakan untuk kontrol kualitas bahan di lapangan. Analisis dengan metode osmometri dapat diperoleh berat molekul rata-rata jumlah (Mn) dengan akurasi tinggi dan mobilitas rendah dan dapat digunakan untuk kontrol kualitas. Analisis dengan metode GPC menghasilkan berat molekul rata-rata jumlah (Mn) dan polidispersitas HTPB, akurasi tinggi, mobilitas rendah, dan dapat digunakan untuk kontrol kualitas dan pengembangan polimer. Tidak terdapat perbedaan signifikan antara berat molekul mutlak dan relatif. Analisis HTPB menunjukkan terjadi penurunan kualitas HTPB dengan terjadinya kenaikan berat molekul setiap waktu. Kualitas HTPB efektif adalah 3 tahun. HTPB perlu dilakukan kontrol kualitas tiap bulan untuk memastikan tidak terjadi kerusakan signifikan atau untuk menyesuaikan formulasi propelan.   BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12306 10.30536/j.jtd.2018.v16.a2871 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 59-70 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12306/9614 Copyright (c) 2018 Heri Budi Wibowo, Widhi Cahya Dharmawan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12307 2025-10-03T07:30:28Z ijoa:ART

ANALISA SENSITIVITAS PADA DESAIN AWAL SATELIT MIKRO PENGAMAT BUMI (SENSITIVITY ANALYSIS ON PRELIMINARY DESIGN OF EARTH OBSERVATION MICRO-SATELLITE) Triharjanto, Robertus Heru Poetro, Ridanto Eko Muhammad, Hari Desain Satelit mikro Satelit pengamat bumi Analisa sensitivitas Makalah ini membahas analisa sensitivitas pada proses desain satelit mikro pengamat Bumi. Tujuan dari analisa ini adalah untuk melihat parameter input desain yang paling mempengaruhi kinerja satelit. Jenis satelit yang menjadi batasan dalam riset ini adalah satelit kelas hingga 100 kg dengan batasan dimensi untuk peluncuran sebagai muatan tambahan (auxilary payload). Misi pengamatan Bumi yang dimaksud juga dibatasi pada misi yang menggunakan sensor optik (multispectral imager), dimana kinerja utamanya adalah resolusi dan jumlah spektrum. Proses desain yang dimaksudkan dalam riset ini dibatasi hingga desain awal (preliminary design) dengan beberapa asumsi yang didasari oleh data empiris. Hasil analisa menunjukkan bahwa resolusi sangat berpengaruh pada jumlah data yang harus diproses terutama untuk resolusi tinggi, sehingga berefek pada jumlah daya listrik yang dikonsumsi. Resolusi, yang merupakan fungsi ukuran lensa juga berpengaruh pada berat satelit yang harus mengakomodasi dimensinya. Pada sisi lain, akomodasi lensa berakibat pada bertambahnya jumlah daya listrik yang bisa dihasilkan oleh subsistem daya satelit. Sementara jumlah spektrum juga berpengaruh terhadap parameter batasan satelit, yakni berat dan konsumsi daya, namun lebih moderat. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12307 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 13-21 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12307/9617 Copyright (c) 2013 Robertus Heru Triharjanto, Ridanto Eko Poetro, Hari Muhammad https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12308 2025-10-03T07:30:28Z ijoa:ART

EVALUASI KINERJA INSULINER BERBASIS EPOKSI MELALUI UJI STATIK MOTOR ROKET CASE BONDED (PERFORMANCE EVALUATION OF EPOXY BASED INSULINER OF CASE BONDED ROCKET MOTOR THROUGH STATIC TEST) Sutrisno Rohman, Fathur AH, Ronny Irianto Dewi, Wiwiek Utami Insuliner Motor roket Case bonded Free standing Radial burning Kegiatan penelitian yang telah dilakukan sebelumnya telah diperoleh material insuliner berbasis epoksi dan metode aplikasinya pada motor roket case bonded. Hasil penelitian ini juga telah diperoleh bahwa insuliner tersebut dapat direkomendasikan untuk digunakan pada motor roket case bonded yang menggunakan propelan radial burning sehingga perlu dibuktikan. Guna menguji kinerja insuliner tersebut telah dibuat dua unit motor roket case bonded mengggunakan insuliner berbasis epoksi dan satu unit motor roket free standing yang menggunakan insulasi termal berbasis epoksi dan lapisan fiber glass cloth untuk diuji statik. Tiga unit motor roket telah diuji statik. Berdasarkan pengujian diperoleh bahwa insuliner berbasis epoksi yang dibuat dapat berfungsi dengan baik. Kegagalan motor roket case bonded yang kedua tidak disebabkan oleh gagalnya insuliner tetapi oleh proses perakitan motor roket yang kurang sempurna. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12308 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 23-33 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12308/9618 Copyright (c) 2013 Sutrisno, Fathur Rohman, Ronny Irianto AH, Wiwiek Utami Dewi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12309 2025-10-03T07:30:28Z ijoa:ART

METODE SEGMENTASI AUTOMATIS UNTUK EKSTRAKSI HUTAN MANGROVE MENGGUNAKAN DATA SATELIT AVNIR-2 STUDI KASUS: PULAU LANCANG (AUTOMATIC OF SEGMENTATION METHOD FOR EXTRACTION MANGROVE FOREST BY USING AVNIR-2 SATELLITE DATA CASE STUDY: LANCANG ISLAND) Arief, Muchlisin Prayogo, Teguh Hamzah , Rossy ALOS AVNIR-2 Mangrove Region Segmentasi citra Thresholding Pulau Lancang Proses segmentasi citra adalah sebuah proses pengolahan citra untuk memisahkan obyek dari background-nya, sehingga obyek tersebut dapat diproses untuk keperluan lainnya atau dianalisa untuk proses lebih lanjut. Banyak metode yang dapat digunakan untuk proses segmentasi, seperti menggunakan threshold, gradient ataupun laplacian. Secara umum proses segmentasi dibagi dalam tiga bagian: klasifikasi, berdasar tepi, dan berdasar daerah/region growing. Pada paper ini dijelaskan algorithma segmentasi yang dibagi dalam tiga tahapan yaitu: Melakukan operasi pengurangan antar band data AVNIR-2, menentukan region growing dan melakukan pengklasan kerapatan mangrove. Region growing ditentukan berdasarkan nilai hasil pengurangan antara band B13 (band1-band3) dan B24 (band2-band4) serta pasangan antara B12 (band1-band2) dan B34 (band3-band4). Kemudian nilai tersebut digunakan sebagai nilai ambang/threshold dalam menentukan klas kerapatan hutan mangrove. Berdasarkan hasil perhitungan luas hutan mangrove di Pulau Lancang adalah 17.24 ha. Hasil tersebut dibandingkan dengan data yang diperoleh dari BAPEDALDA pada tahun 2000, Hasil perbandingannya menunjukkan bahwa metode yang telah dibangun mempunyai akurasi/ketelitian 95.5%. yang dapat diartikan bahwa pemerinah DKI Jakarta bersama masyarakat telah berhasil melestarikan hutan mangrove dan hutannya bertambah ±0.7 ha dalam kurun waktu 9 tahun. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12309 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 35-48 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12309/9620 Copyright (c) 2013 Muchlisin Arief, Teguh Prayogo, Rossy Hamzah https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12310 2025-10-03T07:30:28Z ijoa:ART

Sun Sensor dan Magnetometer Sebagai Sensor Penentu Sikap Satelit Inklinasi Rendah LAPAN-A2 Utama, Satriya Hakim, Patria Rachman LAPAN-A2 penentuan sikap sun sensor magnetometer LAPAN-A2 merupakan satelit low earth orbit (LEO), inklinasi rendah yang salah satu misinya adalah pengamatan citra bumi. Dalam melaksanakan misi pengambilan citra ataupun penurunan data, sikap satelit perlu diketahui operator di ruas bumi. Sebagai sensor utama untuk mengetahui sikap satelit digunakan star sensor. Namun ketika berada di wilayah terang, star sensor dapat dengan mudah terganggu oleh cahaya matahari atau bumi. Tulisan ini memperkenalkan penentuan sikap alternatif menggunakan sun sensor dan magnetometer. Idenya, sun sensor dan magnetometer mengukur vektor matahari dan vektor medan magnet pada sumbu satelit. Lalu, dengan menggunakan model posisi matahari dan propagator orbit SGP4, vektor matahari dan vektor medan magnet pada sumbu inersial bumi dapat dihitung. Dari dua vektor pada dua tata acuan yang berbeda, matriks rotasi yang merupakan representasi sikap satelit terhadap bumi dapat dihitung. Dari pengujian, metode ini berhasil menghitung sikap satelit dengan akurasi 3o.   BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12310 10.30536/j.jtd.2018.v0.a2950 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 71-82 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12310/9621 Copyright (c) 2018 Satriya Utama, Patria Rachman Hakim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12311 2025-10-03T07:30:28Z ijoa:ART

PENGARUH PENAMBAHAN FILLER SIO2, CARBON BLACK, DAN TIO2 PADA SIFAT MEKANIK LINER EPOKSI POLISULFIDA MOTOR ROKET CASE BONDED (THE EFFECT OF SIO2, CARBON BLACK AND TIO2 FILLER ADDING TO MECHANICAL PROPERTIES OF EPOXY POLYSULFIDE LINER OF CASE BONDED MOTOR ROCKET) Dewi, Wiwiek Utami Soegiono, Bambang Sifat mekanik liner Epoksi polisulfida Filler Case bonded Liner epoksi polisulfida virgin (tanpa filler) tidak cukup kuat untuk menahan beban struktural dan kondisi yang ekstrem selama roket beroperasi oleh karena itu penambahan filler sangat penting dilakukan untuk meningkatkan kekuatan mekanik liner. SiO2, carbon black dan TiO2 telah dipilih sebagai filler untuk memperkuat matriks liner epoksi polisulfida pada motor roket case bonded Lapan. Pengaruh penambahan ketiga filler tersebut pada sifat mekanik liner telah diselidiki dalam penelitian ini. Sembilan jenis komposisi liner telah dibuat dan melalui beberapa proses pengujian sifat mekanik yang meliputi: kekerasan, tegangan tarik maksimum, regangan maksimum, dan kekuatan rekat (liner terhadap logam). Hasil penelitian menunjukkan bahwa nilai kekerasan liner sebanding dengan nilai tegangan tarik maksimum liner dan nilai kekuatan rekat liner terhadap logam sebanding dengan nilai regangan maksimum, sementara itu tegangan tarik maksimum liner memiliki hubungan polinomial dengan regangan maksimumnya. Regangan maksimum tertinggi (52%) dicapai pada nilai tegangan tarik maksimum 16,25 kg/cm2. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12311 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 49-58 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12311/9622 Copyright (c) 2013 Wiwiek Utami Dewi, Bambang Soegiono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12312 2025-10-03T07:30:28Z ijoa:BP

Back Pages JTD Vol 15 No 1 Juni 2017 Jurnal, Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12312 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12312/9623 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12313 2025-10-03T07:30:28Z ijoa:FUP

Full Pages JTD Vol 15 No 1 Juni 2017 Jurnal, Redaksi -- BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12313 Indonesian Journal of Aerospace; Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12313/9625 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12314 2025-10-03T07:30:28Z ijoa:ART

METODE TRACKING KECEPATAN ROKET MENGGUNAKAN TRANSPONDER DOPPLER DUA-FREKUENSI (ROCKET SPEED TRACKING METHOD USING TWO-FREQUENCY DOPPLER TRANSPONDER) Widada, Wahyu Doppler tracking Roket Dua-frekuensi Resolusi tinggi Transponder Sistem Doppler tracking untuk roket biasanya hanya menggunakan satu frekuensi pembawa. Tulisan ini membahas sebuah metode Doppler radio pelacak roket dengan menggunakan dua frekuensi gelombang radio. Sistem ini menggunakan transponder Doppler pada frekuensi 465 MHz dan 2400 MHz secara simultan. Radio frekuensi rendah digunakan untuk mengukur kecepatan-tinggi roket dan sebaliknya gelombang radio frekuensi lebih tinggi digunakan untuk mengukur kecepatan rendah roket. Hasil yang diperoleh dari metode ini lebih akurat 5.4 kali pada kecepatan kurang dari 0.7 Mach dibandingkan dengan hasil dari sistem Doppler yang menggunakan hanya satu frekuensi radio. Metode ini cocok untuk mengukur kecepatan roket hingga 3.8 Mach. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12314 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 59-66 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12314/9624 Copyright (c) 2013 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12315 2025-10-03T07:30:28Z ijoa:ART

ANALISIS FAKTOR KOREKSI PERHITUNGAN TRAYEKTORI ROKET LAPAN, STUDI KASUS: RX200 LAPAN-ORARI (CORRECTION FACTOR ANALYSIS OF TRAJECTORY CALCULATION OF LAPAN'S ROCKET, CASE STUDY: RX-200 LAPAN-ORARI ROCKET) Andria, Novi Trayektori roket Akurasi Koefisien gaya hambat Kecepatan awal Variasi gaya dorong Selama ini perbedaan profil trayektori antara hasil simulasi dengan hasil uji terbang roket-roket Lapan masih cukup besar. Upaya perbaikan perhitungan trayektori roket dikonsentrasikan pada tiga parameter yakni nilai koefisien gaya hambat (Cd), nilai kecepatan awal (Vi) dan penyekalaan gaya dorong. Perhitungan trayektori dilakukan menggunakan simulator trayektori roket berbasiskan Simulink yang dikembangkan oleh peneliti dinamika terbang - Lapan. Model RX 200 LAPAN-ORARI 2 digunakan sebagai wahana uji. Dibandingkan dengan hasil uji terbang, error terkecil perhitungan trayektori terdapat pada simulasi dengan menggunakan nilai Vi 0 m/s dengan menyekalakan gaya dorong sebesar 97% gaya dorong yang diperoleh dari uji statik tanpa adanya perubahan nilai Cd. Penelitian ini menyimpulkan bahwa penyebab utama tidak akuratnya perhitungan trayektori roket RX 200 LAPAN-ORARI adalah bukan karena tidak tepatnya nilai Cd yang di-input-kan. Keakurasian perhitungan trayektori dapat ditingkatkan dengan menetapkan nilai kecepatan awal seperti kondisi nyata yakni 0 m/s dan nilai gaya dorong yang tepat dengan menambah frekuensi uji statik untuk motor roket sejenis. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12315 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 67-73 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12315/9626 Copyright (c) 2013 Novi Andria https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12316 2025-10-03T07:30:28Z ijoa:FP

Front Pages JTD Vol 14 No 2 Des 2016 Jurnal, Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12316 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12316/9627 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12317 2025-10-03T07:30:28Z ijoa:ART

SIMULASI ALIRAN FLUIDA DUA DIMENSI TANPA MEMBUTUHKAN KISI-KISI DENGAN MENGGUNAKAN METODE VORTEKS. STUDI KASUS ALIRAN DI SEKITAR SILINDER DAN PELAT DATAR YANG BERGERAK TRANSLASI Widodo, Akhmad Farid Zuhai, Lavi Rizki Muhammad, Hari Metode vorteks Simulasi tanpa kisi-kisi Aliran di sekitar pelat datar Aliran di sekitar silinder Makalah ini membahas algoritma metode vorteks yang merupakan metode numerik simulasi dinamika fluida tanpa membutuhkan kisi-kisi. Metode vorteks memodelkan aliran fluida dengan pendekatan Lagrangian dimana elemen fluida didiskritisasi menjadi bola-bola partikel yang bergerak mengikuti aliran fluida. Untuk menguji hasil simulasi metode vorteks, dilakukan simulasi aliran yang bergerak secara tiba-tiba disekitar silinder dan aliran disekitar pelat datar yang bergerak secara translasi. Hasil simulasi memberikan hasil yang cukup baik dibandingkan dengan pengukuran eksperimental yang ditunjukkan dengan perbandingan pola distribusi vortisitas. BRIN Publishing 2013-12-20 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12317 Indonesian Journal of Aerospace; Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara; 75-84 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12317/9629 Copyright (c) 2013 Akhmad Farid Widodo, Lavi Rizki Zuhai, Hari Muhammad https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12319 2025-10-03T07:30:29Z ijoa:ART

Development of Mobile Ground Control System and GPS Base Auto Tracking Antenna Irwanto , Herma Yudhi high speed UAV mobile ground control system (GCS) GPS base auto tracking antenna hardwar in the loop simulation Flight test of both rocket and high speed Unmanned Aerial Vehicle (UAV), which is currently developed by LAPAN, can not be separated from the need for a monitoring system of all the attitude of the vehicles. Utilizing and combining some of the available equipment components into a ground control system (GCS) equipped with GPS based auto tracking antenna, makes it easy in previous flight test activities that only do tracking antenna manually. This ground control system is equipped with automatic tracking antenna that always leads to the vehicle, so that the data attitude of flying the vehicle will be maximally monitored and analyzed directly with ease. This system has been tested on a laboratory scale related to testing using hardware in the loop simulation system   BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12319 10.30536/j.jtd.2018.v16.a2880 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara; 83-92 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12319/9628 Copyright (c) 2018 Herma Yudhi Irwanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12320 2025-10-03T07:30:29Z ijoa:BP

Back Pages JTD Vol 16 No.1 Juni 2018 Jurnal, Redaksi - BRIN Publishing 2018-09-17 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12320 Indonesian Journal of Aerospace; Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12320/9630 Copyright (c) 2018 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12321 2025-10-03T07:30:29Z ijoa:ART

ALGORITMA PERINGATAN DINI PENCURIAN IKAN PADA DATA AUTOMATIC IDENTIFICATION SYSTEM (AIS) BERBASIS TERESTRIAL DAN SATELIT (ILLEGAL FISHING EARLY WARNING ALGORITHM FOR TERESTRIAL AND SATELLITE-BASED AUTOMATIC IDENTIFICATION SYSTEM (AIS) DATA) Husni, Emir Mauludi R. S., Muhammad Riksa Andanawari Triharjanto, Robertus Heru AIS Pencurian ikan Satelit Pemrograman Python Illegal fishing Satellite Python programming Pencurian ikan merupakan kegiatan yang menyebabkan kerugian sangat besar untuk Indonesia, sementara wilayah perairan Indonesia yang luas membuat kegiatan pengawasan pencurian ikan tersebut menjadi sulit dilakukan. Peraturan internasional yang mewajibkan setiap kapal di atas 300 GT untuk mengirimkan data menggunakan AIS menjadi kesempatan untuk mendeteksi kapal-kapal yang melakukan pencurian ikan. Kemampuan Indonesia untuk mendeteksi sinyal AIS dari satelit LAPAN-A2/Orari memperbesar kesempatan tersebut. Penelitian ini bertujuan membangun bagian dari sistem peringatan dini aktivitas pencurian ikan, berdasarkan data AIS yang diterima oleh sensor di garis pantai dan di satelit. Proses pendeteksian dilakukan dengan menganalisa data perjalanan dari sistem AIS. Jenis-jenis pencurian ikan yang dapat dideteksi oleh algoritma ini adalah trans-shipment, penggunaan pukat harimau, pelanggaran zona teritorial, pelanggaran tidak melapor, pelanggaran wilayah penangkapan, dan pelanggaran tidak mengaktifkan pemancar sinyal AIS. Algoritma yang digunakan adalah metode Ray Casting, untuk menentukan suatu kapal berada dalam satu wilayah atau tidak. Perbaikan performa algoritma ini dilakukan dengan melakukan proses multithreading menggunakan kode Python. Algoritma diuji dengan data AIS dari LAPAN-A2/Orari dan data simulasi. Hasil menunjukkan bahwa algoritma yang dirancang untuk sistem analisis peringatan dini pencurian ikan (illegal fishing) dengan data AIS berhasil mendeteksi 6 jenis pelanggaran sesuai ketentuan Kementerian Kelautan dan Perikanan (KKP) Republik Indonesia yang telah disebutkan di atas dengan menggunakan data simulasi. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12321 10.30536/j.jtd.2016.v14.a2385 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 81-90 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12321/9632 Copyright (c) 2025 Emir Mauludi Husni, Muhammad Riksa Andanawari , Robertus Heru Triharjanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12322 2025-10-03T07:30:29Z ijoa:ART

IDENTIFIKASI PARAMETER DAN PERANCANGAN SISTEM KENDALI PID UNTUK ANALISIS SIKAP TERBANG UAV [PARAMETER IDENTIFICATION AND DESIGN PID CONTROLLER FOR FLYING ATTITUDE ANALYSIS OF UAV] Purwanto, Eko Budi Nasution, Syahron Hasbi Supendi identification system PID parameter Kalman filter Maximum overshoot Based on the state space yield first principle method knowed that characteristic of UAV is static stable. To get the near real condition doing verification of state space model by using the identification system toolbox of Matlab. The yield show that matrix element of state space is different both of them. Furher step is design the PID control system base on new state space, and for improve the performance system used Kalman filter. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12322 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara; 81-93 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12322/9631 Copyright (c) 2013 Eko Budi Purwanto, Syahron Hasbi Nasution, Supendi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12324 2025-10-03T07:30:29Z ijoa:ART

IMPLEMENTASI 3D GAME ENGINE SEBAGAI VISUALISASI SISTEM NAVIGASI 6-DOF PADA ROKET KENDALI LAPAN [3D GAME ENGINE IMPLEMENTATION AS 6-DOF NAVIGATION SYSTEM VISUALIZATION AT GUIDED ROCKET OF LAPAN] Wiryadinata, Romi Munarto, Ri Yusuf, Wildan Kaharjito, Frandi A 3D Game Engine Graphical User Interface IMU 6-DOF Game engine, which are often used by game developers, has software framework that facilitates their work on important tasks such as graphic design or 3D and 2D graphics rendering. This research uses game engine called 3D state game engine for visualize 6-DOF navigation system. The software is developed for visualize range of motion of the object by reading and processing the streaming data from navigation sensor (accelerometers and rate-gyroscope). The test result show that developed software can visualize the motion of the objects in 3D animation. Software can accept and process the data as text file that is transmited in real-time through serial port. IMU hardware with sofware can use through the calibration process first, and be given a filter, so that the better results can be obtained. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12324 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara; 95-105 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12324/9633 Copyright (c) 2013 Romi Wiryadinata, Ri Munarto, Wildan Yusuf, Frandi A. Kaharjito https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12325 2025-10-03T07:30:29Z ijoa:ART

LENDUTAN STRUKTUR TWIN BOOM PESAWAT TERBANG NIR AWAK LSU-05 PADA SAAT MENERIMA BEBAN TERBANG (DEFLECTION OF LSU-05 UAV TWIN BOOM STRUCTURE ON RECIEVING THE FLIGHT LOAD) Bintoro , Atik Pesawat terbang nir awak LSU-05 Beban terbang Lendutan Twin-boom Struktur E-glass UAV Flight load Deflection Struktur twin boom merupakan salah satu komponen konstruksi pesawat terbang nir awak LSU-05 hasil karya Pusat Teknologi Penerbangan - LAPAN. Struktur ini berfungsi sebagai penyetabil gerakan pesawat. Dalam operasionalnya, struktur menerima beban terbang yang dapat mengakibatkan timbulnya lendutan. Melalui metode analitis yang melibatkan misi, dimensi dan konfigurasi struktur twin boom pesawat LSU-05, telah dilakukan penelitian untuk mengetahui sejauh mana kemampuan struktur dalam menerima beban terbang, sehingga mengakibatkan lendutan tersebut. Dari penelitian ini diketahui bahwa pada saat penerbangan, selama 130 menit mulai dari tinggal landas di awal penerbangan sampai dengan terbang jelajah pada kecepatan maksimal 130 km/jam, lendutan maksimal yang terjadi pada struktur hanya mencapai 5,593 x 10-6 m, dengan faktor keamanan sebesar 1,3 berarti struktur relatif aman. Sedangkan untuk pendaratan, kecepatan yang relatif aman dapat dilakukan di bawah 14 km/jam. Jika mendarat pada kecepatan melebihi 20 km/jam, struktur twin boom tersebut mengalami kerusakan parah, karena tegangan yang terjadi sudah melebihi 650 MPa sebagai tegangan ijin bahan struktur yakni komposit e-glass. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12325 10.30536/j.jtd.2016.v14.a2386 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 91-102 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12325/9634 Copyright (c) 2025 Atik Bintoro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12326 2025-10-03T07:30:29Z ijoa:ART

PENGEMBANGAN ANTENA HELIKS X-BAND 8,2 GHZ UNTUK SATELIT MIKRO (DEVELOPMENT OF 8.2 GHZ X-BAND HELICAL ANTENNA FOR MICRO SATELLITE) Faizal , Iwan Helical antenna beamwidth gain impedance VSWR antena heliks lebar berkas penguatan impedansi Antena heliks adalah salah satu antena yang sangat populer dikalangan satelit amatir. Pada frekuensi X-Band antena berpolarisasi sirkuler sangat diperlukan, karena dapat mengatasi efek dari anomali propagasi, refleksi tanah, dan efek spin yang banyak terjadi pada satelit. Antena ini memilki gain yang cukup besar, dapat mencapai 15 dB dan memiliki pola radiasi terarah dengan rasio lebar pita 1,78:1 dan hampir mendekati antena broadcast (≥ 2). Tujuan dari penelitian ini adalah untuk merancang, membuat prototipe dan menganalisis performa antena heliks X-Band pada frekuensi 8,2 GHz untuk satelit mikro, yang mengacu pada desain satelit LAPAN-A3. Metode manufaktur antena ini menggunakan kawat tembaga berlapis perak yang digunakan untuk lilitan heliks dengan diameter 1,29 mm atau AWG 16. Perangkat lunak yang digunakan untuk mendesain antena heliks adalah 4NEC2. Hasil uji simulasi desain antena helix diperoleh nilai VSWR 3,3, dan beamwidth 66 derajat. Dari hasil pengujian VSWR  yang didapat adalah 1,39 dan beamwidth 66 derajat. Perbedaan VSWR tersebut dikarenakan 4NEC2 menggunakan teknik axial feed, sementara prototipe antena heliks menggunakan teknik peripheral feed pada penyesuai impedansinya. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12326 10.30536/j.jtd.2016.v14.a2494 Tweet Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 103-112 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12326/9635 Copyright (c) 2025 Iwan Faizal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12327 2025-10-03T07:30:29Z ijoa:ART

DESAIN AWAL SISTEM SATELIT TELEKOMUNIKASI PERTAHANAN INDONESIA (PRELIMINARY DESIGN OF INDONESIAN MILITARY TELECOMUNICATION SATELLITE) Triharjanto, Robertus Heru Faturrohim, Luqman Poetro, Ridanto Eko Muhammad, Hari Desain satelit telekomunikasi pertahanan TNI satellite design defense telecommunications Indonesian millitary desain satelit Indonesia sebagai negara kepulauan terluas di dunia amat memerlukan sistem satelit untuk menunjang sistem pertahanan dan keamanannya. Atas motivasi tersebut penelitian ini bertujuan untuk membuat desain awal sistem satelit telekomunikasi yang diperlukan untuk pertahanan dan keamanan di Indonesia. Sesuai kaidah perancangan satelit, proses desain awal didahului dengan pembuatan desain konsep. Pada proses desain konsep dilakukan pendefinisikan kebutuhan penggguna, dalam hal ini pihak TNI dan Kementerian Pertahanan, dan studi banding atas solusi satelit telekomunikasi pertahanan di mancanegara. Hasil desain konsep adalah persyaratan misi dan batasan desain, yang harus diacu pada tahap desain awal satelit. Desain awal, diantaranya, menetapkan desain muatan sehingga dapat mengakomodasikan misi, serta ukuran dan berat dari bus satelit, agar bisa memenuhi kebutuhan muatan. Hasil menunjukkan bahwa pemenuhan desain konsep hanya bisa dilakukan dengan desain awal 2 tipe satelit telekomunikasi, yakni dengan frekuensi L-band untuk komunikasi bergerak, dan frekuensi C-band untuk komunikasi statis dengan kecepatan tinggi. Sesuai ketersediaan slot yang menjadi batasan desain, satelit L-band akan ditempatkan di 123 BT. Satelit tersebut mempunyai berat 2200 kg, konsumsi daya 1 kW, dan dapat melayani komunikasi data dengan kecepatan 512 kbps. Satelit C-band, yang akan berada di 118 BT, mempunyai berat 2400 kg, kapasitas daya 1.5 kW, dan dapat melayani komunikasi data dengan kecepatan 10 Mbps. Kedua satelit tersebut dapat beroperasi selama 10 tahun. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12327 10.30536/j.jtd.2016.v14.a2519 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 113-124 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12327/9636 Copyright (c) 2025 Robertus Heru Triharjanto, Luqman Faturrohim, Ridanto Eko Poetro, Hari Muhammad https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12328 2025-10-03T07:30:29Z ijoa:ART

METODE KALIBRASI SENSOR RATE-GYROSCOPE UNTUK IMU ROKET [CALIBRATION METHOD OF RATE-GYROSCOPE SENSOR FOR IMU ROCKET] Wahyudi Susanto, Adhi Widada, Wahyu Hadi, Sasongko Pramono Calibration Rate-gyroscope IMU Rate-gyroscope sensor is used in the IMU to measure the rotation angle in three axes. The output of rate-gyroscope sensor is a voltage which is the angular rate, so to obtain the angle used once an integral process. The integral result of rate-gyroscope sensor depend on sampling time or the cycle time of program to get the datum, so the integral calculation depends on the processor speed of microcontroller (computer). Using of the different sampling time will affect the integral result or in other words we can say that for the same program, if we apply it to a different microcontroller, we will obtain the different calculation. This paper presents the calibration method for determining the calibration factor on the rate-gyroscope sensor, so we will get the actual angle value. The rate-gyroscope sensors on different axes have different characteristics, so each sensor needs to be calibrated. In the experiment results, the calibration factors in three axes are different in both for the clockwise rotation and counterclockwise rotation. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12328 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara; 105-111 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12328/9637 Copyright (c) 2013 Wahyudi, Adhi Susanto, Wahyu Widada, Sasongko Pramono Hadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12329 2025-10-03T07:30:29Z ijoa:ART

Ahmad Alsahlani and Thurai Rahulan, 2017, Composite Structural Analysis of a High Altitude, Solar Powered Unmanned Aerial Vehicle, International Journal of Mechanical Engineering and Robotics Research Vol. 6, No. 1, January 2017 Atik Bintoro, 2016, Lend Marta, Aryandi Bintoro, Atik MUS-01 LSU-03NG characteristic MTOW The characteristic model of MUS-01 wing structure testing has been performed. Planned, this model will be used as an unmanned wing of the LSU-03NG. The test model is made of composite type e-glass. At the time of testing the structure test model is loaded according to MTOW weight. This research method also involves the unmanned aircraft mission, especially on the model test structure, model dimension, and direct experiment in the form of loading on the test model. The result of characterization of the test model during test, showed that the indicated test model has the characteristics as a test model that is unable to accept the unmanned operational load of LSU-03NG series aircraft. So it can not be used as a consideration for the structure of the unmanned aircraft.   BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12329 10.30536/j.jtd.2018.v16.a2962 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 93-100 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12329/9638 Copyright (c) 2019 Aryandi Marta, Atik Bintoro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12330 2025-10-03T07:30:29Z ijoa:ART

PENGUJIAN MODUL PENGOLAH DATA TELEMETRI LAPAN-A3/IPB UNTUK MENGHASILKAN PRODUK LEVEL-0 (THE TESTOF LAPAN-A3/IPB TELEMETRY DATA PROCESSOR MODULE TO PRODUCE LEVEL-0 PRODUCT) Suhermanto, Suhermanto telemetry raw-data decoding decomposision quicklook Telemetry data processing modulis a software for converting the LAPAN-A3/IPB telemetry data into raw sensor data (level-0 product). Telemetry data output from the High Data Rate Modulator-demodulator (HDRM) becomes an input for telemetry data processor, which has entered its setup parameter. The objective of the research is to test LAPAN-A3/IPB telemetry data processor implementation. The development and processing of telemetry data have been performed on a desktop computer that are divided into two stages, data decoding and data decomposition.The performance of the software has been tested using eight samples of raw-data, consisted of multi-spectral and camera matrix data obtained before and after the launch of the satellite. The test results showed, there were no missing telemetry data frames and damaged codeword in the process of decoding.Data on missing multi-spectral lines  and data on camera matrix frame lost in the process of decomposition were not found. It was concluded that the overall performance of the test result was that the system used was not able todecode, decompose, display quick-look LISA, or extractcamera matrix data in real-time.To perform as required, the computer performance needed to be increased up to 8 times. From this process, approximately 92% of CPU time were used for decoding and only about 8% were for the decomposition, extraction of data LISA, or extraction of data camera matrix.Improvement attempt by changing the word-size of 32bit processors into 64bit, did not give significant results and was only able to improve the processing speed of 8.1%. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12330 10.30536/j.jtd.2016.v14.a2510 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 125-136 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12330/9639 Copyright (c) 2025 Suhermanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12331 2025-10-03T07:30:29Z ijoa:ART

METODE DOPPLER RADIO UNTUK MENGUKUR KECEPATAN ROKET RX200 [RADIO DOPPLER METHOD FOR MEASURING VELOCITY OF ROCKET RX200] Widada, Wahyu Doppler tracking Radio transponder Frequency variation This paper discusses the methods and design of radio Doppler to measure the speed of the rocket type RX200. Doppler system consists of a radio transponder to emit a continuous radio signal from the rocket and the radio base station to measure the change in frequency of the radio signal. A change in the frequency of the radio signal caused by the speed of the rocket is used to measure the speed and position of the rocket. The design of radio frequency is 880 MHz transponder adapted to the design speed of the rocket RX200. This method is relatively easy to implement compared with the radar transponder system that has been developed. A simulation of Doppler frequency is performed using the radar data transponder rocket launch experiment RX200 and recomendation of bandwith radio receiver should be 4000 Hz. The combination of these two systems will make a more acurate and reliable tracking system. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12331 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara; 113-119 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12331/9640 Copyright (c) 2013 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12332 2025-10-03T07:30:29Z ijoa:ART

ISOMERISASI POLIMER MELALUI REAKSI SAIN SAYEF UNTUK MENGUBAH KONFIGURASI HTPB (HYDROXYL TERMINATED POLYBUTADIENE) POLYMER ISOMERIZATION BY SAIN SAYEF REACTION TO MODIFY CONFIGURATION OF HTPB (HYDROXYL TERMINATED POLYBUTADIENE) Heru Budi Wibowo PDF 137- Wibowo , Heri Budi polybutadiene propellants polymers Sain Sayef One of the problems in the synthesis of Hydroxyl Terminated Polybutadiene for propellant binders is the level of vinyl is high (up to 30%), while the desired product is 20%. Vinyl bond can be reduced if the chain can be broken with the addition of a hydroxyl group. The research objective is to reduce the amount of vinyl structure in HTPB with the addition of double bonds in the vinyl by applying Sayef Sain reaction. HTPB is reacted with concentrated hydrogen peroxide with the Sain Sayef catalyst in the 1 liter autoclave reactor with ethanol for 1-3 hours at 100° C. After being purified by extraction in hot water and drying, it is analyzed by an infrared spectrometer. The result shows that there is a change in the concentrations of vinyl within the polymers produced by observing the absorption of vinyl groups at a wavelength of 690cm-1. Optimal results obtained with vinyl content of 20% with a temperature of 100° C for 90 minutes. In general, the quality of HTPB can be increased by reducing the levels of vinyl which allowing the HTPB composition to have a vinyl content reduced to 19%. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12332 10.30536/j.jtd.2016.v14.a2387 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 137-146 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12332/9642 Copyright (c) 2025 Heri Budi Wibowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12333 2025-10-03T07:30:29Z ijoa:ART

SISTEM PENYALA NIRKABEL JARAK JAUH UNTUK MUATAN ROKET (WIRELESS SWITCHING FOR ROCKET PAYLOAD) Artono, Endro Salman, Salman muatan nirkabel saklar elektronika Proses penyalaan sistem elektronika pada muatan roket hasil litbang LAPAN selama ini masih manual, dengan menggeser atau menekan saklar pada tabung muatan roket dari posisi mati (OFF) ke posisi hidup (ON). Sistem penyala muatan roket ini dirancang untuk dapat menyalakan atau mematikan muatan roket dengan tanpa melakukan kontak fisik antara operator dengan roket. Dari hasil penelitian ini, muatan roket dapat dinyalakan ataupun dimatikan dari ruang kontrol (ground station) secara nirkabel. Sistem ini juga dapat melepaskan perangkat antarmuka untuk sistem penyalaan dari badan roket, sehingga tidak mengganggu roket saat diluncurkan.   Currently, process for turning on the LAPAN rocket’s payload still manually, by shifting or pushing the manual switch placed on the payload rocket’s body, to the OFF or ON direction/ position. This payload wireless switching system is designed for turning the rocket payload to ON or OFF wirelessly, without any phisical contact from operator to the rocket body. The experiment proof that the rocket payload can be turning ON or OFF from the control room wirelessly. The system can also release the umbilical interface from the rocket body before the rocket launched to prevent disruption. BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12333 10.30536/j.jtd.2018.v16.a2976 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 101-110 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12333/9641 Copyright (c) 2019 Endro Artono, Salman https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12334 2025-10-03T07:30:29Z ijoa:ART

MODEL KOREKSI GEOMETRI SISTEMATIK DATA IMAGER PUSHBROOM MENGGUNAKAN METODE PROYEKSI KOLINEAR [PUSHBROOM IMAGER DATA SYSTEMATIC GEOMETRIC CORRECTION MODEL USING COLLINEAR PROJECTION METHOD] Hakim, Patria Rachman Rahman, Abdul Suhermanto Rachhim, Elvira Systematic geometric correction Pushbroom imager Colinear projection Ancillary data LAPAN-A3 satellite, which is planned to be launched on 2014, will carry a 4 channels pushbroom imager. An image pre-processing is needed to assure that there will be no distortion on the output image data, particularly a systematic distortion, whether it is geometric or radiometric. Systematic geometric correction is intended to eliminate geometric distortion which are predictable such as view angle, earth curvature, earth rotation and varrying camera orientation during observation. The colinear projection method is used in order to transform every pixel on the image into earth coordinate points. Systematic geometric correction needs satellite ancillary data such as position and camera orientation from GPS and star sensor. This research simulated dummy data as substitute to distorted image and ancillary data for designing and simulation purpose. The simulation result shows that the systematic geometric correction algorithm is able to correct the distortion occured in image. A corrected image with 1000 meter accuracy can be achieved with 0,1 degree orientation data accuracy while 0,01 degree orientation data accuracy produces an even better 100 meter accuracy corrected image for nadir observation. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12334 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara; 121-132 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12334/9643 Copyright (c) 2013 Patria Rachman Hakim, Abdul Rahman, Suhermanto, Elvira Rachhim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12335 2025-10-03T07:30:29Z ijoa:ART

PENGUKURAN TURBULENSI DAN ANGULARITAS ALIRAN PADA TEROWONGAN ANGIN SUBSONIK LAPAN (THE MEASUREMENT OF TURBULENCE AND FLOW ANGULARITY IN LAPAN’S SUBSONIC WIND TUNNEL) Hartono, Firman Bessie, Ronald Aribowo, Agus wind tunnel turbulence measurement angularity This paper explains the measurement of turbulence intensity and angularity in LAPAN’s Open Loop Subsonic Wind Tunnel. The objective of the research is to find out the aerodynamic characterstic of the tunnel. Turbulence intensities were measured using 200 mm and 300 mm diameter turbulence sphere. The flow angularity in the cross section of tunnel’s test section was measured using five holes probe at two different axial position i.e. 1. above internal balance turning table and 2. above external balance turning table. The number of measured points are 110 for every cross section plane and the average velocity during angular flow measurement is 15 m/s. Turbulence measurements shows wind tunnel’s turbulence intensity of 0.26% at 25.9 m/s and 0.1% at 19 m/s. Angularity measurement shows relatively large angular flow variation in the jet, i.e. pitch angle of ±3o and achieving +7o at some locations and yaw angle of ±2.5o. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12335 10.30536/j.jtd.2016.v14.a2481 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 147-158 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12335/9645 Copyright (c) 2025 Firman Hartono, Ronald Bessie, Agus Aribowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12336 2025-10-03T07:30:29Z ijoa:ART

Review Perbandingan Teknik Maximum Power Point Tracker (MPPT) untuk Sistem Pengisian Daya menggunakan Sel Surya Azmi, Bayu H, Jefri Abner E B, Prasepvianto Seputra, Hendrik Energi surya Photovoltaic MPPT Konvensional kecerdasan buatan Energi surya telah dianggap sebagai prospek sumber energi terbarukan untuk pembangkit tenaga listrik. Sistem fotovoltaik surya menjadi objek yang populer untuk dikembangkan oleh peneliti. Rendahnya efisiensi dalam konversi energi adalah salah satu kelemahan sistem ini. Modul fotovoltaik memiliki titik operasi tunggal di mana output tegangan dan arus menghasilkan output daya maksimum. Dalam kebanyakan sistem fotovoltaik, algoritma kontrol tertentu, yaitu Maximum Power Point Tracker (MPPT) untuk memanfaatkan secara maksimal energi surya tersebut. Ada tiga metode utama pada MPPT yaitu metode konvensional, metode kecerdasan buatan, dan metode hibrid. Setiap metode memiliki kelebihan dan juga kekurangan. Metode konvensional memiliki kelebihan seperti biaya rendah dan implementasi yang sederhana tetapi juga memiliki kerugian seperti tidak dapat beradaptasi dengan kondisi lingkungan. Metode berdasarkan kecerdasan buatan memiliki Power Point Tracking yang lebih cepat dan koreksi terhadap kondisi lingkungan sebagai kelebihannya tetapi juga memiliki kerugian seperti penerapan yang lebih rumit dan biaya yang lebih mahal.   BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12336 10.30536/j.jtd.2018.v16.a2998 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 111-122 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12336/9644 Copyright (c) 2019 Bayu Azmi, Jefri Abner H, Prasepvianto E B, Hendrik Seputra https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12337 2025-10-03T07:30:29Z ijoa:ART

PENGARUH NILAI KOEFISIEN AERODINAMIKA DAN PADA KESTABILAN TERBANG GERAK PERIODE PENDEK (SHORT PERIOD) RKX-200 LAPAN [EFFECT OF AERODYNAMICS COEFFICIENT VALUE AND TO THE STABILITY OF THE FLY MOTION SHORT PERIOD RKX-200 LAPAN] GS, Endang Mugia A short period modes of motion The rocket flew of short period modes of motion, can be used as a way to measure the stability of the rocket flying. By performing simulation using software Missile DATCOM obtained aerodynamic coefficient and , each of which affects the value of the natural frequency and damping motion short period. RKX-200 Lapan rocket is a quite stable rocket. And the magnitude of the aerodynamic coefficient : -0,12 to -.0,02 and value of : -2,4 to -1,2, with each value remains negative at cruising speed prediction of 0,1 M s.d 2,0 M. It’s good enough to be the guided missile with value 0,18  SM  0,46. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12337 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara; 133-137 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12337/9646 Copyright (c) 2013 Endang Mugia GS https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12338 2025-10-03T07:30:29Z ijoa:ART

PERUBAHAN KARAKTERISTIK PEMBENTUKAN POLIURETAN BERBASIS HTPB DAN TDI BERDASARKAN KOMPOSISI REAKSI (CHANGES IN THE FORMATION CHARACTERISTICS OF POLYURETHANE BASED ON HTPB AND TDI REACTION COMPOSITION) Rosita , Geni cross-lingking polymer chain of polymer swelling HTPB TDI Polyurethane formation occurs through crosslinking of a reaction between the hydroxyl group (OH) of HTPB and isocyanate (NCO) of TDI. Polymer network formation reaction will be formed from the linear bond and a combination of crosslinking. At longer reaction, the polyurethane chains are formed increasingly long and followed by changes in the characteristics. If the reaction has been perfect then the polyurethane chain is  straight and it will become more flexible. Â This research aimed to obtain polyurethane as fuel binder, which was indispendable in solid composite propellant manufacturing. Several samples of existing HTPB were made into a different composition of HTPB/TDI. The process used  reaction kinetics methods based on the composition in order to obtain the mechanical properties of polyurethane.  Average molecular weight, crosslinking density, hardness, and swelling were analized to determine the quality of polyurethane as fuel-binder. The analysis was a consideration for determining the most suitable fuel-binder composition. It was also to test the quality of experimental HTPB produced by LAPAN HTPB Laboratory (HTPBlocal) as an initial procedure in the propellant manufacturing. The analysis showed different results for each composition. The compositions that could be used as the fuel-binder for the formation of polyurethanes were: HTPBA at 7: 1; HTPBB at 9: 1; HTPBC at 8: 1; and HTPBD at 8: 1; whereas HTPBE could not be used because required advanced processing. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12338 10.30536/j.jtd.2016.v14.a2420 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara; 159-170 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12338/9647 Copyright (c) 2025 Geni Rosita https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12339 2025-10-03T07:30:29Z ijoa:ART

EVALUASI KINERJA SAMBUNGAN PROPELAN PADA MOTOR ROKET RX 550 [EVALUATION OF THE PROPELLANT JOINT PERFORMANCE IN ROCKET MOTOR RX 550] Sutrisno Propellant Propellant joint Static test The propellant joints quality of RX 550 rocket motor using segmented HTPB propellant was become a debatable. In static test this rocket motor exploded and the nozzle was broken out at seven second after ignition. To evaluate these propellant joints the propellant installation in rocket motor was discused. The propellant joint strength was tested using Tensilon UTM III-100 test equipment. The rocket motor tube at the propellant joint position were marked and investigated before and after static test. The datas such as thrust and chamber pressure versus time were analyzed for finding the posibility of joints defect. Based on analysis it is found that the propellant joint can work well. The RX 550 rocket motor failure in static test didn’t caused by propellant joints. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12339 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12339/9650 Copyright (c) 2013 Sutrisno https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12340 2025-10-03T07:30:29Z ijoa:BP

Back Pages JTD Vol 14 No 2 Des 2016 Jurnal, Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12340 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12340/9648 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12341 2025-10-03T07:30:29Z ijoa:FUP

Full Pages JTD Vol 14 No 2 Desember 2016 Jurnal, Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12341 Indonesian Journal of Aerospace; Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12341/9649 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12342 2025-10-03T07:30:29Z ijoa:ART

KAJIAN PROGRAM PENINGKATAN KINERJA PROPELAN KOMPOSIT BERBASIS AP/HTPB/AL Wibowo , Heri Budi propelan komposit kinerja propelan roket sonda Kajian strategi litbang dalam meningkatkan kinerja propelan komposit berbasis AP/HTPB/Al dilakukan dalam rangka mencapai teknologi propelan yang setara dengan negara maju dalam penguasaan teknologi roket sipil, khususnya untuk roket Sonda dan roket Pengorbit Satelit di LAPAN. Kajian dilakukan dengan melakukan review terhadap capaian proplelan saat ini, analisis penyebab-penyebabnya, dan penyusunan strategi untuk mengatasinya. Hasil kajian menunjukkan bahwa diperlukan organisasi, tahapan litbang dan pengelolaan SDM yang sistematis, serta tahapan pencapaian teknologi yang perlu dilakukan. Keterbatasan bahan baku propelan merupakan masalah utama dalam pengembangan propelan di Indonesia. Peningkatan kinerja propelan dapat dilakukan dengan meningkatkan solid loading density dan penambahan bahan energetik tinggi. BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12342 10.30536/j.jtd.2018.v16.a3002 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 123-138 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12342/9651 Copyright (c) 2019 Heri Budi Wibowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12343 2025-10-03T07:30:29Z ijoa:ART

SIMULASI CFD PADA DIFFUSER AUGMENTED WIND TURBINE (DAWT) : EFEK BENTUK INLET DAN PANJANG DIFUSER TERHADAP DISTRIBUSI KECEPATAN ANGIN DI EXIT DIFUSER Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Wind turbine Diffuser CFD The objective of the research is to obtain a lighter diffuser design. It is done by modifications previously designed diffuser on the shape and length of its inlet. Thus the study analyze the effect of modified inlet and diffuser length on the distribution of wind speeds at the nozzle exit. Analysis was performed using a CFD-based software. Modifications was made to the diffuser inlet and exit diameter each-amounting to 4 and 2 m. Modified inlet can improve performance by 1.4%; meanwhile the wind angle of 60º, the performance was reduced by 2.45%, due to the separation. Shortening the length diffuser can reduce the velocity distribution in the exit, maximum of occurs at length of 1 m at 4.6%. Therefore it is recommended that optimum diffuser length is 2 m. BRIN Publishing 2013-03-15 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12343 Indonesian Journal of Aerospace; Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara; 149-160 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12343/9652 Copyright (c) 2013 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12344 2025-10-03T07:30:30Z ijoa:FP

Front Pages JTD Vol 14 No 1 Jun 2016 Tekgan, Redaksi Jurnal - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12344 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; i-v 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12344/9653 Copyright (c) 2025 Redaksi Jurnal Tekgan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12345 2025-10-03T07:30:30Z ijoa:ART

PENGARUH DIOCTYL ADIPATE TERHADAP SIFAT RHEOLOGIKAL HTPB TERPLASTISISASI (EFFECT OF DIOCTYL ADIPATE ON THE RHEOLOGICAL PROPERTIES OF PLASTICIZED HTPB) Restasari, Afni Abdillah, Luthfia Hajar Budi, Rika Suwana Hartaya, Kendra Rheologi Plasticizer Binder Propelan Shear Thickening Polimer Pengembangan pengetahuan terhadap sifat rheologikal isian cair dari propelan berguna untuk mendapatkan sifat slurry yang optimum. Pengembangan ini dapat dimulai dari campuran HTPB-DOA sehingga penelitian ini bertujuan untuk mengetahui pengaruh DOA terhadap sifat rheologikal HTPB-DOA yang meliputi sifat alir terhadap shear rate, viskositas dan viskositas saat zero shear rate. Dalam metodenya, DOA divariasi 0, 5, 10, 15 dan 20% dan dicampur dengan HTPB. Sifat rheologikal dipahami dengan mengukur viskositasnya pada kecepatan putar 0,5; 1; 1,5; 2; 2,5; 3; 4 dengan spindel tipe 2 dari viskometer Brookfield dan menganalisa grafik shear stress vs shear rate serta viskositas vs shear rate. Berdasarkan analisa tersebut, diketahui bahwa campuran HTPB-DOA bersifat shear thickening. Semakin banyak DOA yang ditambahkan, semakin rendah viskositas campuran, semakin rendah nilai viskositas pada zero shear rate dan semakin kuat sifat shear thickening dari campuran. BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12345 10.30536/j.jtd.2018.v16.a3003 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 139-148 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12345/9654 Copyright (c) 2019 Afni Restasari, Luthfia Hajar Abdillah, Rika Suwana Budi, Kendra Hartaya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12346 2025-10-03T07:30:30Z ijoa:ART

ALGORITMA DETEKSI FREKUENSI DTMF MENGGUNAKAN KORELASI SILANG UNTUK TELEKOMANDO WAHANA TERBANG (DTMF FREQUENCY DETECTION ALGORITHM USING CROSSCORRELATION FOR VEHICLE TELECOMMAND) Kliwati , Sri Frequency DTMF Detection of cross-correlation In general, the frequency DTMF detection algorithm using FFT (Fast Fourier Transform) and Goertzel Algorithm. However, in certain circumstances a more suitable signal detected by the other algorithms. For example in a non-periodic signal as the measurement sensors for flight vehicle. The purpose of this study is to develop a system telecommand for flight vehicle. And this paper discusses the frequency DTMF (Dual Tone Multi Frequency) detection method using cross correlation algorithm and data-base DTMF. The simulation results show the frequency detection successfully carried out in accordance with the accuracy of the data-base created (1 Hz) to change the frequency of zero to 1700 Hz (DTMF frequency limit). BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12346 10.30536/j.jtd.2016.v14.a2942 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 1-8 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12346/9655 Copyright (c) 2025 Sri Kliwati https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12347 2025-10-03T07:30:30Z ijoa:ART

PEMODELAN SISTEM DAN ANALISIS KESTABILAN DINAMIK PESAWAT UAV (MODELING SYSTEM AND DYNAMIC STABILITY ANALYSIS OF UAV) Purwanto, Eko Budi State space Longitudinal Lateral Stable static Stable dynamic Mission of Unmanned Aerial Vehicle (UAV) “Elang Avionik†is surveillance and aerial photographs. Therefore the flight of UAV must be stable and controlable, and first step activity is dynamic modelling and stability analisys. The problems of UAV system is disturbance, noise of sensor, MIMO and uncertainty dynamic model. For good result using the multivariable robust control, with some step research that is: (1)modeling and stability analysis, (2) design and implementation of PID control system, (3) flight dynamic parameter identification, (4) design and implementation of hardware in the loop simulation, (5) design and implementation of multivariable robust control, (6) test and evaluation of system. Simulation result show that the eigen value in longitudinal is: phugoid mode = –0,061293±0,40526i and non-oscillation mode = –6,1121±4,9253. In lateral directional is:dutch roll mode = –0,91089±5,7994i, spiral mode= –0,036563, and roll subsidence mode = –12,7181. Location of poles system on the left of imaginary axis, the means that the character of system is dynamic stable. But settling time to steady state condition is very long and improved by control system design.Key word: State space, Longitudinal, Lateral, Stable static, Stable dynamic BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12347 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 1-12 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12347/9656 Copyright (c) 2012 Eko Budi Purwanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12348 2025-10-03T07:30:30Z ijoa:ART

PENGATURAN SUDUT AZIMUTH ROKET RUM UNTUK OPERASI PELUNCURAN PADA KECEPATAN ANGIN DI ATAS 10 KNOT (AZIMUTH ANGLE’S SETTING OF ROCKET RUM FOR LAUNCH OPERATION AT WIND SPEED MORE THAN 10 KNOT) Wibowo, Heri Budi Riyadl, Ahmad Nugroho, Yudha Agung Roket RUM stability Azimuth angle of attack the wind speed RUM rocket is a rocket used in the payload competition among university students. The rocket is designed to bring a maximum payload of 1 kg to altitude of 600-1000 m and falls safely on a 500 m radius of the left and right rear of the center point of the launching pad of the conditions of wind speeds below 10 knots. In extreme circumstances where the wind speed is above 10 knots, the effect of speed and direction of wind to the stability of the rocket flight direction large enough to cause it to fall beyond the defined safety radius. The research aims to adjust azimuth setting of the rocket so that the fall of the rocket motor remains secure within the radius of the launch area. The study was conducted by testing a rocket RUM in extreme conditions (wind speed of 10-20 knots) with variations in shear-pin and azimuth angle. The test variables are the position of the fallen rocket motor. The results show that the wind direction and speed significantly affecting direction of rockets flight. The results show that rocket azimuth angle of 60 degrees with the direction of 90 degrees from the wind direction can make thea rocket falls on a secure area (within 500 m). BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12348 10.30536/j.jtd.2016.v14.a2943 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 9-16 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12348/9658 Copyright (c) 2025 Heri Budi Wibowo, Ahmad Riyadl, Yudha Agung Nugroho https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12349 2025-10-03T07:30:30Z ijoa:ART

PENENTUAN BASIS OPERASI PADA SISTEM PEMANTAUAN MARITIM BERBASIS WAHANA TERBANG TAK BERAWAK Suseno, Prasetyo Ardi Probo Wirawan , Adi UAV pemantauan Maritim basis operasi Kluster Natuna Paper ini mendiskusikan metode untuk menentukan basis operasi pada pemantauan maritim yang menggunakan pesawat terbang tak berawak sebagai komponen utamanya. Penentuan basis operasi disusun berdasarkan data-data yang telah direkam oleh satelit radarsat 2. Dalam penelitian ini dipilih laut Natuna sebagai fokus wilayah karena laut Natuna merupakan salah satu laut di Indonesia yang paling rawan mengalami kegiatan penangkapan ikan illegal. Simulasi dilakukan menggunakan software MATLAB. Hasil simulasi yang dilakukan menunjukkan bahwa basis operasi dapat ditempatkan sedemikian rupa, sehingga dengan jumlah operasi yang minimal, seluruh daerah yang berpotensi kegiatan penangkapan ikan illegal masih dapat tercakup dalam wilayah operasi tersebut.   BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12349 10.30536/j.jtd.2018.v16.a3034 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 149-158 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12349/9657 Copyright (c) 2019 Prasetyo Ardi Probo Suseno, Adi Wirawan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12350 2025-10-03T07:30:30Z ijoa:ART

ANALISIS POTENSI STASIUN BUMI SATELIT LAPAN-TUBSAT KOTOTABANG UNTUK PENGAWASAN JALUR STRATEGIS SELAT MALAKA (THE POTENTIAL ANALYSIS OF LAPAN-TUBSAT SATELLITE GROUND STATION (KOTOTABANG) FOR OBSERVING THE STRATEGIC CHANNEL OF MALACCA STRAIT) Judianto, Chusnul Tri Kototabang ground station LAPAN-TUBSAT LAPAN-TUBSAT is the first generation of LAPAN satellite program which is developed by technology collaboration between LAPAN and TU Berlin, German. As a surveillance satellite, LAPAN-TUBSAT has ability to observe the earth surface until 5 meter ground resolution by using analog video camera. Utilization of this satellite to observe the strategic location entire Indonesia in real time has not been done thoroughly. Therefore the technical upgrading of the Ground Station in strategic areas such as border areas, the National/International cruise line and National vital objects should be improved. One of the strategic areas of Indonesia is the region of Malacca Strait which is the area of International shipping waterway and border of 4 countries; Indonesia, Malaysia, Singapura and Thailand. Until now, to observe the Malacca region was performed using Rancabungur/Rumpin ground station that have minimum coverage area. The Kototabang ground station is one of the strategic ground stations that cover the entire of Malacca regions which needs to be improved in maintenance and technical operation level. The potential value of Kototabang ground station will be elaborated technically in this paper. BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12350 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 13-23 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12350/9659 Copyright (c) 2012 Chusnul Tri Judianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12351 2025-10-03T07:30:30Z ijoa:ART

DEKOMPOSISI TERMAL PROPELAN KOMPOSIT BERBASIS AMONIUM PERKLORAT/HYDROXY TERMINATED POLYBUTADIENE (AP/HTPB) (THE THERMAL DECOMPOSITION ANALYSIS OF AMMONIUM PERCHLORATE/HYDROXYTERMINATED POLYBUTADIENE (AP/HTPB) COMPOSITE SOLID PROPELLANT) Dewi, Wiwiek Utami Ismah, Yulia Azatil Decomposition Propellants DTA TGA DTG Thermal decomposition process of AP/HTPB solid propellant type RUM, 450 and 1220 were investigated by DTG60 (Differential Thermogravimetric) with operational parameters: temperature 30 – 400oC, nitrogen flow rate 50 ml/min, and heating rate 2.5 C/min. Thermal decomposition analysis will be the first step of decomposition kinetics research in determining life time of the propellant. TGA curve of propellant RUM was found to be two staged meanwhile the thermal decomposition of propellant 450 and 1220 has become one staged. The DTA curve/thermogram of propellant RUM show the formation of intermediate product before full-length decomposition. Unlike propellant RUM, DTA curves of propellant 450 and 1220 do not show the formation of intermediate product. Decomposition process of propellant 450 and 1220 accelerate by Al presence. The difference between AP modal on propellant 450 and 1220 show insignificance effect to the amount of decomposition energy consumption. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12351 10.30536/j.jtd.2016.v14.a2944 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 17-24 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12351/9661 Copyright (c) 2025 Wiwiek Utami Dewi, Yulia Azatil Ismah https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12352 2025-10-03T07:30:30Z ijoa:ART

(AUTOMATIC IDENTIFICATION SYSTEM (AIS) SATELIT DATA CORRECTION USING INTERPOLATION AND EXTRAPOLATION METHODE, (Case Study : LAPAN-A2 and LAPAN-A3 Satellite)) Karim, Abdul Permala, Rizki Mukhayadi, M Hasbi , Wahyudi Nasional Institute Aerounautics and Space (LAPAN) has two satellites (LAPAN-A2 and LAPAN-A3) that are carry Automatic Identification System (AIS) sensors. It can be use for monitoring Indonesian maritime. The altitude of the satellite about 642 Km and 500 km so it has a wide area covered and receive big data. The problem is the AIS technology use the Time Division Multiple Access (TDMA) system that has limitations in handling big data so that some data received can be damaged due to collision. Therefore, in this research has been done the analysis and correction data using interpolation and extrapolation methods. The results  is improvements of valid data about 22,6 % for LAPAN-A2 satellite and 20,8 % for LAPAN-A3 satellite.   BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12352 10.30536/j.jtd.2018.v16.a3049 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 159-168 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12352/9660 Copyright (c) 2019 Abdul Karim, Rizki Permala, M Mukhayadi, Wahyudi Hasbi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12353 2025-10-03T07:30:30Z ijoa:ART

PENGEMBANGAN PERANGKAT LUNAK ANALISIS LINTAS TERBANG ROKET MULTI-STAGE (DEVELOPMENT OF TRAJECTORY ANALYSIS SOFTWARE FOR MULTI-STAGE ROCKET) Poetro, Ridanto Eko Jenie, Yazdi I Sasongko, Rianto Adhy Utama , Satriya Rocket Flight Trajectory Simulation This paper discusses the development of a computer software for simulating and analyzing flight trajectory of rocket systems. Many aspects may influence the trajectory, such as those related to the internal characteristic of the system, those representing external or environmental influence, and also the ones corresponding to the procedures of the launching and the operation during its flight. The software is developed based on the mathematical equations representing the balance of forces and moments occur during the flight of a rocket. Some conditions related to rocket internal characteristic variation, external perturbance, and flight procedure/operation are represented as parameters variations of the mathematical equations used for computing the rocket system attitude and movement variables. The software, developed using MATLAB/ SIMULINK application, is then used for simulating and analyzing the flight trajectory of a multi-stage rocket in some flight conditions. At this development stage, as the simulation results show, the software can perform its function quite well to compute the system variables during each of its flight phases and display the information required for further analysis. In future development, some validation tests still need to be accomplished for ensuring the accuracy and validity of the method used in this software. BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12353 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 24-36 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12353/9662 Copyright (c) 2012 Ridanto Eko Poetro, Yazdi I. Jenie, Rianto Adhy Sasongko, Satriya Utama https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12354 2025-10-03T07:30:30Z ijoa:ART

APLIKASI CFD DALAM PENENTUAN PERFORMA MESIN TURBOFAN MODEL CFM56-5B YANG MENGALAMI CACAT PADA KIPAS UNTUK KEPUTUSAN MAINTENANCE Wuwung, Vicky Wandani, Puspa Bintoro , Carolus Bilah kipas CFM56-5B Kerusakan dent CFD Numeca Efisiensi Kipas Performa mesin Penelitian ini membahas mengenai kajian kerusakan yang terjadi pada bilah kipas mesin turbofan CFM56-5B. Kerusakan tersebut memerlukan adanya sebuah keputusan maintenance, apakah bilah kipas tersebut masih layak digunakan ataukah perlu di repair atau diganti. Meskipun regulasi menetapkan bahwa kerusakan tersebut masih dapat diterima, namun perlu ditinjau dari segi performanya, apakah kipas masih dapat memberikan performa yang baik atau tidak. Kajian dilakukan dengan menyimulasikan model bilah kipas CFM56-5B pada kondisi baik dan cacat pada perangkat lunak CFD-Numeca di kondisi take-off dan cruise. Cacat pada bilah berupa dent dengan kedalaman 0.069†dan terletak seragam di semua bilah pada 70% span bilah di bagian leading edge sebagai simulasi kerusakan akibat adanya bird strike. Simulasi numerik dilakukan dengan kondisi pemodelan aliran steady, dan menggunakan model turbulen Spallart-Allmaras. Hasil simulasi numerik menunjukkan adanya penurunan performa mesin pada Thrust di kondisi take-off sebesar 14% dan penurunan efisiensi sebesar 16%, sedangkan pada kondisi cruise, penurunan Thrust dan efisiensi berturut-turut adalah sebesar 55%, dan 54%. Penurunan Thrust pada saat take-off berdasarkan regulasi AC 25-13 adalah aman dan tidak perlu dilakukan repair atau replacement. Namun, meskipun aman, mesin akan boros bahan bakar ketika berada dalam kondisi cruise sehingga perlu dilakukan repair atau replacement. Penentuan keputusan maintenance jika didasarkan pada regulasi AC 25-13 pada akhirnya adalah tidak diperlukannya repair atau replacement pada bilah kipas. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12354 10.30536/j.jtd.2016.v14.a2945 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 25-36 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12354/9664 Copyright (c) 2025 Vicky Wuwung, Puspa Wandani, Carolus Bintoro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12355 2025-10-03T07:30:30Z ijoa:ART

RAIM DALAM RANGKA MENDUKUNG IMPLEMENTASI SISTEM NAVIGASI PENERBANGAN BERBASISKAN SATELIT DI INDONESIA (RAIM IN THE IMPLEMENTATION OF SATELLITE BASED NAVIGATION IN INDONESIAN AIR TRAFFIC MANAGEMENT) Septiawan, Reza Septiawan Sutedjo, Bayu Sarotama , Afrias Air navigation system GPS Receiver Autonomous Integrity Monitoring (RAIM) is a method to monitor the integrity of GPS using mesurement to redundant satellites on the receiver side. Comonly 2 algorithm are used to perform RAIM, i.e. snapshot method and sequential method. In snapshot method, single set measurement of GPS signal is used, meanwhile in sequential method several sets of measurements (past and current) GPS signal are used. Therefore, the sequential method has the capacity to detect position failure due to low fault to noise ratio. The low fault to noise ratio is mostly caused by the satellite’s position at the time of position measurement. RAIM is very useful for GPS users to be able to determine the whether the GPS can give accurate position, based on its satellite’s positions, satellite’s service life or error in the receivers. Such accuracy is important especially for the use in GPS navigation sistem in Air Traffic Management (ATM). The disturbance can also be caused by ionosfer condition. In order to support the use of GPS navigation system in ATM in Indonesia, Communication Navigation Surveillance-ATM (GPS CNS-ATM) team of BPPT perform simply RAIM asessment that can be informed to the flightcrew or Air Traffic Center, to be informed via Notice To Air Men (NOTAM). The GPS signal observation is done in 5 different locations in Indonesia. BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12355 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 37-49 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12355/9663 Copyright (c) 2012 Reza Septiawan, Bayu Sutedjo, Afrias Sarotama https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12356 2025-10-03T07:30:30Z ijoa:ART

PENGARUH GANGGUAN LINGKUNGAN ANTARIKSA PADA SISTEM ELEKTRONIK LAPAN-TUBSAT (EFFECT OF SPACE ENVIRONMENT DISTURBANCE IN LAPAN-TUBSAT SATELLITE) Najati, Nayla SEL LAPAN-TUBSAT Real time telemetry Long time telemetry PCDH LAPAN-TUBSAT has been operated more than five years. During the operation, LAPAN-TUBSAT faces several anomaly. It could be observed by using real time telemetry and long time telemetry. When and where an anomaly appeared can be detected with long time telemetry. Anomaly event on LAPAN-TUBSAT’s PCDH is caused by Single Event Latch-Up (SEL) that happen in scale of weeks.These conditions required LAPAN-TUBSAT operators to take action in order to make LAPAN-TUBSAT back to normal operation. This paper describes statistic of SEL that occur in LAPAN-TUBSAT. Almost 70% of SEL event take place at South Atlantic Anomaly (SAA) and the rest at polar. BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12356 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 50-52 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12356/9665 Copyright (c) 2012 Nayla Najati https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12357 2025-10-03T07:30:30Z ijoa:ART

FINITE ELEMENT MODELING OF LAPAN-A5/CHIBASAT DEPLOYABLE SOLAR PANEL COMPOSITE PLATE Triharjjanto, Robertus Heru Budiantoro, Poki Agung LAPAN-A5/ChibaSat, that will carry synthetic aperture radar payload, requires a lot more power generation capacity, compared to its predecessor. Therefore, its solar panel will be deployed in orbit to ensure maximum sun exposure. Since the deployable system requires solar panel plate that lightweight and strong, honeycomb composite material is selected. The selection of such material requires special treatment in the satellite structural stiffness calculation. The objective of the research is to find simple stiffness model of the plate, so that later it can be integrated with the total satellite structural model and used by launch authority in its total vehicle modal analysis. The modeling used finite element software, and the simplified honeycomb model is validated using standar plate stiffnes problem. After model validation, the boundary condition as in the LAPAN-A5/ChibaSat deployable system is imposed. The result shows that the stiffness of the deployable solar panel plate has met the launch requirement of PSLV’s auxiliary payload. Therefore, the design mode can be used in the development of LAPAN-A5/ChibaSat.   BRIN Publishing 2019-04-25 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12357 10.30536/j.jtd.2018.v16.a3065 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara; 169-175 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12357/9666 Copyright (c) 2019 Robertus Heru Triharjjanto, Poki Agung Budiantoro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12358 2025-10-03T07:30:30Z ijoa:ART

PENINGKATAN KUALITAS FOKUS CITRA IMAGER MULTISPEKTRAL SATELIT LAPAN-A3 (IMAGE-FOCUSING QUALITY IMPROVEMENT ON LAPAN-A3 SATELLITE MULTISPECTRAL IMAGER) Tahir, Andi Mukhtar Hakim, Patria Rachman Syafruddin, A. Hadi Imager multispektral Fokus citra Modulation transfer function Satelit LAPAN-A3 membawa imager multispektral sebagai muatan utama, yang memiliki empat kanal warna yaitu merah, hijau, biru, dan near-infrared. Sistem optik imager dirancang dengan menggunakan beam-splitter yang akan membagi cahaya yang melewati sistem lensa menuju detektor masing-masing kanal warna. Karena setiap detektor memiliki posisi dan juga orientasi yang berbeda terhadap pusat lensa, maka akan terjadi ketidakseragaman derajat kefokusan untuk setiap citra yang dihasilkan oleh masing-masing kanal warna, yang dapat mengurangi kualitas citra komposit yang dihasilkan. Penelitian ini bertujuan untuk meningkatkan kualitas citra komposit imager multispektral satelit LAPAN-A3 dengan cara memastikan agar setiap kanal warna akan menghasilkan citra dengan derajat kefokusan yang seragam. Metode yang digunakan yaitu dengan mengambil sejumlah data pengamatan terhadap obyek dengan pola geometri zebra-cross, dan kemudian diolah dengan menggunakan perangkat lunak Imatest. Penentuan kualitas fokus citra dilakukan dengan mengukur Modulation Transfer Function (MTF) pada frekuensi spasial tertentu. Berdasarkan sejumlah pengamatan dan perhitungan yang dilakukan, derajat kefokusan citra yang dihasilkan masing-masing detektor dapat diseragamkan dengan mengatur jarak detektor tersebut terhadap pusat lensa. Selain itu, percobaan yang dilakukan juga dapat mengurangi distorsi ko-registrasi kanal yang terjadi pada sumbu horisontal. Kedua hasil tersebut secara signifikan dapat meningkatkan kualitas citra imager multispektral satelit LAPAN-A3, terutama dalam aspek geometri. Hasil penelitian ini diharapkan dapat digunakan sebagai panduan dalam proses operasional satelit LAPAN-A3 selanjutnya dan juga dapat mendukung pengembangan imager multispektral eksperimen yang sedang dikembangkan untuk satelit LAPAN-A4. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12358 10.30536/j.jtd.2016.v14.a2946 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 37-50 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12358/9668 Copyright (c) 2025 Andi Mukhtar Tahir, Patria Rachman Hakim, A. Hadi Syafruddin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12359 2025-10-03T07:30:30Z ijoa:ART

METODE KALIBRASI RADAR TRANSPONDER ROKET MENGGUNAKAN DATA GPS (CALIBRATION METHOD OF RADAR TRANSPONDER FOR ROCKET USING GPS DATA) Widada, Wahyu Radar transponder GPS Google-earth Calibration method This paper discusses the method of calibration of radar transponders for the rocket launch applications using GPS data. Calibration is performed by measuring the distance of two positions with GPS data and used as a reference for the calibration range radar transponder. Transponder is placed on the measured position and the radar transceiver is placed in a position of radar base station. The obtained results shows that the calibration method is very easy to do, reference to a longer distance can improve the accuracy result of the calibration. We obtained a calibration factor value for the radar system used in the experiment is 0.9275..Keywords: Radar transponder, GPS, Google-earth, Calibration method BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12359 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 57-62 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12359/9667 Copyright (c) 2012 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12360 2025-10-03T07:30:30Z ijoa:ART

RANCANG BANGUN PLATFORM GYMBAL UNTUK PAYLOAD UAV (DEVELOPMENT OF PLATFORM GYMBAL FOR UAV PAYLOAD) Prabowo, Gunawan S Gymbal IMU Servo Surveillance Have been developing a platform gymbal sistem, this work beginning from conceptual desain, preliminary design, trade off component, and continued with critically design, analysis and integration in the laboratory. Also integration with kamera sistem for surveillance mission. This platform have designed to maintenance in Z direction axes. IMU is used for provide reference of airframe and servo as a actuator.In the parsial test, the eror in each axes is about 0,6º. BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12360 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 63-70 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12360/9669 Copyright (c) 2012 Gunawan S. Prabowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12361 2025-10-03T07:30:30Z ijoa:ART

RETIKULASI HIDROXYL TERMINATED POLUBUTADIENE (HTPB) MANDIRI DENGAN TOLUENE DIISOCIANATE (TDI) MEMBENTUK POLIURETAN SEBAGAI FUEL BINDER PROPELAN Rosita , Geni HTPB TDI gel time propelan fuel-binder LAPAN telah berhasil membuat HTPB secara mandiri. Tahapan berikutnya adalah melakukan pembuatan fuel binder dengan mereaksikan HTPB mandiri tersebut dengan TDI. Tahapan uji ini untuk mendapatkan gel time dan kekerasan yang dapat memenuhi syarat sebagai binder propelan. Pada penelitian ini dilakukan reaksi HTPB : TDI pada beberapa perbandingan, dan HTPB yang direaksikan berbeda pada viskositas dan berat molekul reratanya. Dari beberapa komposisi hasil reaksi, yang dapat digunakan sebagai fuel binder propelan adalah yang memenuhi beberapa kriteria, antara lain tidak ada gelembung udara, elastis, tidak lengket untuk memudahkan pencetakan, tidak keras dan tidak getas supaya propelan tidak mudah retak. Hasil pengamatan selama gel time, yang dapat digunakan sebagai fuel binder propelan adalah komposisi HTPB:TDI, 6:1, 7:1, 8:1 dan 9:1. Dengan demikian maka HTPB mandiri yang dikembangkan sudah dapat digunakan sebagai fuel binder pada pembuatan propelan komposit. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12361 10.30536/j.jtd.2016.v14.a2947 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 51-60 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12361/9671 Copyright (c) 2025 Geni Rosita https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12362 2025-10-03T07:30:30Z ijoa:FP

Full Paper JTD Vol. 16 No.2 Desember 2018 Jurnal, Redaksi - BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12362 Indonesian Journal of Aerospace; Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12362/9670 Copyright (c) 2020 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12363 2025-10-03T07:30:30Z ijoa:ART

PENDEKATAN BARU PEMETAAN BATHIMETRIC MENGGUNAKAN DATA PENGINDERAAN JAUH SPOT STUDI KASUS: TELUK PERIGI DAN TELUK POPOH (THE NEW APPROACH TO MAPPING BATHIMETRIC USING SPOT REMOTE SENSING DATA CASE STUDY: THE BAY AND POPOH GULF) Arief, Muchlisin Bathymetric SPOT Isobaths Shallow water depth correlation Bathymetric mapping derived from remote sensing have been carried out researchers, in order to determine the depth of the shallow waters especially sallow water depth. Bathymetric relief map shows the earth/terrain depicted by contour lines is called the isobath. Usually bathymetric determination using exponential function of depth. While in this paper described a new approach to calculate the depth of seawater derived from SPOT-4 satellite data using empirical formulas functions of logarithmic or quadratic equation built through correlasi the depth map obtained from DIHIDROS (Navy) with Digital Number or the reflectance values of SPOT band-1. This experience has been tested at Perigi bay in Trenggalek district and Popoh bay in Tulung Agung district. Based on the calculations, the spread of sallow water depth on Perigi and popoh bay about 5 – 70 meters. BRIN Publishing 2012-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12363 Indonesian Journal of Aerospace; Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara; 71-80 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12363/9672 Copyright (c) 2012 Muchlisin Arief https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12364 2025-10-03T07:30:30Z ijoa:ART

KAJIAN EKSPERIMENTAL TENSILE PROPERTIES KOMPOSIT POLIESTER BERPENGUAT SERAT KARBON SEARAH HASIL MANUFAKTUR VACUUM INFUSION SEBAGAI MATERIAL STRUKTUR LSU Abdurohman, Kosim Marta , Aryandi VARTM Tensile strength Modulus elastisitas Failure mode Vacuum infusion merupakan salah satu metode manufaktur yang digunakan untuk meningkatkan sifat mekanik komposit. Untuk mengaplikasikan metode ini dalam pembuatan struktur LAPAN Surveillance UAV (LSU), perlu diketahui terlebih dahulu sifat mekanik dari komposit hasil metode ini secara eksperimen. Salah satu eksperimen yang dilakukan yaitu pengujian tarik untuk mendapatkan tensile strength, modulus elastisitas, dan failure mode yang terjadi pada komposit. Eksperimen dilakukan terhadap komposit CFRP menggunakan material serat karbon searah (UD) 0â° dan matriks poliester dibuat dengan metode vacuum infusion mulai dari tahap preparasi sampai tahap pengujian. Dari hasil manufaktur didapat nilai densitas dan ketebalan komposit serta fraksi massa dan fraksi volume material penyusun komposit. Spesimen dan proses pengujian mengikuti standar ASTM D3039 yang merupakan standar pengujian tarik untuk komposit dengan matriks polimer. Hasil pengujian menunjukkan nilai ultimate tensile strength 1011,67 MPa, modulus elastisitas 59074,96 MPa, dan failure mode SGV (Long Spliting, Gage, Various). BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12364 10.30536/j.jtd.2016.v14.a2948 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 61-72 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12364/9674 Copyright (c) 2025 Kosim Abdurohman, Aryandi Marta https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12365 2025-10-03T07:30:30Z ijoa:FP

Front Pages JTD Vol 18 no.1 Juni 2020 Jurnal, Redaksi - BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12365 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12365/9673 Copyright (c) 2020 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12366 2025-10-03T07:30:30Z ijoa:ART

SIMULASI KINERJA FORWARD ERROR CONTROL CODING UNTUK SATELIT MIKRO PENGINDERAAN JARAK JAUH Dwiyanto Sugihartono Reed Solomon QPSK 16-QAM Remote sensing Micro satellite application for remote sensing in this time has been expanded and particularly supported by growth of electronics component that low power and small size. Large amount of image data, less of contact time and limited satellite’s power obliges of efficiency mechanism design to assured data satellite communication is accepted properly by earth station. Various of scenario of data transmissions on micro satellite have been developed in order to ensure all data that taken by payload can be delivered and accepted by station earth truly. Forward Error Control Coding or Forward Error Correction method is mechanism that added redundancy bit to delivery data with a purpose to improve error correction of received data. FEC performance can be known by compare of different value of Eb/N0 needed for Bit Error Rate (BER) in common without FEC. In this research conducted simulation performance FEC Reed Solomon by undertaking change of beet amount per symbol, code length and code ability in repairing symbol error. Simulation Result shows getting smaller code rate that used then ever greater code reinforcement. The simulation using forward error control coding Reed Solomon for data transmission remote sensing results code RS(255,223) have best performance with coderate 0,874 and coding gain 3,4dB on value of BER 10-4. BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12366 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 82-92 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12366/9675 Copyright (c) 2012 Dwiyanto, Sugihartono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12367 2025-10-03T07:30:30Z ijoa:ART

ANALISIS KANDUNGAN ALUMINIUM POWDER PROPELAN BERDASAR ENERGI PEMBAKARAN DARI BOMB KALORIMETER (ANALYSIS OF PROPELLANT’S ALUMINUM POWDER CONTENT BASED ON BURNING ENERGY FROM BOMB CALORIMETER) Hartaya, Kendra Analisis Propelan Aluminium Kalorimeter bom Telah dilakukan analisis hasil penelitian propelan dengan variabel kandungan aluminium terhadap hasil energi pembakaran. Pengukuran besarnya energi pembakaran propelan dilakukan dengan bomb calorimeter. Sampel propelan dibuat dengan mencampur HTPB dan aluminium selama 15 emnit dilanjutkan pencampuran dengan AP halus selama 20 menit, lalu dengan AP kasar selama 50 mrnit. Setelah pengadukan berakhir maka ditambahkan TDI dan diaduk selama 15 menit. Kandungan Al di variasi dari 8% hingga 18%. Energi pembakaran yang dihasilkan adalah 2885 kal/gr hingga 3750 kal/gr. Pada 18% Al energi pembakaran mulai menurun. Penurunan ini diakibatkan oleh sebagian besar sampel yang terbakar sama dengan sampel yang mengalami erosiv. BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12367 10.30536/j.jtd.2016.v14.a2949 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara; 73-80 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12367/9676 Copyright (c) 2025 Kendra Hartaya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12368 2025-10-03T07:30:30Z ijoa:ART

ANALISIS POSISI ANTENA AIS UNTUK MISI PEMANTAUAN KAPAL SATELIT SAR MIKRO LAPAN Dwiyanto, Dwiyanto Jayani, Ade Putri Septi AIS Antena SAR SNR coverage AIS merupakan sistem pengatur lalu lintas kapal dimana sistem ini mengenali dan menentukan lokasi kapal melalui pertukaran data dengan kapal atau stasiun VTS terdekat. Informasi yang berupa identitas kapal, posisi, arah kapal, dan kecepatan dapat ditampilkan dalam layar atau melalui sebuah Electronic Chart Display and Information System (ECDIS). AIS dimaksudkan untuk membantu awak kapal untuk memantau dan memungkinkan otoritas maritim melacak dan memantau pergerakkan kapal. Tren aplikasi penggunaan data AIS saat ini semakin berkembang dengan dipasangnya receiver AIS di satelit.  keuntungan pemasangan receiver di satelit adalah mempunyai cakupan wilayah yang luas juga bisa memantau kapal dimana satelit mengorbit. Kombinasi komplemen data AIS dan data SAR dari satelit saat ini semakin menjadi pilihan untuk memantau kejahatan kelautan secara kontinue dan dalam wilayah yang luas seperti Indonesia. Penelitian ini dilakukan untuk menganalisis penempatan antena AIS satelit. Penelitian dilakukan dengan melakukan simulasi antena yang digunakan dan menganalisis Signal to Noise Ratio (SNR) sinyal dari masing masing posisi didapatkan posisi yang optimal. Pertimbangan yang dilakukan untuk menentukan posisi adalah dari luasan dan bentuk coverage AIS serta pertimbangan kemudahan digabungkan dengan data SAR. Hasil simulasi dan perhitungan yang dilakukan penempatan antena pada sumbu Y satelit menjadi pilihan yang optimal untuk digunakan dalam satelit SAR. pada posisi antena ini antena memeiliki coverahe yang lumayan sempit tapi memanjang searah sumbu Y. Pada posisi ini coverage AIS juga sebidang dengan coverage SAR sehingga waktu diterimanya data AIS dari kapal sama dengan saat kapal terdeteksi oleh sapuan SAR. BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12368 10.30536/j.jtd.2020.v18.a3153 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara; 1-14 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12368/9678 Copyright (c) 2020 Dwiyanto, Ade Putri Septi Jayani https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12369 2025-10-03T07:30:30Z ijoa:ART

PEMBUATAN DAN ANALISIS KINERJA SISTEM THERMAL INSULATION PADA MOTOR ROKET YANG MENGGUNAKAN PROPELAN CASE-BONDED Sutrisno Liner Free standing Case-bonded Liner material of case-bonded propellant rocket motor have been made by adding some filler to the liner material composition used in free standing rocket motor. The liner was manufactured by spinning method to the rocket motor tube. The case-bonded liner performance in radial burning rocket motor was analyzed using material characteristic test result combined with rocket motor burning mechanism and free standing rocket motor static test result. The case-bonded liner materials are superior to the free standing liner because it is lighter (18,94%) and have higher heat resistance (6,75%). The application of case-bonded liner for radial burning rocket motor using single configuration propellant will be safe because the heat of propellant combustion passed through the isolator materials beforethe rocket motor tube. Based on the analysis it is found that the case-bonded liner can be recommended to the radial burning rocket motor using single configuration propellant.  BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12369 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 93-101 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12369/9679 Copyright (c) 2012 Sutrisno https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12370 2025-10-03T07:30:30Z ijoa:BP

Back Pages Vol 14 No 1 Juni 2016 Tekgan, Redaksi Jurnal - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12370 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12370/9677 Copyright (c) 2025 Redaksi Jurnal Tekgan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12371 2025-10-03T07:30:31Z ijoa:FUP

Full Pages JTD Vol 14 No 1 Juni 2016 Jurnal , Redaksi - BRIN Publishing 2025-07-07 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12371 Indonesian Journal of Aerospace; Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12371/9680 Copyright (c) 2025 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12372 2025-10-03T07:30:31Z ijoa:ART

ANALISA PEMILIHAN BENTUK VORTEX GENERATOR UNTUK SAYAP PESAWAT LSU-05 MENGGUNAKAN METODE NUMERIK Herdiana, Dana Hartono, Firman Telah dilakukan pengujian perdana dari pesawat LSU-05 buatan LAPAN dimana hasil evaluasi pengujian terdapat kekurangan yaitu pada saat pesawat melakukan manuver, hal tersebut diakibatkan oleh beberapa faktor. Salah satu faktor adalah kurangnya koefisien gaya angkat maksimum. Untuk mengatasi hal tersebut maka ada beberapa solusi yang dapat mengatasi hal tersebut. Salah satunya yaitu dengan penambahan komponen pada sayap yaitu vortex generator. Metode yang digunakan untuk penelitian ini adalah metode numerik yaitu mensimulasikan penambahan vortex generator pada sayap dengan berbagai varian bentuk dan posisi pemasangan dari vortex generator menggunakan CFD (Computational Fluid Dynamic). Model yang disimulasikan adalah model sayap saja dan sayap dengan vortex generator. Bentuk yang dipilih untuk vortex generator adalah rectangular, triangular, dan gothic (mod) serta posisi pasang mulai dari 15 %, 20 %, dan 25 % dari panjang chord. Dari hasil yang diperoleh bentuk triangular memiliki nilai CLmax yang lebih besar dibanding bentuk rectangular dan gothic (mod) yaitu 1.4553 dan posisi pasang yang memiliki CLmax yang lebih besar yaitu di posisi pasang 20%. Bentuk vortex generator yang cocok dipasang pada sayap pesawat LSU-05 adalah bentuk triangular di posisi pasang 20%.   BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12372 10.30536/j.jtd.2020.v18.a3211 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara; 15-29 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12372/9681 Copyright (c) 2020 Dana Herdiana, Firman Hartono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12373 2025-10-03T07:30:31Z ijoa:ART

PERHITUNGAN DAN PERANCANGAN IGNITER BERBASIS KALKULASI PROPULSI ROKET (Studi Kasus Roket RX-320) Samosir, Ganda Extreme conditions Internal factor External factors The solid rocket motors, like all the LAPAN’s rocket, has been using the composite fuel of Hydroxyl Terminated Poly Butadiene (HTPB) type which is not easy to self-igniting. The quite extreme environment conditions are needed in order to ignite this non-hypergolic solid fuel, such as the ambiance pressure and temperature must be about 40 bar and 280°C respectively. The aforementioned conditions must be well given by the prime igniter designed or commonly known as igniter. The performance of an igniter could be very influenced by 2 (two) massive variables; first one is the internal factor, such as: squib ingredient, filament material, primer composition, igniter main charge, and the second one is external factor, such as: propellant’s type, dimension and the configuration of the rocket’s combustion chamber. In other word, chosen the proper rocket’s igniter are depending on the type and its mission.The propulsion calculation applied in this paper to design the igniter of the rocket RX-320, gives some major variables, i.e.: the biggest tube length; = 357 mm, its outside diameter; = 51 mm, total orifices and its diameter are 165 and 4 mm respectively. BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12373 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 102-113 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12373/9682 Copyright (c) 2012 Ganda Samosir https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12374 2025-10-03T07:30:31Z ijoa:ART

KALIBRASI RADIOMETRI VICARIOUS KAMERA MULTISPEKTRAL SATELIT LAPAN-A3/IPB DI WILAYAH BUKIT JADDIH MADURA Salaswati, Sartika Hakim, Patria Rachman Syafrudin, A Hadi Hartono, Rommy Utama, Satriya Herawan, Agus Yatim, Rakhmat Ardinal, Rifki Pamadi, Bambang Sigit Satelit LAPAN-A3/IPB merupakan satelit mikro eksperimental yang memiliki misi penginderaan jauh sebagai salah satu misi utamanya. Dalam melaksanakan misi penginderaan jauh tersebut, satelit LAPAN-A3/IPB dilengkapi dengan muatan utama berupa kamera multispektral empat kanal (merah-hijau-biru-inframerah dekat) jenis pencitraan pushbroom dengan resolusi spasial 15 meter dan lebar sapuan 120 km serta resolusi radiometri 16 bit dan resolusi temporal 21 hari. Untuk menghasilkan data citra pengamatan yang memiliki kualitas standar setiap saat, salah satu kalibrasi yang harus dilakukan adalah kalibrasi radiometri vicarious yang dilakukan setelah satelit mengorbit. Penelitian ini menganalisis hasil kalibrasi radiometri vicarious untuk kamera multispektral satelit LAPAN-A3/IPB di wilayah bukit Jaddih Madura yang telah dilakukan pada tahun 2018 lalu. Dengan membandingkan data citra observasi yang dihasilkan satelit dan data radiansi hasil pengukuran lapangan dengan menggunakan spektrometer, diperoleh koefisien radiansi yang menyatakan hubungan antara data digital number citra kamera multispektral dengan data radiansi sensor ToA (Top-of-Atmosphere). Analisis yang telah dilakukan menunjukkan bahwa koefisien radiansi yang dihasilkan kalibrasi radiometri vicarious di bukit Jaddih Madura tidak berbeda jauh dengan koefisien radiansi yang dihasilkan pada beberapa kalibrasi radiometri vicarious sebelumnya. Analisis temporal juga menunjukkan bahwa koefisien radiansi yang dihasilkan dengan menggunakan data observasi bukit Jaddih pada periode waktu lainnya juga menghasilkan nilai koefisien radiansi yang sama. Hasil ini menunjukkan bahwa hasil kalibrasi radiometri vicarious yang dihasilkan cukup akurat. Walaupun demikian, akurasi kalibrasi radiometri vicarious yang dilakukan dapat ditingkatkan dengan menggunakan data atmosfer yang dihasilkan sensor sunfotometer. BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12374 10.30536/j.jtd.2020.v18.a3212 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara; 31-42 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12374/9685 Copyright (c) 2020 Sartika Salaswati, Patria Rachman Hakim, A Hadi Syafrudin, Rommy Hartono, Satriya Utama, Agus Herawan, Rakhmat Yatim, Rifki Ardinal, Bambang Sigit Pamadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12375 2025-10-03T07:30:31Z ijoa:ART

PERHITUNGAN DAN ANALISIS LOSSES, DIAMETER EFEKTIF ROTOR, DAN PENYERAPAN DAYA DAN ENERGI PADA DIFFUSER AUGMENTED WIND TURBINE (DAWT) Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Wind turbine DAWT Electrical energy Losses The use of diffuser in wind turbine (DAWT) is aimed at increasing the effective speed to produce a higher power. A bigger and heavier turbine results in difficulty in manufacturing the turbine orientation system. This research consists of three parts i.e. the calculation and analysis of the losses, determination of the effective diameter of the rotor, and the calculation and analysis of the absorbed energy by DAWT. The losses calculation and analysis is based on the friction between the airflow and wall. The diameter of the rotor is choosen in the diffuser area which has minimum turbulence flow produced by the wind angle. The calculation and analysis of the power is based on its rotor diameter. Then the power converted to become energy. In this research, DAWT is assumed to have no orientation system so that easily manufactured, i.e. the rotor is oriented at a single direction. Wind direction and frequency is selected in three configurations. In the first configuration, the wind direction comes from all the twelve wind source direction with the same frequency in the 24 hour period, producing 2 hourly periods for every wind direction. In the second configuration, wind from 90° and 270° or perpendicular to the axial turbine axes are eliminated, and hence producing 10 different wind directions at 2.4 hourly periods. In the third configuration, the turbine is set at the beach whereby the wind direction comes only at two direction; the sea and land wind directions. At these conditions, the wind is assumed to come at 0°, 30°, 150°, 180°, 210°, and 330°. The aim of this research is to calculate the energy absorption of the wind rotor, and comparing with those produced without the diffuser system in place. In this research, a 2m rotor diameter and 4m diffuser diameter is selected, power coefficient of 0.3, wind speed of 5m/sec, and these parameters are constant for the 24 period under analysis. The result of the calculation shows that there are losses near wall especially for high wind angle. The rotor diameter have chossen about 1,940 m. The energy absorption of the wind rotor without the diffuser is 6.231 kJ. The energy absorption values for the 1st, 2nd and 3rd configuration with the diffuser produce 54.361, 65.234, and 101.316 kJ respectively. It shows that the use of diffuser in the wind rotor could produce an increase of up to 9 to 16 times in the power absorption of the rotor. BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12375 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 114-123 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12375/9683 Copyright (c) 2012 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12376 2025-10-03T07:30:31Z ijoa:FP

Front Page JTD Vol. 13 No. 2 Desember 2015 Jurnal, seketariat Redaksi - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12376 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12376/9684 Copyright (c) 2025 seketariat Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12377 2025-10-03T07:30:31Z ijoa:ART

METODE DOUBLE EXPONENTIAL SMOOTHING UNTUK ESTIMASI POSISI ROKET MENGGUNAKAN RADAR TRANSPONDER (DOUBLE EXPONENTIAL SMOOTHING METHODS FOR ESTIMATING POSITION ROCKET USING RADAR TRANSPONDER) Widada , Wahyu estimasi posisi radar transponder double exponential smoothing Data posisi sistem radar transponder masih mengandung derau signal, oleh karena itu perlu memproses algoritma estimasi dan digunakan untuk mengetahui posisi waktu berikutnya. Tulisan ini membahas estimasi posisi roket dari hasil pengukuran radar transponder dengan menggunakan metode double exponential smoothing. Metode ini diimplementasikan pada hasil pengukuran radar transponder uji terbang roket RX122. Hasil eksperimen menunjukkan bahwa posisi roket dapat diestimasi menjadi lebih akurat dengan analisa nilai Root Mean Square Error (RMSE) sebesar 0,67 dan nilai tersebut sekitar 2,2 kali lebih kecil. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12377 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 95-101 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12377/9686 Copyright (c) 2025 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12378 2025-10-03T07:30:31Z ijoa:ART

KRISTALISASI AMMONIUM PERKLORAT (AP) DENGAN SISTEM PENDINGINAN TERKONTROL UNTUK MENGHASILKAN KRISTAL BERBENTUK BULAT Pinalia, Anita Ammonium perchlorate Crystallization Rounded crystal AP is the solid particles with the largest composition in compossite propellant, with fractions 60-80%. Rounded particles of AP indirectly gives better performance of propellant. Therefore we need experiment the crystallization process to produce rounded AP crystal. In this experiment, crystallization was conducted by using a controlled cooling system. Cooling is done through two stages and using a different coolant. The first stage of slow cooling using water (30°C), and continued rapid cooling with ethylene glycol (-27°C). These experiment generate 45.45 kg AP with a purity 99.67%, 40 mesh crystal size, crystal shape close to round, yield 39.71%. BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12378 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 124-132 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12378/9687 Copyright (c) 2012 Anita Pinalia https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12379 2025-10-03T07:30:31Z ijoa:ART

PERHITUNGAN FAILURE INDEX STRUKTUR SAYAP PESAWAT TERBANG TANPA AWAK Ai-X1 DENGAN MENGGUNAKAN KRITERIA TSAI-HILL DISIMULASIKAN DENGAN METODE ELEMEN HINGGA Iryani, Lenny Wibowo, Singgih Satrio pesawat terbang tanpa awak material komposit Tsai-Hill failure index Untuk mengetahui kekuatan struktur suatu pesawat terbang, dilakukan perhitungan dan analisis kekuatan struktur. Struktur sayap pesawat terbang yang disusun dari material komposit, penghitungan dan analisis kekuatan struktur salah satunya dilakukan dengan menghitung failure index untuk masing-masing layer/susunan dari material komposit tersebut. Pada penelitian ini, struktur sayap Pesawat terbang tanpa awak (PTTA) Ai-X1 yang terbuat dari material komposit dianalisis kekuatan strukturnya dengan menghitung failure index dari masing-masing layer/susunan material komposit tersebut. Perhitungan failure index dilakukan dengan menggunakan kriteria kegagalan Tsai-Hill. Hasil dari penelitian ini yaitu nilai failure index pada masing-masing layer/susunan material komposit struktur sayap pesawat Ai-X1. Berdasarkan kriteria Tsai-Hill masing-masing layer/susunan tersebut menunjukkan tidak adanya keretakan pada lamina.   BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12379 10.30536/j.jtd.2020.v18.a3228 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara; 43-51 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12379/9688 Copyright (c) 2020 Lenny Iryani, Singgih Satrio Wibowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12380 2025-10-03T07:30:31Z ijoa:ART

PENGARUH GUGUS HIDROKSIL SEKUNDER TERHADAP SIFAT MEKANIK POLIURETAN BERBASIS HTPB (HYDROXY TERMINATED POLYBUTADIENE) (EFFECT OF SECONDARY HYDROXYL GROUPS ON MECHANICAL PROPERTIES OF POLYURETHANE BASE HTPB (HYDROXY TERMINATED POLYBUTADIENE)) Wibowo , Heri Budi HTPB Hidroksil sekunder Kontrol kualitas Propelan Beberapa pengujian terhadap propelan komposit menunjukkan bahwa parameter dasar kontrol kualitas HTPB seperti struktur ikatan, bilangan hidroksil, panjang rantai, dan fungsionalitas tidak dapat memberikan kepastian karakteristik mekaniknya. Berdasarkan mekanisme pembentukannya secara radikal, maka dapat diperoleh struktur HTPB dengan gugus hidroksil terikat posisi primer dan sekunder. Perbedaan gugus hidroksil akan memberikan kestabilan yang berbeda sehingga akan mempengaruhi reaktifitas pembentukan poliuretan. Penelitian bertujuan untuk mempelajari pengaruh adanya gugus hidroksil sekunder terhadap sifat mekanik poliuretan berbasis HTPB. Penelitian dilakukan dengan membuat poliuretan dari HTPB dan toluene diisocyanate (TDI) dengan perbandingan NCO/OH adalah satu, dengan menggunakan variasi bilangan OH sekunder dan primer. HTPB dan TDI dicampur dalam autoklaf pada suhu 45â°C selama 1 jam dalam kondisi hampa udara, kemudian diperam selama satu minggu pada suhu kamar. Hasilnya diuji sifat mekaniknya meliputi kuat tarik dan elongasi dengan peralatan tensilometer L-200. Hasil analisis menunjukkan bahwa pengaruh adanya gugus hidroksil sekunder terhadap sifat mekanik poliuretan adalah positif dan signifikan. Adanya gugus hidroksil sekunder mengurangi kuat mekanik dari poliuretan. Parameter gugus hidroksil sekunder tidak dapat diabaikan sebagai parameter dasar kontrol kualitas HTPB. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12380 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 103-111 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12380/9690 Copyright (c) 2025 Heri Budi Wibowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12381 2025-10-03T07:30:31Z ijoa:ART

ANALISIS LINTAS TERBANG ROKET MULTI-STAGE RKN200 Sasongko, Rianto. A Jenie, Yazdi. I Poetro, Ridanto. E Rocket Flight trajectory Stage separation This paper deals with a trajectory analysis of RKN200 multi-stage rocket system. The implementation of a multi-stage configuration means that a separation process has to be taken within the flight phase. The separation process is basically a transition process from a phase with booster as initial/launch propulsion to that with sustainer as the propulsion for the rest of flight time. RKN200 is a multi-stage rocket developed by LAPAN Indonesia for defence applications. In a multi-stage rocket development process, stage separation becomes a critical phase which should be considered carefully, since this phase will significantly affect the entire flight performance of the rocket. In this paper, the trajectory of RKN200 is analyzed in various cases with separation process included. The separation stage is modeled as a discrete process, i.e. by applying a sudden change on the rocket parameters values at the time of separation. In addition to that, impulsive force and moment which occur as a result of the separation ignition will also introduced into the mathematical model of the rocket dynamics, such that their influence to the rocket flight variables can be counted and computed . The modeling, simulation, and analysis of the flight trajectory are conducted using a simulation software already developed for rocket dynamic and performance analysis. Some simulation results are presented and analyzed to evaluate the RKN200 flight trajectory in some flight settings and conditions, and also to observe the effect of stage separation process on the rocket flight. BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12381 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 132-146 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12381/9689 Copyright (c) 2012 Rianto. A. Sasongko, Yazdi. I. Jenie, Ridanto. E. Poetro https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12382 2025-10-03T07:30:31Z ijoa:ART

PENGARUH PENAMBAHAN GLOVE DAN PENGURANGAN YEHUDI SERTA PERGESERAN LOKASI APEX TERHADAP KARAKTERISTIK AERODINAMIKA SAYAP PESAWAT TERBANG Sudira, I G.N NWDU VSAERO Glove Yehudi Apex Success indicator in airplane design process is depended on success or not in wing design process. Wing design process was supported by many design variable and the final result was compromise one from many scientific science or specialist. The first step in airplane wing design after design requirement & objective (DR&O) was defined, is determining wing planform through parametric study. Parametric study was conducted to make sure that all design parameters have been considered especially for aerodynamic and structural aspect. This paper discuses the influence of glove and yehudi changes and also apex location movement with respect to aerodynamic characteristic of the wing. Additional of the glove was intended to compensate yehudi existent due to structural aspect mainly for landing gear placement. Disadvantage of aerodynamics aspect due to yehudi existent is expected will be overcome by additional of glove. Apex location is also important parameter to control the shape of pressure coeffient of wing profile. Apex location can be moved according to sensitivity of designer to achieve design target. For the whole, it can be said that glove and yehudi and also apex location can be isolated its influence to major variable design namely to wing profile pressure distribution. The computer program used in this analysis is integration of the program for wing geometry generation, paneling process and computational fluid dynamic code (CFD), in this case VSAERO, and by author it is called NWDU. BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12382 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 159-172 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12382/9691 Copyright (c) 2012 I G.N. Sudira https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12383 2025-10-03T07:30:31Z ijoa:ART

CHARACTERIZATION OF SIZE AND SHAPE OF AMMONIUM PERCHLORATE PARTICLE FROM CHINA, SOUTH KOREA, AND INDONESIA AND THEIR INFLUENCES ON PROPERTIES OF PROPELLANT Hutauruk, Jones Bura, Romie Oktovianus Wibowo, Heri Budi Characterization ammonium perchlorate propellant The aim of this study is to obtain characteristics of ammonium perchlorate particle that used in Rocket Technology Center (LAPAN). Characterization begin from the determination of particle size distribution with Particle Size Analyzer. The SEM is used to obtain information about the morphology of AP, furthermore, the results are reprocessed using ImageJ software to analyze the shape of AP particle, and the Surface area was obtained by using BET. Characteristic of AP such as particle size, shape, and surface area are important parameters because those are directly related to propellant combustion energy. Ammonium perchlorate was procured from China, South Korea, and Indonesia with a particle size of 200µm From this study, the particle size of APC200, APH200 and API200 was obtained, which are 265 µm, 236 µm, and 242 µm, with particle shape aggregate value of 0,68, 0,38 and 0,33, roundness of 0,57, 0,79,0,63, and surface area of 1,104 m2/g, 5,561 m2/g, and 2,972 m2/g. BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12383 10.30536/j.jtd.2020.v18.a3346 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara; 53-62 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12383/9692 Copyright (c) 2020 Jones Hutauruk, Romie Oktovianus Bura, Heri Budi Wibowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12384 2025-10-03T07:30:31Z ijoa:ART

RANCANG BANGUN SISTEM PENGUJIAN MOTOR BRUSHLESS UNTUK APLIKASI SOLAR-LAPAN SURVEILLANCE UAV BERBASIS LABVIEW (DESIGN OF BRUSHLESS MOTOR PERFORMANCE TESTING SYSTEM FOR SOLAR-LAPAN SURVEILLANCE UAV APPLICATION BASED ON LABVIEW) Sugiarto, Tommy Setyadewi, Imas Tri Marta, Aryandi P., Gunawan Setyo Pesawat Tanpa Awak Sel Surya Motor Brushless Solar LSU LabVIEW Tantangan terbesar dalam pengembangan pesawat tanpa awak adalah keterbatasan energi. Salah satu solusi masalah tersebut adalah dengan menggunakan energi alternatif diantaranya sel surya. Aplikasi pesawat tanpa awak dengan sel surya membutuhkan analisa perhitungan kebutuhan daya pesawat saat terbang, analisa tersebut akan berguna untuk menentukan spesifikasi komponen yang akan digunakan pada pesawat. Penelitian ini akan membahas rancang bangun sistem pengujian kinerja motor brushless untuk aplikasi pada Solar LAPAN Surveillance UAV (LSU) menggunakan perangkat lunak LabVIEW. Dari hasil pengujian sistem ini mampu melakukan pengukuran dengan galat sebesar 1.27%,0.61%, dan 5.65% masing masing untuk pengukuran RPM, tegangan dan arus pada baterai.  BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article https://ejournal.brin.go.id/ijoa/article/view/12384 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 113-119 3032-0895 Copyright (c) 2025 Tommy Sugiarto, Imas Tri Setyadewi, Aryandi Marta, Gunawan Setyo P. https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12385 2025-10-03T07:30:31Z ijoa:ART

RANCANG BANGUN MODEL WAHANA HOVERWING XHW-1 Mulyanto, Taufiq Baruna, Digit Mitra Hoverwing Hovercraft WiSE-craft Design Model build Hoverwing craft is a combination of hovercraft and WiSE-craft. Hoverwing craft operation has transition phase from air cushion lift to aerodynammic lift, and vice versa. A Hovering model, named XHW-1, was designed and built to understand further the design problem related to this kind of vehicle and to observe the transition phase. To simplify construction, manufacture and testing, but without reducing the uniqueness of the vehicle, the model was designed to be operated on a flat surface. The design considered hovercraft related aspect and aircraft aspect as well. The configuration chosen was monohull. The model weight 755 gr, has 1.2 m wing span, and 20 x 30 cm air cushion. Preliminary test showed that air cushion could function properly and that model could reach 3 m/s forward speed. BRIN Publishing 2012-04-10 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12385 Indonesian Journal of Aerospace; Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara; 147-158 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12385/9693 Copyright (c) 2012 Taufiq Mulyanto, Digit Mitra Baruna https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12386 2025-10-03T07:30:31Z ijoa:ART

Roll Amplification of Solid Rocket Motor in LAPAN Sounding Rocket Sudiana, O. Teofilatto, P. Sounding rocket solid rocket motor roll amplification Sounding rockets have been used for scientific research and implemented in meteorological and upper atmosphere studies since the late 1950s. Sounding rockets are sub-orbital carriers that follow a parabolic trajectory from launch to landing. Supporting the roadmap of Satellite Launch Vehicle development, LAPAN had launch The Sounding Rocket Program.A sensitive amplification from the production of an unpredicted roll rate was detected during the boost of the sounding rocket, despite of the tail wings in cruciform configuration at last flight test. One of this phenomenon can be influenced by the flow field of the combustion chamber during boosting time.The basic idea of this research is to model the roll amplification effect as a swirling motion of portion of exhaust gas that participate to the rotation dynamics of the rocket rather than to exit immediately flow the combustion chamber. Available flight data where is obtained from last flight test presented. It is shown the presence of a significant roll amplification when solid rocket motor is used during burning time. The result has a good agreement to presence of a portion of exhaust gas influence an unpredicted roll amplification. BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12386 10.30536/j.jtd.2020.v18.a3351 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara; 63-72 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12386/9694 Copyright (c) 2020 O. Sudiana, P. Teofilatto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12387 2025-10-03T07:30:31Z ijoa:ART

PENYEMPURNAAN PROSES PEMBUATAN PROPELAN KOMPOSIT LAPAN BERDASAR HASIL PENELITIAN DARI INDIA (PROCESS IMPROVEMENT OF LAPAN’S COMPOSITE PROPELLANT PREPARATION BASED ON RESEARCH RESULT FROM INDIA) Hartaya , Kendra Propelan Impuls spesifik Komposit Telah dilakukan pembahasan terhadap proses dalam pembuatan propelan padat komposit. Pembahasan bertujuan untuk mendapatkan kepastian mengenai urutan dalam proses pencampuran bahan baku hingga memperoleh sampel propelan yang siap uji. Pembahasan untuk mendapatkan urutan pencampuran bahan baku dilakukan terhadap makalah-makalah para peneliti dari India dengan sudut pandang bahan baku utama propelan yang yang mudah diperoleh yang terdiri dari binder (HTPB), hardener (isosianat), AP, Al powder. Metode dalam penelitian ini adalah penelitian terhadap kepustakaan dan eksperimen. Eksperimen dilakukan sebagai wujud adopsi teknologi proses dari hasil penelitian kepustakaan. Hasil dari penelitian ini, diperoleh sampel propelan yang dibuat dengan urutan pencampuran HTPB dengan Al powder, setelah campuran homogen ditambahkan AP halus, AP sedang, AP kasar, diakhiri penambahan Hardener. Setelah homogen dicetak dengan dimensi yang diinginkan, dioven pada suhu 60â°C selama 20 jam. Setelah itu pelepasan mandril dan diperoleh propelan siap uji baik uji statik maupun uji fisik. Waktu dari awal pencampuran hingga menjadi sampel siap uji sebesar 125 menit sedang dari teknologi india sebesar 290 menit, sehingga dengan demikian ada alasan untuk menambah waktu proses guna mendapatkan hasil lebih baik dalam hal homogen campuran. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12387 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 121-129 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12387/9695 Copyright (c) 2025 Kendra Hartaya https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12388 2025-10-03T07:30:31Z ijoa:ART

INCREASING DATA TELEMETRI SOUNDING ROCKET LAPAN WITH PULSE CODE MODULATION METHODE Arisandi , Effendi Dodi The telemetry data of the sounding rocket when flight in the space is very important to known. This data will be used for next mission or evaluation the last rocket flight. Commonly the data of the sensor in the sounding rocket are accelerometer, gyroscope, magnetometer, GPS and so on. As much data as possible than can be sent to the ground control system when the rocket flies. The problem is when the baud rate is low so not much data can be transmitted. Another problem is when the using serial bit standard communication such as the baud rate is 115.200 which mean that the maximum data in one second is 14,400 characters. It is less than when using the PCM bit rate. Application of PCM in the telemetry for sounding rocket LAPAN is new and need development to reach the optimal. With the PCM method the communication data can transmit around 1.25Mbps or 156,250 characters based on the TR FM02-S-2 full S-band transmitter. In this research, focus to the implementation the PCM method on the FPGA for sending and receiving the data via cable. Two FPGA boards can work together for sending and receiving data with PCM method with the total bit is 1.25Mbps.   BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12388 10.30536/j.jtd.2020.v18.a3353 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara; 73-80 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12388/9696 Copyright (c) 2020 Effendi Dodi Arisandi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12389 2025-10-03T07:30:31Z ijoa:ART

ANALISIS DATA SENSOR ACCELEROMETER PADA UJI TERBANG ROKET EKSPERIMEN LAPAN TIPE RX–200 (ANALYSIS SENSOR DATA ACCELEROMETER IN FLIGHT TEST ROCKET EXPERIMENT LAPAN TYPE RX-200) Kurdianto, Kurdianto Sensor Accelerometer Mikroprosesor Ground station Roket RX–200 adalah jenis roket model balistik dengan diameter 200mm. Roket ini dilengkapi dengan muatan (payload) berupa sensor pengindera gerak berbasiskan mikroprosesor berupa 6-Degree of Freedom (6-DOF) Inertial Measurement Unit (IMU) dan sistem telemetri onboard dengan menggunakan frekuensi 900MHz. Karakteristik terbang roket RX-200 saat uji terbang dapat dianalisis dari data sensor pengindera gerak yang diterima menggunakan antena omni 900MHz dan antena yagi 900MHz. Dari data yang diterima, roket mengalami percepatan hingga sebesar 19.2G, burning out terjadi pada detik ke 7.09, dengan ketinggian terbang roket dari General Position System (GPS) mencapai 1952 m atau 1.9 Km. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12389 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 131-137 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12389/9697 Copyright (c) 2025 Kurdianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12390 2025-10-03T07:30:31Z ijoa:ART

ALGORITMA DETEKSI SUDUT AZIMUT DAN ELEVASI ROKET MENGGUNAKAN SEMBILAN ANTENA ARRAY YAGI-UDA Zain, Satria Gunawan Susanto, Adhi Widodo, Thomas Sri Widada, Wahyu Angle Estimation Noise effects Yagi-Uda Antennas Rocket movement estimation Radiation pattern of Yagi-Uda antenna is elliptical. This pattern can be used as a detector for the direction of the source of a radio emission. A total of nine Yagi-Uda antennas fitted with a 3x3 configuration. With this configuration, the measurement range for azimuth and elevation angles can reach 80º. The simulation was performed by using an antenna radiation pattern data. The number of antennas used for this simulation is nine. Then the data is merged into a 3x3 antenna configuration data. Based on data from nine antenna radiation patterns, the algorithm for the estimation of azimuth and elevation angles can be applied. Simulation results show that the measurement error of the signal without noise is close to zero. The algorithm used in this simulation can be applied to noise below 25%. BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12390 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara; 1-7 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12390/9698 Copyright (c) 2012 Satria Gunawan Zain, Adhi Susanto, Thomas Sri Widodo, Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12391 2025-10-03T07:30:31Z ijoa:ART

PENGARUH DARI POSISI PUSAT MASSA ROKET YANG TIDAK TERLETAK PADA SUMBU AXIS SIMETRI TERHADAP DINAMIKA TERBANG ROKET BALISTIK (THE DYNAMIC OF THE ROCKET DUE TO THE OFFSET OF ITS CENTER OF MASS RELATIVE TO THE SYMMETRIC AXIS) Riyadl, Ahmad Pusat massa roket Simulasi dinamik Wobbling Dalam uji terbang roket balistik kadang terjadi suatu gerakan wobbling yaitu suatu gerakan yang tidak linear menbentuk lintasan yang konus. Fenomena ini dapat terjadi dikarenakan berbagai sebab, dimana salah satu penyebabnya adalah posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket. Sehubungan roket LAPAN pada umumnya termasuk roket balistik maka perlu dilakukan penelitian untuk mengetahui kemungkinan dapat terjadinya gerakan wobbling pada saat uji terbang yang disebabkan oleh posisi pusat massa roket yang tidak terletak pada sumbu axis simetri. Dari hasil perhitungan pada penelitian ini terlihat bahwa posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket menyebabkan terjadinya gangguan momen roll, pitch dan yaw pada roket, dimana gangguan dari momen roll, pitch dan yaw tersebut memicu gerakan wobbling. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12391 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 139-147 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12391/9699 Copyright (c) 2025 Ahmad Riyadl https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12392 2025-10-03T07:30:31Z ijoa:FUP

Full Pages JTD Vol 18 No.1 Juni 2020 Jurnal, Redaksi - BRIN Publishing 2020-11-06 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12392 Indonesian Journal of Aerospace; Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12392/9700 Copyright (c) 2020 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12393 2025-10-03T07:30:31Z ijoa:ART

IMPLEMENTASI CHIRP SIGNAL GENERATOR PADA FPGA UNTUK MISI PENCITRAAN LAPAN SURVEILLANCE AIRCRAFT - SYNTHETIC APERTURE RADAR (LSA-SAR) (IMPLEMENTATION OF CHIRP SIGNAL GENERATOR ON FPGA FOR IMAGING MISSION OF LAPAN SURVEILLANCE AIRCRAFT - SYNTHETIC APERTUR Tahir, Andi Mukhtar Jayani , Ade Putri Septi Radar Chirp generator DDS chirp generator Radar bekerja dengan memanfaatkan sinyal gelombang elektromagnet yang dihasilkan olehperangkat waveform generator. Sinyal yang dipancarkan oleh radar akan dipantulkan sebagian olehtarget dan pantulan ini ditangkap oleh radar untuk diolah dengan cara membandingkan sinyal yangdipancarkan dengan sinyal yang dipantulkan kembali sehingga menghasilkan informasi berupakecepatan, jarak, atau citra dari suatu target. Waveform generator merupakan perangkat yang memegangperanan awal dalam sebuah sistem radar yang turut menentukan kinerja dari suatu sistem radar,oleh karena itu pada penelitian ini penulis akan membuat sebuah waveform generator sebagailangkah awal dalam percobaan di bidang teknologi radar. Waveform generator yang dibuatmenghasilkan sinyal chirp dengan menggunakan metode Direct Digital Synthesizer (DDS) yangmenggunakan memori yang lebih kecil dibandingkan Memory-based Chirp Generator, karena sinyalreferensi yang digunakan hanya berupa sebuah sinyal sinus dan cosinus. DDS chirp generator inidiimplementasikan pada board Field Programmable Gate Array Altera tipe Cyclone IV yang merupakandevelopment board produksi Terasic tipe DE2-115 dan menghasilkan keluaran berupa sinyal chirp.Hasil pengukuran sinyal keluaran menggunakan osiloskop menunjukkan sinyal chirp denganfrekuensi sampling 200 MHz, jumlah sample 6415 dan periode sampling 32 us, sedangkanpengukuran menggunakan spectrum analyzer terlihat terjadi pergeseran nilai frekuensi sehinggabandwidth tercapai sebesar 75,9 MHz. Namun secara keseluruhan hasil ini menunjukkan bahwasistem berjalan dengan baik. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12393 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 149-161 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12393/9701 Copyright (c) 2025 Andi Mukhtar Tahir, Ade Putri Septi Jayani https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12394 2025-10-03T07:30:31Z ijoa:ART

THE COMPARATION OF TWO LAPAN'S PROPELLANTS OF DIFFERENT COMPOSITION Jihad, Bagus H. Soemardi, Tresna P. Priadi, Dedi Impuls specific Characteristic efficiency Proppellant Simulation This paper compares two LAPAN'S propellant compositions. The A propellant has a composition of AP/AL/Binder with ratio of 70/10/20, and propellant B has ratio 75/7.5/17.5, both with HTPB base but different curing agent. As comparator of this simulation is RX-1512.01 rocket that has flight tested. The performances which compared are specific impulse and efficiency characteristic. Result shows that the propellant B gives higher specific impulse, however higher losses is, about 5.373 percent. One to be considered is that the propellant B produce combustion temperature higher than propellant A by 200 k, that may influence the rocket structures. Keywords: Impuls specific, characteristic efficiency, propellant, simulation. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12394 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12394/9702 Copyright (c) 2025 Bagus H. Jihad, Tresna P. Soemardi, Dedi Priadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12395 2025-10-03T07:30:31Z ijoa:ART

DESAIN NOSEL ROKET CAIR RCX250 MENGGUNAKAN METODE PARABOLIK DENGAN MODIFIKASI SUDUT EKSPANSI Priamadi, Eko Hakim, Arif Nur Bura, Romie O Liquid rocket Parabolic nozzle Thrust CFD The present research is conducted to design the optimum nozzles for RCX250 engine, that is designed to produce maximum thrust of 250 kgf with combination of LOX and Kerosene as its propellant. The new nozzles were determined to be parabolic nozzle, with conical nozzle as its comparison. The parabolic nozzle was designed using Thrust Optimized Parabolic (TOP) method invented by G.V.R.Rao. TOP nozzle design method is performed by approximating a Thrust Optimized Contoured (TOC) Nozzle using parabolic equation. The method would result more efficient nozzle than conical or ideal bell nozzle. Further, the parabolic nozzle were modified in its initial and exit angle to create uniform velocities distribution at nozzle exit. A Computational Fluid Dynamics Method (CFD) is used to simulate the nozzle designs. The simulation was carried out in axis-symmetric condition using commercial CFD software. The simulation results show that MOD 1 nozzle, with initial angle (θN) 26 deg and exit angle (θe) 12 deg, gives maximum thrust, which is 4.67 % higher than reference conical nozzle. BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12395 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara; 8-17 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12395/9704 Copyright (c) 2012 Eko Priamadi, Arif Nur Hakim, Romie O. Bura https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12396 2025-10-03T07:30:31Z ijoa:ART

RANCANG BANGUN TABUNG KOMPOSIT TEKANAN TINGGI UNTUK PROPELAN ROKET CAIR KOROSIF (DESIGN OF COMPOSITE OVERWRAPPED PRESSURE VESSEL FOR CORROSIVE LIQUID ROCKET PROPELLANT) Hakim, Arif Nur Tabung propelan cair Korosif Komposit Liner Rancang bangun tabung komposit tekanan tinggi (COPV) telah dilakukan untuk memperkecil berat struktur tabung propelan wahana roket cair. Tekanan operasi yang diharapkan dari tabung ini adalah 150 bar dan harus mampu menahan asam nitrat yang bersifat sangat korosif. Simulasi numerik dilakukan untuk memprediksi kekuatan struktur tabung SS304. Stainless steel SS304 dipilih sebagai tabung liner karena karakteristik ketahanan yang bagus terhadap korosi dan biaya yang relatif murah. Tabung liner kemudian dilapisi dengan serat karbon dan resin epoxy EPR 174 secara manual dengan metode hand lay up. Uji hidrostatik dilakukan untuk menguji kekuatan tabung dan uji X-ray digunakan untuk menganalisa kondisinya setelah uji hidrostatik. Berat riil tabung komposit adalah 9,1 kg, atau 67% dari berat tabung yang menggunakan SS304 setebal 5,5 mm. Hasil pengujian menunjukkan bahwa tabung komposit tersebut dapat menahan tekanan statis hingga 200 bar, namun masih ada sedikit kebocoran. Stretching dilakukan pada pembebanan pertama dengan menaikkan tekanan secara perlahan-lahan sehingga tabung akan meregang secara tepat dan menjaga komposit tetap terikat pada tabung liner dan dapat mencegah kegagalan struktur hingga tekanan 200 bar. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12396 Indonesian Journal of Aerospace; Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara; 163-173 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12396/9707 Copyright (c) 2025 Arif Nur Hakim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12397 2025-10-03T07:30:31Z ijoa:FP

Front Pages JTD Vol 18 no.2 Desember 2020 Jurnal, Redaksi - BRIN Publishing 2020-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12397 Indonesian Journal of Aerospace; Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12397/9703 Copyright (c) 2020 Redaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12398 2025-10-03T07:30:31Z ijoa:ART

OPTIMALIZATION OF MICROSTRIP SLOT ARRAY ANTENNAS FOR MULTI-WIDEBAND Fitri, Iskandar Microstrip slot antenna Array configuration Network impedance Multi tuning stub Microstrip slot antenna fed by matching network of microstrip line to increase very wide-bandwidth and multiband is proposed. The microstrip line composed of multi tuning stubs is used to control slots antenna real impedance to match with impwdance cahracteristic of feeding line so that it could increase the bandwidth. The design are achieves good input impedance in the ranges frequency of 1.3 - 5.1 GHz for single slot and 1.1 - 6.4 GHz for two slots. The bandwidths of antennas become very wide if the slots made in array configuration. The measured return loss S11 agrees well with the simulation results for single slot as axample. Keywords: microstrip slot antenna, array configuration, network impedance, multi tuning stub. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12398 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12398/9705 Copyright (c) 2025 Iskandar Fitri https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12399 2025-10-03T07:30:31Z ijoa:ART

DESAIN ALAT UJI NOSEL DENGAN MENGGUNAKAN PRINSIP TEROWONGAN ANGIN SUPERSONIK Jihad, Bagus H Priadi, Dedi Windtunnel Nozzle Supersonic Run-time Schlieren The accuracy of nozzle design can be improved by validation. Two methods of validation is software or hardware application. The software can be either CFD software or special software for the nozzle design, such as NOZZLE ® or Aerospike ®. The limitations of CFD software is on unsteady flow conditions. while the limitations of special software is the obscurity of assumptions used. Therefore, the flow validation experimental is important to be implemented. Lapan has three units of wind tunnels, namely subsonic, transonic and supersonic. They have the capability to measure the external flow of the body. While the nozzle design purpose is mostly to investigate the internal flow of the nozzle. Therefore, the nozzle flow testing system which is called a mini wind tunnel has been designed. This wind tunnel is designed to have speed of Mach 2.4, but the effective speed of 2 Mach. By using a calculation we obtain the run time of 46 seconds. If we assume the pressure drop is 40%, then actually the run time is 28 seconds. BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12399 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara; 18-27 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12399/9706 Copyright (c) 2012 Bagus H. Jihad, Dedi Priadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12400 2025-10-03T07:30:31Z ijoa:ART

SISTEM KONTROL SUN SEEKER SUATU MODEL UNTUK MENGENDALIKAN PERILAKU WAHANA ANTARIKSA Purwanto, Eko Budi Sun seeker control system Fase lead Waktu penetapan Lewatan maksimum Kondisi tunak Sun seeker control system doing by monitoring the sun as main reference. The result of monitoring the sun position used for the line correction of space vehicle. In these paper used simulation method for gated parameter value control system. To know the influence of sun seeker control system, simulation was doing with and without lead compensator. The result of simulation show that without sun seeker control system the time settling is ts = 0.35 second and maximum overshoot Mp = 44,4 percent. These results not reasonable for controling of plan with high velocity like rocket and satellite. Later simulation with phase lead sun seeker control system, give settling time ts = 0,12 second and maximum overshoot Mp 5 percent. From the simulation data that sun seeker control system can used for space vehicle control and agree with steady state error specification.Keywords: Sun seeker control system, FFase lead, Waktu penetapan, lewatan maksimum, kondisi tunak BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12400 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12400/9708 Copyright (c) 2025 Eko Budi Purwanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12401 2025-10-03T07:30:31Z ijoa:ART

SIMULASI GERAK DAN ANALISIS KESTABILAN KOPLING INERSIA WAHANA DIRGANTARA DENGAN BENTUK BADAN RAMPING Muhammad, Hari Samputra, Hilman Jenie, Yazdi I Sembiring, Javensius Inertia coupling Stability analysis Slender body Flight simulation Inertia coupling is a motion phenomenon of a high-speed airplane having slender body and low aspect ratio. This inertia coupling happens when the aircraft performs a roll manoeuvre motion with a high roll rate. This paper will discuss the derivation of inertia coupling equations of motion, modelling equations of motion in the Matlab/Simulink software, simulating the dynamics motion, and analyzing the stability of the inertia coupling. Numerical simulation and stability analysis of the inertia coupling for a fighter aircraft will be presented in this paper. BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12401 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara; 28-40 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12401/9709 Copyright (c) 2012 Hari Muhammad, Hilman Samputra, Yazdi I. Jenie, Javensius Sembiring https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12402 2025-10-03T07:30:32Z ijoa:ART

PENGEMBANGAN METODE PENENTUAN KARAKTERISTIK RANCANGAN AWAL ROTOR TURBIN ANGIN Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Rancangan awal Koefisien daya Tip speed ratio A method for determining design characteristics of a wind turbine rotor has been developed. Given the desired power and operational wind speed, the approximate design diameter and rotor rpm can then be determined. The size of the rotor diameter is governed by the blade performance, in which is normally given as power coefficient Cp; designed rotor spedd can be known after calculating the tip spedd ratio. Using this method, the blade and rotor characteristics can be designed quickly as a preliminary design parameter. Keywords: Rancangan awal, Koefisien daya, Tip speed ratio. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12402 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12402/9710 Copyright (c) 2025 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12403 2025-10-03T07:30:32Z ijoa:FP

Front Page JTD Vol. 13 No. 1 Juni 2015 Jurnal, Redaksi - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12403 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12403/9711 Copyright (c) 2025 Reaksi Jurnal https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12404 2025-10-03T07:30:32Z ijoa:ART

SIMULASI PENGGUNAAN DIFFUSER PADA TURBIN ANGIN SUMBU HORISONTAL UNTUK KENAIKAN DAYA Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Wind turbine Diffuser CFD One technique to improve the power output of a wind turbine is by implementing a diffuser, which is called the diffuser augmented wind turbine (DAWT). The area ratio between the inlet and outlet of the diffuser increases the flow rate inside the diffuser which in effect produces higher output power. In this research, a 2 meters rotor diameter was used. Diffuser diameter ratio variation of 2, 3, 4, and 5 were chosen which provides inlet diameter of 4, 6, 8, and 10 meter respectively. Power rotor coefficient is assumed to be constant of 0.30. Air speed distribution inside the diffuser is calculated using CFD method. The inlet speed to the diffuser is varied to give 4 different speeds. The wind angle at the inlet is also varied at 0º, 30º and 60º. The simulation result showed that at 0 degree angle, diffuser diameter ratio variation of 2, 3, 4, and 5 will increase the power output about 58, 622, 3169, and 11519 times respectively. It also showed that the increase in the output power for diameter diffuser ratio of 2 at 0º and 60º angle is 58 and 4 times respectively.  BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12404 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara; 41-52 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12404/9713 Copyright (c) 2012 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12405 2025-10-03T07:30:32Z ijoa:ART

ANALISIS DESAIN, TEKNOLOGI DAN PRESTASI TURBIN ANGIN 10 KW Ginting, Dines Energi angin Energi terbarukan Turbin angin Small-scale wind energy conversion systems have been developed and utilized for rural electric generation. Performance and success of the systems strongly depend on available wind power as well as the design and technologies. Recently, that alternative energy technology is more important to support the electric supply and to anticipate continously increase of electric needs. In order to increase the use of that renewable energy technology, a 10 kW wind turbine has been chosen to be developed. Analysis of the wind turbine shows that the design, technologies, and performances are specific and limited to the application and wind power availability. The adaption and improvement is needed for developing the more effective use to the wind turbine. Keywords: Wind energy, energy terbarukan, Turbine angin. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12405 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12405/9712 Copyright (c) 2025 Dines Ginting https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12406 2025-10-03T07:30:32Z ijoa:ART

PEMBENTUKAN STRUKTUR MIKRO DAN SIFAT MAGNETIK Sm2Co17 MELALUI CARA SINTERING Siahaan, Mabe Magnet permanen SmCo Proses sintering Struktur mikro Koersivitas The studies, observation of microstructure and magnetic coercivity of the permanent magnet sample have been done through a metallurgy powders technique preparation process. The raw materials with the composition of Sm (Co, Cu, Fe, Zr)z equal 8.5 (at percent) initially in the form of powders alloys with the mean particle size of was 20-30 um. This powder is compacted through one direction pressed in the dies and the following with heat treatment steps. After sintering steps and homogeneity of each at a temperatures of 1190 degree celcius and 1130 degree celcius, the solid sample achieved with Sm2Co17 is mainly the magnetics phase. Further heat treatment that their received the next 10 degree celcius/minute until room temperature. And have succeeded to form cellular structures on the matrixs of magnetics phases while other phases in the form cellular structures on the matrixs of magnetics phases while other phases in the form of grain boundary and the magnetics coercivity. Conclution from result of this study is compared with the result of former research. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12406 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12406/9714 Copyright (c) 2025 Mabe Siahaan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12407 2025-10-03T07:30:32Z ijoa:ART

ANALISIS LOSSES PIPA LURUS BERDIAMETER 40 cm PADA TEROWONGAN ANGIN LAPAN Fitroh, Ahmad Jamaludin Pipe losses CFD wind tunnel One of LAPAN’s programs is design and build the ramjet open tested wind tunnel. The lenght of pipe connecting between wind tunnel and storage tank was designed long enough so it was estimated there is big losses along the pipe. The object of this research is to calculation that losses, specially for the straight part only. The magnitude of the losses was gotten from simulation using software based on CFD theory. This research used two methods, i.e. based on pressure method and based on mass flow rate method. The simulation’s result using based on mass flow rate method gave the higher losses for the straight pipe so that result was chosen as the final result. That result was processed become the losses as a function of mass flow rate. The higher mass flow rate will produce the bigger losses. At mass flow rate of 60 kg/s, the losses is 0.135 %/m and at 100 kg/s the losses is 0.299 %/m. The relation between both parameter is close to linier curve.  BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12407 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara; 53-60 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12407/9715 Copyright (c) 2012 Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12408 2025-10-03T07:30:32Z ijoa:ART

DESAIN DAN PENGUJIAN INTAKE KONIKAL SISTEM PROPULSI RAMJET PADA KECEPATAN SUPERSONIK (DESIGN AND TEST OF CONICAL INTAKE OF RAMJET PROPULSION SYSTEM AT SUPERSONIC SPEED) Sofyan, Sofyan Bura, Romie Oktovianus Intake supersonik Ramjet Pressure recovery Rasio laju massa Riset ini bertujuan untuk mendesain intake supersonik untuk aplikasi sistem propulsi ramjet. Desain intake ramjet sangat penting bagi proses pembakaran dalam ruang bakar mesin ramjet. Dalam desain intake konikal ini, kondisi Mach 2 dijadikan sebagai acuan, dengan kompresi eksternal. Penelitian ini juga menguji intake ramjet dalam terowongan angin supersonik. Desain dilakukan dengan menempatkan gelombang kejut pada bibir cowl intake untuk memperoleh pressure recovery yang tinggi dan gaya hambat serendah mungkin. Hasil desain analitik dibandingkan dengan hasil numerik pada berbagai kondisi intake – subkritikal, kritikal, dan superkritikal. Hasil numerik juga divalidasi dengan eksperimen model. Intake yang didesain memberi pressure recovery sebesar 0,93, namun hasil ini cukup berbeda dengan hasil eksperimental. Ini disebabkan karena efisiensi kompresi tidak diikutkan dalam proses desain. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12408 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 1-13 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12408/9717 Copyright (c) 2025 Sofyan, Romie Oktovianus Bura https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12409 2025-10-03T07:30:32Z ijoa:ART

ANALISA AERODINAMIKA KENDALI CANARD ROKET RKX 250 Ginting, Salam Canard Dinamika stabilitas Statik stabilitas Static margin Pusat tekanan aerodinamika Mach number In the framework of guided missile development in LAPAN, Center of Technology has been rocket designed, constructed and then performed a guided missile trial launching in Pameungpeuk in May 2002. However the result was still far from expectation. It has been realized that numerous of factors played a part in the failure of the missile trial launching, which are structure strenght, propulsion, propellant, guidance system and aerodynamic stability. From all the above factors, aerodynamic static stability is the initial requirement which has to be validated before stepping to the next design process. Based on the above situation, it has been carried out a analysis un RKX 250 rocket aerodynamic static stability with canard guidance which configuration is almost similiar with the one that was launched in Pameungpeuk. To find out the rocket's aerodynamic static stability, a research on lift coefficient and drag coefficient must be done first. From the lift coefficient data, a conduction the center pressure of aerodynamics rocket. Method that is used in this research is the ine which was developed by quadrature multhopp which is analytical method (Krasnov N.F.1978).  BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12409 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12409/9716 Copyright (c) 2025 Salam Ginting https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12410 2025-10-03T07:30:32Z ijoa:ART

ESTIMASI BIAYA DAUR HIDUP DAN OPTIMISASI HARGA PESAWAT TERBANG Zain, Rais Ahyarsi, Odi Conceptual aircraft design Life cycle cost Object oriented approach Visual C++ Since the conceptual design phase, the estimate of airplane life cycle cost (LCC) is carried out to support a decision making process. The LCC consist of research, development, testing, and evaluation cost, where an airplane estimated price (AEP) is a part of this calculation. Furthermore, AEP is employed as a non linear objective funtion for developing a constrained optimization algorthm. Rosen’s gradient projection is applyed in the development of computer program named Cost Analysis implementing object oriented approach on Microsoft Visual C++ 6.0. In order to verify the application, some data of Ourania jet airplane were utilized for carrying out a case study. The result of Cost Analysis shows that the estimated LCC are similar to the reference. Also, the optimization problems can be solved by Rosen’s algorithm less than ten iterations. BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article https://ejournal.brin.go.id/ijoa/article/view/12410 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara 3032-0895 Copyright (c) 2012 Rais Zain, Odi Ahyarsi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12411 2025-10-03T07:30:32Z ijoa:ART

RANCANGAN DAN IMPLEMENTASI SISTEM PENERIMA S-BAND DATA VIDEO SATELITE LAPAN-TUBSAT Rahman, Abdul Video surveillance One of the LAPAN-TUBSAT satellite mission is video surveillance. This mission is done with transmiting real time video from satellite. For reception of this transmission in ground station it is needed to specify the specification and general design of the receiver, so that it could receive and process the signal transmission from the satellite to become real time video, Specifying of the specification of this receiver used link budget calculation, transmission type and other RF parameters. The specification and general design of this receiver was implemented as an S-BAnd Video Receiver and already tested using real time transmission from DLR-TUBSAT satellite's video and applied in LAPAN-TUBSAT data reception.  BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12411 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12411/9718 Copyright (c) 2025 Abdul Rahman https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12412 2025-10-03T07:30:32Z ijoa:ART

METODE ADAPTIF FREKUENSI-CUTOFF UNTUK COMPLEMENTARY FILTER PADA ACCELEROMETER DAN GYROSCOPE UNTUK SUDUT PITCH DAN ROLL WAHANA TERBANG (ADAPTIVE CUTOFF-FREQUENCY METHOD FOR COMPLEMENTARY FILTER OF ACCELEROMETER AND GYROSCOPE FOR PITCH AND ROLL ANGLES FLIGH Widada , Wahyu Complementary filter Accelerometer Gyroscope Integrasi sensor Wahana terbang Unit pengukuran inersia (Inertial Measurement Unit/IMU) adalah perangkat elektronik yang digunakan untuk mengukur kecepatan, orientasi, dan gaya gravitasi, dengan menggunakan kombinasi sensor accelerometer dan gyroscope, dan juga magnetometer pada wahana terbang. Tulisan ini membahas metode complementary filter dengan variabel adaptif cut-off frequency untuk integrasi sensor accelerometer dan gyroscope pada pengukuran pitch dan roll pada aplikasi wahana terbang seperti roket kendali dan pesawat tanpa awak. Accelerometer dapat digunakan untuk mengukur sudut tetapi terpengaruh oleh derau frekuensi tinggi, sedangkan gyroscope digunakan untuk mengukur sudut tetapi dipengaruhi drift noise. Filter ini dapat mengintegrasikan kedua sensor untuk mengukur sudut dengan lebih akurat, dari hasil percobaan menunjukkan Root Mean Square Deviation (RMSD) menjadi lebih baik sekitar 5,6 kali dibanding dengan pengukuran tanpa menggunakan filter. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12412 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 15-24 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12412/9719 Copyright (c) 2025 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12413 2025-10-03T07:30:32Z ijoa:PRE

Preface Jurnal Teknologi Dirgantara - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12413 Indonesian Journal of Aerospace; Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12413/9720 Copyright (c) 2025 Jurnal Teknologi Dirgantara https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12414 2025-10-03T07:30:32Z ijoa:ART

UPAYA PENINGKATAN KUALITAS GEOMETRIK CITRAUPAYA PENINGKATAN KUALITAS GEOMETRIK CITRA LAPAN-TUBSAT PADA APLIKASI SURVEILEN Rokhmana, Catur Aries Judianto, Chusnul Tri Videography system LAPAN-TUBSAT Satellite Geometric image improvement Indonesia has developed and operates the LAPAN-TUBSAT micro satellite since 2007 for supporting the surveillance application to observe the earth surface. LAPAN-TUBSAT satellite carried a video camera as an imaging sensor with 5 m ground resolution and 3.5 km swath. Data from this camera still have a weak geometric. This paper will reviews regarding LAPAN-TUBSAT data processing from video recordings as an effort to increase the geometric quality of the LAPAN-TUBSAT image. The correction model rectification of a simple single photograph is used for geometric correction. While the using of super resolution operator for increasing the video image resolution. The correction model rectification of a simple single photograph is used for geometric correction. While the super resolution operator attempted to efforts to increase the resolution of the video image. The experimental results shows geo-reference image with better geometric quality. The evaluation of LAPAN-TUBSAT performance should be carried out In the near future especially for providing Altitude information (Z). This is related to satellite manoeuvre ability to generate a stereo image with better B/H ratio BRIN Publishing 2012-02-08 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12414 Indonesian Journal of Aerospace; Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara; 70-81 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12414/9721 Copyright (c) 2012 Catur Aries Rokhmana, Chusnul Tri Judianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12415 2025-10-03T07:30:32Z ijoa:ART

PEMISAHAN POLIMER HTPB (HYDROXY TERMINATED POLYBUTADIENE) MELALUI KOLOM RESIN BERPORI UNTUK MERUBAH DISTRIBUSI BERAT MOLEKUL HTPB (SEPARATION OF HTPB POLYMER (HYDROXY TERMINATED POLYBUTADIENE) THROUGH POROUS RESIN COLUMN FOR MODIFY MOLECULAR WEIGHT DIST Wibowo , Heri Budi Propelan HTPB Polibutadien Pemisahan Produk HTPB yang diproses secara radikal memiliki kelemahan distribusi berat molekul yang lebar dan berat molekulnya cenderung lebih tinggi dari prediksi. Untuk dapat memperoleh HTPB yang sesuai untuk fuel binder propelan, maka diperlukan suatu metode pemisahan HTPB berdasarkan berat molekulnya. Tujuan penelitian ini adalah mengembangkan metode pemisahan HTPB berdasarkan perbedaan ukuran molekul berdasar filtrasi dalam kolom rersin berpori. Manfaat penelitian yang diharapkan adalah diperoleh metode pemisahan yang baik untuk dapat memperbaiki berat molekul polimer sehingga memenuhi persyaratan fuel binder propelan. Penelitian dilakukan dengan mengalirkan polimer ke dalam kolom berisi resin berpori “Crosslinked PE†dengan menggunakan pelarut toluenhidrofuran, kemudian setiap fraksi 2 mL diambil dan dianalisis konsentrasi dan berat molekulnya dengan kromatografi gel. Parameter pemisahan yang akan dicari adalah ukuran resin, panjang kolom, dan kecepatan alir pelarut (elusi). Hasil analisis dan pembahasan menunjukkan bahwa pemisahan polimer HTPB dengan menggunakan resin berpori dapat memisahkan polimer HTPB dengan baik. Untuk mendapatkan hasil pemisahan yang sempurna, maka dibutuhkan panjang kolom 100 cm, kecepatan elusi 2 mL per menit, resin ukuran 10 mikrometer, maka diperoleh metode pemisahan dengan tingkat kesalahan 2%. Dengan menggunakan metode pemisahan, dapat digunakan untuk memperbaiki berat molekul rata-rata HTPB dengan mengurangi beberapa fraksi yang memiliki berat molekul terlalu tinggi atau terlalu rendah. Hasil optimasi dapat digunakan untuk memperbaiki berat molekul rata-rata produk HTPB yang semula 6.000 menjadi 2.549 gr per mol sehingga memenuhi persyaratan sebagai fuel binder propelan, dan distribusi berat molekul rata-rata mendekati satu. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12415 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 25-37 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12415/9722 Copyright (c) 2025 Heri Budi Wibowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12416 2025-10-03T07:30:32Z ijoa:PRE

Preface Jurnal Teknologi Dirgantara - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12416 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12416/9723 Copyright (c) 2025 Jurnal Teknologi Dirgantara https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12417 2025-10-03T07:30:32Z ijoa:ART

MODEL DISTORSI PEMBIASAN ATMOSFER PADA CITRA SATELIT LAPAN-A2 DAN LAPAN-A3 (ATMOSPHERIC REFRACTION DISTORTION MODEL ON LAPAN-A2 AND LAPAN-A3 SATELLITE IMAGE) Hakim, Patria Rachman Citra satelit Distorsi geometri Pembiasan atmosfer Least-square Citra satelit umumnya memiliki distorsi baik dalam hal geometri maupun radiometri. Salah satu distorsi geometri yang umum terjadi pada citra satelit adalah distorsi yang diakibatkan karena terjadinya proses pembiasan cahaya oleh atmosfer. Dengan adanya pembiasan atmosfer, perhitungan proyeksi obyek di permukaan bumi pada bidang kamera menjadi rumit dan memerlukan proses komputasi yang cukup panjang. Makalah ini memodelkan distorsi pembiasan atmosfer tersebut dalam persamaan sederhana berdasarkan variabel orientasi kamera dan ketinggian satelit. Metode regresi linear least square digunakan untuk mengidentifikasi model persamaan dengan tingkat kesalahan terkecil. Hasil identifikasi menunjukkan bahwa distorsi pembiasan atmosfer pada citra satelit LAPAN-A2 dan LAPAN-A3 dapat dimodelkan menggunakan persamaan rasional orde-3 dengan hanya satu peubah yaitu orientasi kamera atau persamaan rasional orde-1 dengan dua peubah yaitu orientasi kamera dan ketinggian satelit. Hasil simulasi modul koreksi citra menunjukkan bahwa dengan menggunakan model persamaan yang diajukan maka perhitungan distorsi geometri pada citra satelit dapat dilakukan dengan lebih cepat tanpa mengurangi akurasi geometri citra secara signifikan. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12417 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 39-51 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12417/9724 Copyright (c) 2025 Patria Rachman Hakim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12418 2025-10-03T07:30:32Z ijoa:ART

RANCANG BANGUN PROTOTIPE SISTEM HEADING AUTOPILOT BERBASIS RATE-GYROSCOPE DAN MICROCONTROLLER Widada, Wahyu Heading autopilot Rate-gyroscope Stepper motor AVR microcontroller This paper discusses an experiment result of the prototype system feedback control for vehicle heading autopilot. The heading angle is measured with a rate-gyroscope and controlling with a control system based on a microcontroller and a stepper motor. This system is successfully realized within 0.5 degree of the error for heading angle. The accuracy of heading sensor is decrease due to vibration from stepper motor. To overcome such problem we recommended to use an analog lowpass filter and a mounting anti vibration. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12418 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12418/9725 Copyright (c) 2025 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12419 2025-10-03T07:30:32Z ijoa:ART

PENINGKATAN REOLUSI PERHITUNGAN FREKUENSI GELOMBANG SINUS MENGGUNAKAN FFT (IMPROVING CALCULATION RESOLUTION OF SINE WAVE FREQUENCY USING FFT) Kliwati , Sri Resolusi frekuensi gelombang sinus FFT. Perhitungan perubahan frekuensi sinyal sinus sangat penting untuk aplikasipada intrumentasi. Seperti pada sistem Doppler yang juga memerlukan perhitunganfrekuensi keluaran berupa gelombang sinus. Tulisan ini membahas peningkatanresolusi perhitungan perubahan frekuensi gelombang sinus berbasis algoritma FastFourier Transform (FFT). Penambahan waktu sampling data dapat meningkatkanresolusi frekuensi dengan signifikan, tetapi sampling data menjadi lebih rendah. Padaaplikasi frekuensi Doppler 440 MHz resolusi kecepatan sekitar 6.8 m/detik dengansampling data 10 Hz. Resolusi dan sampling data ini harus disesuaikan dengankecepatan dan durasi terbang roket agar optimal dalam pengukurannya BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12419 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 53-58 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12419/9726 Copyright (c) 2025 Sri Kliwati https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12420 2025-10-03T07:30:32Z ijoa:ART

PENGARUH VARIASI SUDUT SERANG SUDU PADA PRESTASI TURBIN ANGIN Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Hartono, Firman Sudu Sudut serang Research on variations of angle of attack turbine blade has been conducted to investigate their correlation with windturbine performances, and for these purposes, AEROFOIL LS (1)-0417 MOD has been selected with 4 angle variations. The first variation is selscted with constant slipstream, the second with Cl max of 0.3, while the third and fouth variations with Cl max of 0.5 and 0.7 respectively. Based on blade element and momentum theory for obtaining efficiency, the following results for all the four variations are 18.15 percent, 16.46 percent, 16.15 percent and 16.26 percent. Hence, it can be concluded that, a highest efficiency is obtained with a constant slipstream as in case 1. In practice, to achieve such configuration, a more accurate blade fabricantion process is required to obtain the highest efficiency. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12420 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12420/9727 Copyright (c) 2025 Sulistyo Atmadi, Ahmad Jamaludin Fitroh, Firman Hartono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12421 2025-10-03T07:30:32Z ijoa:ART

PENGARUH MASSA HIDROXY TERMINATED POLYBUTADIENE (HTPB) TERHADAP BESARNYA PENGARUH VINIL DALAM MENINGKATKAN LAJU KENAIKAN VISKOSITAS DAN KEKERASAN BINDER PROPELAN PADAT KOMPOSIT (THE EFFECTS OF HIDROXY TERMINATED POLYBUTADIENE (HTPB)`S MASS ON THE MAGNITUD Restasari, Afni Ardianingsih, Retno Abdillah, Luthfia Hajar Hidroxy terminated polybutadiene Kekerasan Laju kenaikan viskositas Vinil Binder propelan Propelan padat komposit yang memiliki viskositas dan kekerasan yang baik dapat menghasilkan performa yang baik. Karakteristik propelan tersebut meningkat dengan kenaikan kandungan vinil HTPB dalam binder. Besarnya pengaruh vinil bergantung pada persentase massa HTPB dalam binder yang berubah apabila bilangan hidroksil HTPB dan bilangan isosianat curing agent berubah. Oleh karena itu, penelitian ini bertujuan untuk mempelajari tingkat korelasi dan besarnya pengaruh persentase massa HTPB dalam binder propelan terhadap besarnya kenaikan laju kenaikan viskositas dan kekerasan sebagai akibat dari peningkatan kandungan vinil HTPB. Dalam penelitian ini, dibuat binder B dengan HTPB B yang mengandung 25% vinil dan dibandingkan dengan binder A dengan HTPB A yang mengandung 59% vinil. Komposisi binder meliputi perbandingan massa HTPB/TDI (Toluena diisosianat) 10:1, 11:1, 12:1, 13:1, 14:1 dan 15:1. Viskositas binder pada 10 menit pertama dan kedua pengadukan, serta kekerasan binder setelah 2 hari pematangan diuji dan perbedaan nilainya antara pada binder A dan B dihitung. Grafik % massa HTPB versus perbedaan laju kenaikan viskositas dan % massa HTPB versus perbedaan kekerasan dibuat untuk mendapatkan % besarnya pengaruh dan tingkat korelasi. Ditemukan bahwa terdapat hubungan positif antara % massa HTPB dengan kenaikan laju kenaikan viskositas dan kenaikan kekerasan binder sebagai akibat dari peningkatan kandungan vinil. Persentase massa HTPB berkorelasi sangat kuat sebesar 83,7 % dengan kenaikan laju kenaikan viskositas binder. Persentase massa HTPB juga berkorelasi sangat kuat sebesar 80,9% dengan kenaikan kekerasan binder. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12421 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 61-70 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12421/9728 Copyright (c) 2025 Afni Restasari, Retno Ardianingsih,, Luthfia Hajar Abdillah https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12422 2025-10-03T07:30:32Z ijoa:ART

SISTEM KENDALI ROKET UNTUK GERAK UNPITCHING Andiarti, Rika Sofyan, Edi PID Controller Missile Unpitching A missile control system utilizing Proportional-Integral-Derivative (PID) controller is proposed. With this controller, the missile is constrained to flight with zero pitch angle. By choosing LAPAN's missile RKX-100 as a dynamic model, this PID controller is applied. Simulation results show that the applying controller seems to be effective in missile unpitching manuver. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12422 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12422/9729 Copyright (c) 2025 Rika Andiarti, Edi Sofyan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12423 2025-10-03T07:30:32Z ijoa:ART

RANCANG BANGUN ENJIN ROKET CAIR DENGAN GAYA DORONG 1000 KGF MENGGUNAKAN PROPELAN ASAM NITRAT – KEROSEN (DESIGN OF LIQUID ROCKET ENGINE WITH 1000 KGF THRUST USING NITRIC ACID – KEROSENE PROPELLANT) Hakim , Arif Nur Enjin roket cair Injektor Asam nitrat Kerosen Enjin roket cair bergaya dorong maksimum 1000 kgf dengan pendinginan regenerative menggunakan fuel telah dirancang sebagai langkah awal untuk menjawab kebutuhan sistem propulsi roket yang memiliki impuls spesifik yang lebih tinggi, waktu pembakaran yang lebih lama dan kemampuan kontrol untuk Program Roket Pengorbit Satelit. Enjin didesain menggunakan pasangan asam nitrat dan kerosen avtur masing-masing sebagai oksidator dan fuel dengan sistem pengumpan gas inert bertekanan untuk mendorong propelan ke ruang bakar. Untuk mendistribusikan propelan, enjin mengadopsi injektor tipe impinging stream dengan 3 jet asam nitrat menabrak 1 jet kerosene yang dikelilinginya. Uji subsistem dilakukan untuk mengetahui kinerja masing-masing komponen enjin, sedangkan uji bakar dilakukan untuk mengetahui kinerja enjin secara keseluruhan. Hasil pengujian menunjukkan bahwa enjin ECX1000H2 dengan injektor konfigurasi kedua dapat menghasilkan semburan gas hasil pembakaran yang lurus dan cukup stabil dengan thrust rata-rata sebesar 610 kgf dan maksimum 670 kgf. Rendahnya thrust disebabkan oleh konfigurasi injektor yang masih belum optimal dan kecepatan suplai gas pendorong yang tidak cukup untuk membuat dorongan maksimum. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12423 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 71-85 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12423/9730 Copyright (c) 2025 Arif Nur Hakim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12424 2025-10-03T07:30:32Z ijoa:ART

PERANCANGAN IGNITER UNTUK MOTOR ROKET PADAT RX 420/4000 Rohili, Sukandi Nasir Igniter Motor roket RX 420/4000 Igniter is a rocket component with the function of providing activated energy to the surface of solid propellant in the burning chamber of the rocket motor. Igniter design needs overall data of the rocket especially initial free volume and stable combustion pressure of the propellant. The properties of either primer or main charge especially its density and fraction of condensed particles of it combustion products are also needed. This paper presents the design of igniter for RX-420/4000 solid rocket with wagon wheel-cylinder dual configuration. The design result gives data as follows main case length = 302.6 mm, diameter = 52 mm; main charge weight of 338.31 g; volume = 212.19 cc and nozzle throat area = 12.6 mm; the intermediate case of 200 mm length; 30 mm diameter with black powder weight = 310.87 g and volume of 141.37 cc, the overall length of igniter included stick of 402.6 mm.  BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12424 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12424/9731 Copyright (c) 2025 Sukandi Nasir Rohili https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12425 2025-10-03T07:30:32Z ijoa:ART

MULTI FREKUENSI ENCODER FLIGHT TERMINATION SYSTEM (MULTI FREQUNECY ENCODER FLIGHT TERMINATION SYSTEM) Arisandi , Effendi Dodi Multi Frekuensi Encoder FTS Metode DDS Penjumlahan Frekuensi Flight Termination System (FTS) adalah suatu sistem yang digunakan untuk menghentikan suatu misi peluncuran wahana udara apabila wahana tersebut mengalami kegagalan dalam misinya. Encoder FTS adalah bagian dari FTS yang akan memberikan sinyal perintah dalam bentuk gelombang sinus dengan frekuensi tertentu. Sinyal sinus yang secara umum disebut sinyal tone ranging dapat dibangkitkan dalam rentang frekuensi audio, 20Hz-20KHz. Metode Direct Digital Synthesis (DDS) dapat digunakan untuk membangkitkan sinyal tone ranging yang berupa sinyal sinus atau kotak (pulse). Kerahasiaan sinyal tone ranging yang dikirimkan pada bagian penerima FTS sangat penting agar tidak bisa diganggu oleh sinyal lain. Dengan menggunakan metode DDS AD9850, dapat dihasilkan sinyal sinus multi frekuensi pada endcoder FTS; 750Hz, 1000Hz, dan 1250Hz. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12425 Indonesian Journal of Aerospace; Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara; 87-93 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12425/9732 Copyright (c) 2025 Effendi Dodi Arisandi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12427 2025-10-03T07:30:32Z ijoa:ART

DESAIN DAN PENGUJIAN STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Triharjanto, Robertus Heru Satelit mikro LAPAN-TUBSAT The paper discuss about the design and test of the structure of LAPAN-TUBSAT micro-satellite, which is the task done by the writer during his time as the member of LAPAN-TUBSAT integration and test. The discussion includes the design requirment for the structure as mechanical interface and its implementation as well as its design validataion process via test as accordance to the requirement set by the launcher authority. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12427 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12427/9733 Copyright (c) 2025 Robertus Heru Triharjanto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12428 2025-10-03T07:30:32Z ijoa:ART

SIMULASI PENGUJIAN PRESTASI SUDU TURBIN ANGIN Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Sud Turbin angin Fluent Identification of whether aerodynamic performances of a rotor blades has met the criteria according to its design or not, the general procedure is to fabricate and perform a field testing; or testing its model in a windtunnel. Both method require high cost however; therefore, a simulation method using Fluent software had used for obtaining lower cost. The model used in an LS (1)-0417 Mod airfoil having 3 blades and rotor diameter 7.21 m. Simulation test shows a good result with a difference of 4.61 percent for torque and power from design result.  BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12428 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12428/9734 Copyright (c) 2025 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12429 2025-10-03T07:30:32Z ijoa:ART

RANCANG BANGUN GENERATOR TURBIN ANGIN TIPE AKSIAL KAPASITAS 200 W Nurtjahjomulyo, Agus Generator Turbin angin Generator is the component of wind turbine that convert mechanical to electrical energy and has a specific character which operates at low speed rotation ( 1000 rpm). Engineering design of wind turbine generator capacity 200 W discussed in this paper represents the results of fabrication and testing of the generator as a model. The experiment showed that the generator can be producing power 200 W at rotation 450 rpm with torque about 8.5 Nm. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12429 Indonesian Journal of Aerospace; Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12429/9735 Copyright (c) 2025 Agus Nurtjahjomulyo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12430 2025-10-03T07:30:32Z ijoa:PRE

Preface Jurnal Teknologi Dirgantara - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12430 Indonesian Journal of Aerospace; Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12430/9736 Copyright (c) 2025 Jurnal Teknologi Dirgantara https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12431 2025-10-03T07:30:33Z ijoa:ART

RANCANG BANGUN SISTEM PENAHAN PANAS PADA MOTOR ROKET CIGARETTE BURNING Sutrisno Pembakaran sigaret Pembakaran radial Tegangan termal Bahan isolasi panas The thrust of cigarette burning rocket motor is relatively lower but the is burning time is too long than that of the radial burning. The cigarette burning rocket motor structure easy to be fail due to the thermal stress thermal effect. Hence the thermal insulation sistem becomes very important. This paper discuss about the design and preparation of thermal insulation system in the cigarette burning rocket motor. The carbon and polyester fiber were used as the thermal protector materials in burning chamber. The liner matrix and inhibitor in the cap side were made from epoxy. O-ring spacer was applied to avoid the gas leakage from the combustion chamber. The performance of thermal insulation system was tested through static test of rocket motor. The result of the test provide that thermal insulation system showed the good performance. It is found that the burning time of the rocket motor is 116 second and the maximum temperature of the outer surface of the tube is 139 degree celcius. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12431 Indonesian Journal of Aerospace; Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12431/9737 Copyright (c) 2025 Sutrisno https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12432 2025-10-03T07:30:33Z ijoa:ART

EFEK DEFLEKSI PADA SUDU TURBIN ANGIN TERHADAP KELUARAN DAYA Atmadi, Sulistyo Fitroh, Ahmad Jamaludin Defleksi Sudu Turbin angin Keluaran daya Rugi-rugi The type of material used in the fabrication of wind turbine blade is a very important factor so that it will not exceed the allowable maximum deflection. An analysis is conducted to study this deflection effect to that power output and as case study, a 7.6 m blade of 10 kW LPN 10000 E turbine is used. Several assumption as such as deflection due to wind speed at perpendicular to local plane local blade are diameter blade and direction of aerodynamic at aerofoil plane local blade are considered. The distribution of blade deflection along the twisted span is assumed uniform. Calculation is performed for the polynomial order of 2,3 and 4, with variety of deflection of 0.2 m, 0.5m, 1 m and 1.5 m. for design wind speed of 9 m per s it was found that for 0.5 deflection, the losses of 6 percent, 9 percent and 12 percent for blade shape polynomial order 2,3 and 4 consequentively are produced; whereas for 1.5 m deflection, losses are 46 percent, 53 percent, and 56 percent for the same polynomial shape. If a maximum loss of 10 percent is taken, then the max allowable deflection is 0.5 m.  BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article https://ejournal.brin.go.id/ijoa/article/view/12432 Indonesian Journal of Aerospace; Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara 3032-0895 Copyright (c) 2025 Sulistyo Atmadi, Ahmad Jamaludin Fitroh https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12433 2025-10-03T07:30:33Z ijoa:ART

SISTEM WIND-DIESEL UNTUK PEMBANGKIT LISTRIK DI LOKASI DENGAN KECEPATAN ANGIN MENENGAH DI INDONESIA Pakpahan, Sahat Angin-diesel Modus bergantian Penghematan bahan bakar Windspeed is used as a reference in utilization of windturbine as a generating system and will be the main variable for calculation of the energy produced at a certain location. Windspeeds are classified in small scale, medium and large scales. Applications of small scales are generally in the stand-alone mode, while the large systems are intended for interconnection into the utility grid. In between, there are medium scale applications with the annual average windspeed of 4.0 m/s - 50 m/s. Examples of applications are hybrid of windturbine with local diesel generating sets, known as wind-diesel system using one or more windturbines of the size of 10 kW-100 kW and to be matched with the capacity of the existing deisel. most applications are in the intermittent mode of operation in order to obtain higher fuel saving which is used to operate the diesel. Some configurations, selection of components, modelling and calculations are presented to identify more detailed behaviour of the system. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12433 Indonesian Journal of Aerospace; Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12433/9738 Copyright (c) 2025 Sahat Pakpahan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12434 2025-10-03T07:30:33Z ijoa:ART

PENGEMBANGAN MODEM AFSK UNTUK TELEMETRI MUATAN ROKET UHF Widada, Wahyu AFSK modem Band-rate Telemetry Roket UHF Modem is an important component in the telemetry data system of the rocket. The telemetry data based on amateur radio is usually used an AFSK modem. This paper describes the development of AFSK modem using a microcontroller which the speed can be set to the maximum bandwidth of the radio. The prototype is use a 16 MHz of microcontoller and the speed can be set to 2.4 kbps that available to the standard bandwidth of an amateur radio. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12434 Indonesian Journal of Aerospace; Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12434/9739 Copyright (c) 2025 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12435 2025-10-03T07:30:33Z ijoa:ART

PENELITIAN KARAKTERISTIK AERODINAMIKA SAVONIUS BERSUDU BANYAK DENGAN METODA PENGGESERAN MESH Aribowo, Agus Energi angin Savonius Koefisien Momen Sliding Mesh Rotation of Savonius blades could be simulated using Sliding Mesh methode. The effective solution can be obtained by interfacing between moving zone and fixed zone by coordinating the linked cell. The number of tested blades 2,3,4 and 6. The result is the Savonius turbine with 3 blades having torque coefficient higher and efficiency level the compared which the other blades. The spacing of blade axis make airflow infiltrate and causing increase of force momen and negative drag force. By increasing the number of blades will result in the reduction of negative and positive force between one blade to the other. As a result, the performance will be reduced due to the increased number of blades.  BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12435 Indonesian Journal of Aerospace; Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12435/9740 Copyright (c) 2025 Agus Aribowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12436 2025-10-03T07:30:33Z ijoa:ART

TEKNIK KONTROL SLIDING MODE UNTUK AUTOPILOT ROKET Andiarti, Rika Autopilot Roket Tracking Kontrol Sliding mode This paper deals with autopilot for rocket tracking problem by using sliding mode controller. Rocket model is considered as a linear system with two control input; wing and tail deflection. Simulation results show that the controller effectively works and gives desired performance (fast reaching and low chattering). BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12436 Indonesian Journal of Aerospace; Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12436/9741 Copyright (c) 2025 Rika Andiarti https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12437 2025-10-03T07:30:33Z ijoa:PRE

Preface Jurnal Teknologi Dirgantara - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12437 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12437/9742 Copyright (c) 2025 Jurnal Teknologi Dirgantara https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12438 2025-10-03T07:30:33Z ijoa:ART

PENELITIAN KARAKTERISTIK AERODINAMIKA TRAILING EDGE SIRIP ROKET PADA KECEPATAN TRANSONIK DENGAN SIMULASI NUMERIK Aribowo, Agus Research of fin aerodynamic at a speed of Transonik of importance remember at this speed regim rocket have strongly increas in coefficient of drag, where will cause negativety to attainment of altitude target or its dynamics stability. In general there is 3 fin type which is inverterate to be used by rockets of LAPAN. Third of him have been done by examination use simulation of CFD in 2-D compressible flow at a speed of 1.6 M to 2.4 M. From result of the research discovered behavioral phenomenon born embryo of shockwave at a speed of transonic in region of models B trailing edge cause direct to degradation of pressure and enlarge coefficient of drag. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12438 10.30536/j.jtd.2005.v3.a811 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12438/9743 Copyright (c) 2025 Agus Aribowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12439 2025-10-03T07:30:33Z ijoa:ART

MODELING AND SIMULATION OF PROLATE DUAL-SPIN SATELLITE DYNAMICS IN AN INCLINED ELLIPTICAL ORBIT : CASE STUDY OF PALAPA B2R SATELLITE Muliadi, J. Jenie, Said D. Budiyono, A. - In response to the interest to re-use PAlapa B2R satellite nearing its End of Life (EOL) time, an idea to incline the satellite orbit in order to cover a new region has emerged in the recent years. As a prolate dual-spin vehicle, Palapa B2R has to be stabilized against its internal energy dissipation effect. This work is focused on analyzing the dynamics of the reusable satellite in its inclined orbit. The study discusses in particular the stability of the prolate dual-spin satellite in the effect of pertubed field of gravity due to the inclination of its elliptical orbit. Palapa B2R physical data was substituted into the dual-spin's equation of motion. The coefficient of zonal harmonics J2 was induced into the gravity-gradient moment term that affects the satellite attitude. The satellites's motion and attitude were then simulated in the pertubed gravitational field by J2 with the variation of orbit's eccentricity and inclination. The analysis of the satellite dynamics and its stability was conducted for designing control system for the vehicle in its new inclined orbit. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12439 10.30536/j.jtd.2005.v3.a812 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12439/9744 Copyright (c) 2025 J. Muliadi, Said D. Jenie, A. Budiyono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12440 2025-10-03T07:30:33Z ijoa:ART

KONTROLER GAIN SCHEDULING UNTUK RUDAL UDARA KE UDARA Andiarti, Rika A control system for an air-to-air guided missile is developed. Gain scheduling control technique is used to perform the missile flight toward a moving target. The simulation results show that the gain scheduling control technique is effective to obtain the desired missile performance. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12440 10.30536/j.jtd.2005.v3.a813 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12440/9745 Copyright (c) 2025 Rika Andiarti https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12441 2025-10-03T07:30:33Z ijoa:ART

KARAKTERISTIK DINAMIKA STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Triharjanto, Robertus Heru Sugiarmadji HPS The TUBSAT-LAPAN micro satellite is planned to be launched using PSLV rocket. The design constraints of the mechanical system of the satellite are able to accomodate structural requirment for PSLV, which are first resonance frequency in the rocket longitudinal axis 90 Hz and first resonance frequency in the lateral axis 45 Hz. Therefore, the structural dynamic characteristic data of the satellite is important to be evaluated, such as natural frequency and mode shapes of the satellite structures, The normal modes analysis made is done usingh Finite Element Methods commercial software NASTRAN. To simplify the FEM modeling the satellite components inside the compartmens is replaced by a dummy load simulating their contribution to satellite mass, centerof gravity and inertia, which was made by the same material as the satellite's structure, i.e. Al-Alloy 2024T351. Meanwhile, the FEM modeling for both the UHF antena used the Stainless Steel materials as the real antena. The analysis results show that the lowest local natural frequency of the satellite occurs on the UHF antena. The first natural frequency of the antena structures in lateral direction is 52,29 Hz. The first natural frequency of the satellite in lateral direction 151.47 Hz completing the satellite integration, vibration test was done to the satellite. The test shows that the first global frequency is 72-75 Hz in the lateral direction and 148 Hz in longitudinal direction. Structural dynamic characteristic of TUBSAT_LAPAN micro satellite in free flying condition are also analyzed using no-constraint condition to check the safe separation clearance scenario. The results show that the first natural frequencies for satellite structures (combination) become very small, less than 0.00032 Hz. But, the lowest of the first natural frequency for UHF antena structures is almost constant, 52.30 Hz in lateral direction. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12441 10.30536/j.jtd.2005.v3.a814 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12441/9746 Copyright (c) 2025 Robertus Heru Triharjanto, Sugiarmadji HPS https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12442 2025-10-03T07:30:33Z ijoa:ART

ANALISIS BEBAN TEKUK KRITIS STRUKTUR SANDWICH BAHAN KOMPOSIT PADA SIRIP ROKET RX LAPAN Putra, Ronald Gunawan The using of sandwich structure on the tail of RX LAPAN Rocket offers several advantages compared to conventional structure, such as lightweight, higt stiffiness and good fatigue property. But, one of the problems is its weakness under compressive loads, especially when there is a delaminated area. Buckling modes that often occur in sandwich structure due to compressive loads is overall buckling. This paper will analyze the influence of delamination over critical buckling load with finite element method using 2-D modeling. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12442 10.30536/j.jtd.2005.v3.a815 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12442/9747 Copyright (c) 2025 Ronald Gunawan Putra https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12443 2025-10-03T07:30:33Z ijoa:ART

RANCANGAN DAN ANALISIS STRUKTUR SUDU TURBIN ANGIN LPN 10000 E Atmadi, Sulistyo Hartono, Firman Structure of the LPN 10000 E wind turbine blade has been manufactured and its structural analysis to find out the strenght of this structure during its operation has also been conducted. The method of aero bending moment and centrifugal bending moment and load has been used while neglegting frcitional and torsional load. The analysis is obtained for composite blade strengthened by high strength carbon unidirectional reinforcement composite. With safety factor of 1.3 minimum, it was concluded that the blade is strong enough to use at its designed operational load. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12443 10.30536/j.jtd.2005.v3.a816 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12443/9748 Copyright (c) 2025 Sulistyo Atmadi, Firman Hartono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12444 2025-10-03T07:30:33Z ijoa:ART

NITROSELULOSA DARI KULIT BATANG PISANG Satibi, Loekman This paper describes the manufacturing of nitrocellulose from the bark of banana tree as a model of the manufacturing from other sources of cellulose in general. The process can be devided into two steps. The fisrt step is the production of cellulose from the bark of banana tree by coustic soda process while in the second step the cellulose obtained then subjected to nitration procces using nitric acid and controlled by addition of sulfuric acid. In the fisrt step dry bark of banana tree digested using coustic soda solution. Coustic soda concentration, the weight ratio of coustic soda solution to dry bark of banana tree, and digestion time were taken as process variables. The results of the fisrt step concludes that the highest cellulose yields is 33,36 percent, obtained at the digestion operating condition of NaOH concentration 3,33 percent, ratio of NaOH solution to dry bark of banana tree 12per1 and digestion time 4,5 hours and permanganate number is 17,27, while the lowest permanganate number of cellulose is 14,40 in accord with almost the lowest yield 26,58 percent obtained at the digestion process condition of NaOH concentration 5 percent, ratio of NaOH solution to dry bark of banana tree 12per1 and digestion time 4,5 hours. These results are almost in accord with the prediction. The second step operation will be accomplished after the completion of the equipments. Sulfuric acid solution is used to control nitration process based on the third Le Chatelier chemical principle. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12444 10.30536/j.jtd.2005.v3.a817 Indonesian Journal of Aerospace; Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12444/9749 Copyright (c) 2025 Loekman Satibi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12445 2025-10-03T07:30:33Z ijoa:ART

MEMPREDIKSI FREKUENSI FUNDAMENTAL PADA MODEL SATELIT INASAT.1 PADA SUMBU X DENGAN MENGGUNAKAN METODA SPEKTRUM DAYA Wahono, Daryono Restu The fundamental frequency of UUT can be predicted using power spectral density method with random signal input source. The test execution of INASAT 1 satellite shall meet the following standard of Indian Space Research Organisation (ISRO) in Polar Satellite Launch Vehicle (PSLV) auxiliary satellite user's manual a fundamental frequency in Lateral axis X 45 Hz. these values are with fixed boundary conditions at the spacecraft mounting interface and include the contribution of separation system. The test result of LAPAN satellite model INASAT.1 for X axis is predicted for fundamental frequency. It was detected that resonance frequency started at 80 Hz and peak accured at 120 Hz BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12445 10.30536/j.jtd.2004.v2.a799 Indonesian Journal of Aerospace; Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12445/9750 Copyright (c) 2025 Daryono Restu Wahono https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12446 2025-10-03T07:30:33Z ijoa:ART

PENGARUH PELARUT (ETIL BENZENA), PERBANDINGAN STYRENE BUTADIENE RUBBER (SBR) TERHADAP STIREN, DAN JUMLAH INISIATOR (BPO) PADA PEMBUATAN HIGH IMPACT POLYSTYRENE (HIPS) Wahyuni, Dwi High impact polystyrene (HIPS) is the widely used material now, and also for the aerospace material as a communication instrument system and an electrical insulation. In order to produce HIPS, there are a view method which can be executed. In this case, the research is executed by the copolymerization processes of styrene butadiene rubber (SBR) solution in styrene. Variables which influence to the result properties (HIPS) are the SBR to styrene ratio, the solvent (ethyl benzene), the benzoyl peroxide initiator (BPO). The properties of the product are tensile strength, impact strength, softening point, melting point and the hardness. The result showed that the properties of the HIPS product was near of the HIPS high heat. The optimal processes condition was the solvent to the styrene monomer ratio was 0.05492, the SBR to the styrene ratio was 0.1236 and the BPO to the styrene ratio was 0,0003. The properties of the HIPS product were: the impact strength was (519-1215) N per cm, the tensil strength not more than was 106 N per cm, the elongation was (36-54) percent and the hardness was (65-69) shore A. This properties achieved at the mixing polymerization processes 4 scale in 11-12 hours, the early mixing at 4 scale 1 hours, the cutting chain 2 drops. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12446 10.30536/j.jtd.2004.v2.a800 Indonesian Journal of Aerospace; Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12446/9751 Copyright (c) 2025 Dwi Wahyuni https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12447 2025-10-03T07:30:33Z ijoa:ART

PENELITIAN DAN RANCANGAN OPTIMAL TURBIN PENGGERAK TEROWONGAN ANGIN SUBSONIK SIRKUIT TERBUKA LAPAN Atmadi, Sulistyo In an effort to improve flow condition and flow speed up to 50 m per s inside LAPAN Subsonic Wind Tunnel, an existing power system and turbine has to be redesigned. Specifications for these requirments have been determined and calculated for the required power and aerofoil type and their dimensions. A method based free vortex design was used to get optimal result. The optimization result produced a turbine with 3 m diameter, with 10 blades, 1.5 m hub diameter. A D RAF PROPELLER aerofoil type was used to produce 230 HP power and 1824 Nm torque, with an efficience 89 percent. This result was considered both technically and economically. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12447 10.30536/j.jtd.2004.v2.a801 Indonesian Journal of Aerospace; Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12447/9752 Copyright (c) 2025 Sulistyo Atmadi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12448 2025-10-03T07:30:33Z ijoa:ART

EMISI RADIASI MEDAN ELEKTROMAGNETIK KABEL KOMUNIKASI BROADBAND Mardjoeki, Sumami Broadband communication technology transmits data in high speed. Broadband communications using aerial cable as its transmission medium, will radiate electromagnetic field into its surrounding environment. The radiated electromagnetic field is a potential source of interference, especially with other frequency radio devices, which are operated in the same frequency range. In this case, the long wires carrying broadband signals will generate a radio frequency electromagnetic emission. This paper makes a study about interference from the xDSL (Digital Subcriber Line) communication broadband signals, which using an existing telephone subscriber loop cable network as its transmission medium. Generally, the subsciber loop cable is an aerial cable. In order to make the radiation influence does not impact the other radio equipment performance, the standard CISPR 22 regulates the limits, which are 35 dBuV (average) at a distance of 30 for Class A (industrial) equipment and at a distance of 10 m for Class B (residential) equipment. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12448 10.30536/j.jtd.2004.v2.a802 Indonesian Journal of Aerospace; Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12448/9753 Copyright (c) 2025 Sumami Mardjoeki https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12449 2025-10-03T07:30:33Z ijoa:ART

PENELITIAN MEKANISME STALL AKIBAT PERKEMBANGAN GELEMBUNG SEPARASI PADA SAYAP NACA 0017 SECARA EKSPERIMEN DI TEROWONGAN ANGIN SUBSONIK Aribowo, Agus This paper presents the results of investigation the separation buble which growing and burst on aerofoil NACA 0017 with effect mechanism of stall in the subsonic wind tunnel. Experiment have done on wind speed 20 m per s and 30 m per s. The data pecked from the orifice of pressure with interval 2 degree until stall position. The result was separation buble which growing on the airfoil, going to ahead of airfoil together with increasing the Reynolds number. After touching, the flow appeared to separate from the upper airfoil without reattachment. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12449 10.30536/j.jtd.2004.v2.a803 Indonesian Journal of Aerospace; Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12449/9754 Copyright (c) 2025 Agus Aribowo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12451 2025-10-03T07:30:33Z ijoa:ART

RANCANG-BANGUN SISTEM FLIGHT-RECORDER SEDERHANA UNTUK PELUNCURAN ROKET Widada, Wahyu In the rocket launch campaign, the telemetry system is very important system in order to send various data from the sensor to the base-station. However the signal of telemetry is not usually in good condition, and the data is very dificult to analyze. In this paper described the method to backup the sensor data by use of flight-recorder. It was very useful if the recovery of payload was successful, and the data flight can be analyze. The system used 2 wire serial eeprom with 131.071 byte of memory and 6 input for analog channels. The speed recording was 10 ms or 100 data per second. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article https://ejournal.brin.go.id/ijoa/article/view/12451 10.30536/j.jtd.2004.v2.a805 Indonesian Journal of Aerospace; Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara 3032-0895 Copyright (c) 2025 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12454 2026-05-11T04:07:28Z ijoa:ART

PENGARUH TEMPERATUR SISTEM PADA FIGURE OF MERIT STASIUN BUMI PITA S DAN PITA X Surjo, Achmadi One of the veri important in a satellite communications system is the figure of merit for space segment as well as for the ground segment. The parameter which will be discussed in this paper is the figure of merit of a ground station of S band and X band for remote sensing system application. The parameters which influences it are antenna gain and temperature of system. The antenna which will be used is parabola antenna whose magnitude gain depends on diamter and efficiency of reflector. While the ground station antenna moves to track the desired satellite, so the elevation angle changes as well as the azimuth angle. On S band system influence of rain cab be ignored, while on the X band the influence needs to be considered. From the analysis conducted at 0.1 time percentage, the result is influence of rain to the "figure of merit is necessary to be estimated. BRIN Publishing 2026-05-11 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12454 Indonesian Journal of Aerospace; Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12454/9758 Copyright (c) 1970 Achmadi Surjo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12455 2025-12-23T03:42:08Z ijoa:ART

PENELITIAN PEMBUATAN POLI METIL METAKRILAT Wahyuni, Dwi Dewi, Sri Rukmini The poly methyl methacrylate (PMMA) research has been excecuted. Methyl methacrylate is polymerized by the free radical inisiation with the suspension condition using benzoyl peroxyde inisiator, water as a solution and the gelatine stabilizer, in this reseaarch is executed as a standard ratio (part per part:monomer : water : stabilizer = 100 : 350 : (0.1 1) with the inisiator to monomer ratio variation (part per part) are: 0.1 per 50; 0,175 per 50; 0,25 per 50; 0,25 per 50, the temperature variation are : 30 degree C, 45 degree C, 60 degree C and the time polymerization until 320 minutes. The result showed that the optimum monomer polymerizeation was at the inisiator to monomer ratio 0,25 per 50, the temperature at 45 degree C and at the time polymerization until 300 minutes with the monomer conversion was 86 percent. The Infra Red Spectroscopy analyses showed that there are poly methyl methacrylate in the product. The Gas Liquid Chromatography analysis showed the evolution of the monomer (methil methacrylate concetration. BRIN Publishing 2025-12-23 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12455 Indonesian Journal of Aerospace; Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12455/9759 Copyright (c) 1970 Dwi Wahyuni, Sri Rukmini Dewi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12484 2025-10-03T07:30:33Z ijoa:PRE

Preface Lapan, Lapan - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12484 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12484/9783 Copyright (c) 2025 Lapan Lapan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12485 2025-10-03T07:30:33Z ijoa:ART

KONTROL JARAK JAUH BERBASIS MULTI TONE UNTUK SISTEM TERMINASI PENERBANGAN ROKET (MULTI - TONE BASED REMOTE CONTROL FOR ROCKET FLIGHT TERMINATION SYSTEM) Widada , Wahyu Sistem Terminasi Penerbangan Multi-tone Roket UAV Tulisan ini membahas desain dan prototip komunikasi jarak jauh untuk Flight Termination System (FTS). FTS beroperasi di pita frekuensi UHF 400-470 MHz. Sistem ini menggunakan tiga multi-frekuensi tone untuk telekomando ke wahana terbang. Simulasi dan desain telah dianalisis untuk membuat sistem komunikasi yang handal berdasarkan campuran tiga sinyal tone bersama-sama untuk radio dengan lebar pita sub-carrier 3 KHz. Frekuensi tone yang digunakan untuk remote control adalah 1050, 1550, dan 2550 Hz. Beda frekuensi minimal dari masing-masing sinyal tone adalah 0.5 KHz. Hasil percobaan menunjukkan sinyal multi-tone terdeteksi dengan benar sesuai dengan hasil yang telah didesain dan simulasikan. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article https://ejournal.brin.go.id/ijoa/article/view/12485 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 82-91 3032-0895 Copyright (c) 2025 Wahyu Widada https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12487 2025-10-03T07:30:33Z ijoa:ART

ANALISIS PERANGKAT LUNAK SIMULATOR BINTANG UNTUK PENGUJIAN STAR SENSOR (ANALYSIS SOFTWARE STAR SIMULATOR FOR STAR SENSOR TESTING) Ubay, Muh. Sulaiman Nur Saifudin, M. Arif Saifudin Sikap satelit Sensor bintang Simulator bintang Sensor bintang merupakan sensor yang banyak digunakan dalam determinasi sikap satelit (attitude determination) karena tingkat akurasi yang tinggi dalam menghasilkan data sikap satelit. Teknologi sensor bintang terus dikembangkan untuk menghasilkan kinerja yang lebih baik sehingga secara khusus akan meningkatkan performa dan reliabilitas ADCS (Attitude Determination and Control System) satelit. Pada karya tulis ilmiah ini dilakukan analisa terhadap perangkat lunak simulator bintang untuk pengujian sensor bintang dengan tujuan agar pengujian sensor bintang dapat dilakukan tanpa terkendala oleh tempat dan waktu. Posisi bintang yang disimulasikan bersifat statis untuk menguji konsistensi pembacaan data bintang. Simulator bintang yang dibangun menunjukkan kinerja simulator bintang statik sudah cukup baik, dari sisi spesifikasi perangkat keras telah menghasilkan citra bintang sesuai dengan kebutuhan yaitu eror piksel < 80 miliderajat. Dari hasil pengujian sensor bintang dapat dilihat bahwa reading stability simulator menghasilkan data telemetri yang stabil dengan nilai error attitude yaitu ï„RA=0, ï„DE=0, ï„AZ=0. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12487 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 92-100 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12487/9787 Copyright (c) 2025 uh. Sulaiman Nur Ubay, M. Arif Saifudin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12490 2025-10-03T07:30:33Z ijoa:ART

PENENTUAN KANDUNGAN OKSIDATOR BERDASAR REAKSI STOIKIOMETRI DAN STRUKTUR KRISTAL DALAM RANGKA ADOPSI FORMULASI PROPELAN HLP (DETERMINATION OF OXIDATOR CONTENT BASED ON STOICHIOMETRICAL AND CHRYSTAL STRUCTURE ON PURPOSE OF HLP PROPELLANT FORMULATION ADOPTIO Hartaya, Kendra Abdillah, Luthfia Hajar Ardianingsih , Retno Oksidator Propelan HLP Telah dilakukan penentuan komposisi propelan LAPAN berdasar formulasi propelan HLP. Penentuan komposisi propelan LAPAN berdasar pada stoikiometri reaksi pembakaran HTPB dan pembakaran Al oleh AP. Berdasarkan stoikiometri ini diperoleh prosentase AP adalah 68% sehingga HTPB 31% dan Al 1%. Selanjutnya rasio AP kasar (200μm) terhadap AP Halus (70μm) ditentukan berdasar asumsi bahwa struktur yang terbentuk oleh sekumpulan butiran AP adalah Body Center Cubic (BCC). Berdasar asumsi BCC, jika radius AP kasar R, maka radius AP halus r=41,42%, atau jika AP kasar 200μ maka AP halus 83μm. Dalam satu satuan sel BCC, terdapat 2 butir AP kasar dan 3 butir AP halus sehingga rasio AP kasar-AP halus = 2/3 AP kasar yang sesuai dengan propelan HLP adalah ukuran 180-280μ (rata-rata ukuran r=165 μ, ruang kosong r=29.10-4μ). Karena tidak ditemukan supplier AP ukuran kurang dari 100μ, diduga AP halus propelan HLP adalah rekayasa dari AP ukuran besar, atau diperoleh melalui kerjsasama khusus. Komposisi propelan Lapan berdasar formulasi HLP, mengandung AP 68% (campuran AP Kasar dan AP halus), AP kasar 200μ (R) AP halus 83μ (r=41,42%) atau AP kasar 165μ, AP halus 29.10-4μ. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12490 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 102-114 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12490/9789 Copyright (c) 2025 Kendra Hartaya, Luthfia Hajar Abdillah, Retno Ardianingsih https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12492 2025-10-03T07:30:33Z ijoa:ART

IMPLEMENTASI ENCODER REED-SOLOMON PADA FPGA BERBASIS CCSDS (REED-SOLOMON ENCODER IMPLEMENTATION ON FPGA BASED ON CCSDS) Hakim, Patria Rachman Rahman, Abdul Rahman Amin, Deddy El Roza , Widya Rahim , Elvira Channel coding Encoder Reed-Solomon PDH FPGA CCSDS Salah satu fungsi sistem Payload Data Handling (PDH) pada sebuah satelit adalah melakukan channel coding untuk data citra satelit. Consultative Committee for Space Data Systems (CCSDS) telah merekomendasikan penggunaan encoder Reed-Solomon (RS) untuk keperluan channel coding tersebut. Untuk dapat merealisasikan transmisi dengan laju data yang tinggi, maka implementasi algoritma encoder RS pada sitem PDH satelit membutuhkan Field Programmable Gate Array (FPGA). Penelitian ini bertujuan untuk merancang modul encoder RS(255,223) berbasis CCSDS dan mengimplementasikan encoder tersebut pada FPGA dengan desain rangkaian yang lebih optimal dibandingkan dengan encoder RS komersial (IP-core). Berdasarkan hasil pengujian yang telah dilakukan, encoder yang dirancang memiliki beberapa kelebihan dalam hal efisiensi gerbang logika yang digunakan dan tingkat kinerja data keluaran yang dihasilkan. Selain itu, pada penelitian ini juga dikembangkan metode encoding paralel yang akan diterapkan pada sistem PDH satelit. Hasil pengujian menunjukkan bahwa dengan menggunakan metode tersebut, data keluaran yang dihasilkan encoder memiliki laju data yang lebih tinggi dan tidak membutuhkan data dummy untuk melengkapi data keluaran. Kedua hasil tersebut diharapkan dapat mendukung pengembangan sistem PDH satelit yang dilakukan di Pusat Teknologi Satelit saat ini. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12492 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 116-127 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12492/9791 Copyright (c) 2025 Patria Rachman Hakim, Abdul Rahman, Deddy El Amin, Widya Roza , Elvira Rahim https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12493 2025-10-03T07:30:33Z ijoa:ART

STUDI PARAMETRIK PENGARUH ROUGHNESS TERHADAP PROFIL KECEPATAN LAPISAN BATAS PADA SIMULASI ATMOSPHERIC BOUNDARY LAYER DI WIND TUNNEL (PARAMETRIC STUDY OF ROUGNESS INFLUENCE TOWARD THE BOUNDARY LAYER VELOCITY PROFILE ON THE SIMULATION OF ATMOSPHERIC BOUNDAR Subagyo, Subagyo ABL Angin Gaya Bangunan Simulasi Eksperimen Pengaruh kekuatan angin yang bekerja pada gedung tinggi sangat penting untuk dipahami berkaitan dengan desain dan analisis bangunan tinggi. Hal ini diperlukan agar bangunan yang dirancang dapat memenuhi kriteria aman. Pengaruh angin dalam hal ini dipengaruhi oleh profil kecepatan angin yang merupakan kurva lengkung yang terletak di batas lapisan. Dalam hal ini lapisan batas biasanya disebut dengan Atmospheric Boundary Layer (ABL). ABL adalah bagian dari atmosfer yang berimbas langsung terhadap permukaan bumi. Profil kecepatan aliran pada ABL dapat memiliki gradien landai atau curam tergantung pada karakteristik dari permukaan hulu. ABL dapat diketahui dan direkonstruksi melalui dua metode yaitu eksperimen dan simulasi numerik. Penelitian rekonstruksi ABL dalam makalah ini menggunakan metode eksperimen. Dalam eksperimen atau percobaan, rekonstruksi ABL biasanya dilakukan dengan try and error, perlu untuk mengetahui kecenderungan parameter ABL untuk membuatnya lebih mudah dan lebih efektif dalam membangun ABL. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12493 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 128-138 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12493/9792 Copyright (c) 2025 Subagyo https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12503 2025-10-03T07:30:33Z ijoa:ART

PENGUJIAN SISTEM MUATAN PADA ROKET EKSPERIMEN LAPAN JENIS RKX–100, RTX–100 DAN RWX–200 (TESTING PAYLOAD SYSTEM IN ROCKET EXPERIMENTS LAPAN TYPE RKX-100, RTX-100 AND RWX-200) Kurdianto, Kurdianto Muatan Microcontroller Telemetri Muatan (Payload) berupa sensor pengindera gerak pada roket eksperimen merupakan hal yang sangat penting, karena dapat mengetahui gerakan roket sesuai dengan misi yang ditentukan. Dalam paper ini pengujian muatan roket yang berupa sistem pengindera gerak berbasis ATMEGA 32 dipaparkan. ATMEGA 32 sebagai microcontroller berfungsi untuk membaca dan memerintahkan input yang ada agar dapat ditampilkan di ground station setelah ada proses transmited dari telemetri Maxstream 900 MHz. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12503 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 140-144 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12503/9799 Copyright (c) 2025 Kurdianto https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12506 2025-10-03T07:30:33Z ijoa:ART

ANALISA KEAKURATAN SENSOR SUHU ANALOG MODUL APRS SATELIT LAPAN-A2 DENGAN MENGGUNAKAN MODUL UJI VALIDASI (ANALISYS OF ANALOGUE TEMPERATURE SENSOR ACCURACY ON LAPAN-A2 SATELLITE APRS MODULE USING VALIDATION TEST MODULE) Tahir, Andi Muhktar Amin, Deddy El APRS Satelit Lapan-A2 Sensor suhu Uji validasi Modul Automatic Position Reporting System (APRS) merupakan salah satu muatan Satelit Lapan-A2 (Lapan-Orari), sebuah mikro satelit yang mempunyai misi penanggulangan bencana alam. Modul APRS yang digunakan oleh Lapan-A2 merupakan produk komersial sehingga perlu dilakukan pengujian thermal sebelum diluncurkan, terutama untuk mengukur keakuratan data dari sensor suhu analog yang terdapat di dalamnya. Pengujian thermal dengan menggunakan thermal chamber VC3 4018 terhadap sensor analog selain berfungsi untuk mengukur temperatur dari APRS itu sendiri dan suhu ruang di sekitarnya, pada dasarnya juga bertujuan untuk mengetahui daya tahan modul APRS terhadap perubahan suhu saat Lapan-A2 berada di orbit.Dengan meletakkan sebuah sensor suhu dijital secara berdampingan langsung dengan sensor suhu analog dalam modul APRS, proses pengujian di dalam thermal chamber berlangsung. Sebagai acuan untuk proses validasi kedua sensor suhu tersebut, dipergunakan data suhu yang diperoleh dari dua sensor suhu dijital yang diletakkan di dalam thermal chamber selama proses pengujian dan data ini diproses di dalam sebuah modul mikrokontroler yang diberi nama modul uji validasi sebelum dikirim ke modul APRS, sehingga nantinya data akhir dari keempat sensor suhu keluar bersamaan sehingga dengan mudah dapat langsung dibandingkan. Hasil akhir yang berupa grafik temperatur terhadap waktu menunjukkan bahwa dengan menggunakan rentang kesalahan ±1°C, sensor analog dari modul APRS kurang akurat dalam memberikan data terutama pada saat temperatur diatas 30°C. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12506 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 140-144 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12506/9802 Copyright (c) 2025 Andi Muhktar Tahir, Deddy El Amin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12507 2025-10-03T07:30:33Z ijoa:ART

DESAIN DAN IMPLEMENTASI SISTEM PAKAR ANALISIS PERFORMANSI ANTENA SEASPACE AXYOM 5.1 BERBASIS WEB (DESIGN AND IMPLEMENTATION WEB BASED EXPERT SYSTEM FOR ANALIZING PERFORMANCE OF ANTENNA SEASPACE 5.1) Ardiansyah, Ardiansyah Hidayat, Arif Ramadhan, Panji Rachman Munawar , STA. Antena Log Penjejakan Secara umum, sistem pakar adalah sistem yang berusaha mengadopsi pengetahuan manusia ke komputer yang dirancang untuk memodelkan kemampuan menyelesaikan masalah seperti layaknya seorang pakar. Antena adalah salah satu perangkat utama dalam penerimaan data satelit penginderaan jauh. Alat ini digunakan di stasiun bumi. Fungsi utama antena adalah menerima data yang dipancarkan dari satelit ke bumi. Untuk mempermudah melakukan monitor dan analisis performansi antena secara waktu nyata diperlukan suatu aplikasi yang mampu bekerja secara otomatis dan dapat dimonitor dari jarak jauh. Aplikasi ini melakukan pengolahan log tracking satelit yang ada di ACU kemudian mengolah mendapatkan nilai C/N dan menampilkannya dalam bentuk web. Sebelumnya perekayasa membutuhkan waktu 1 jam dalam mengambil log, melakukan plot, analisis dan membuat kesimpulan. Aplikasi ini mampu memproses log file dan membuat keputusan setelah 1 menit satelit melewati jangkuan antena. BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12507 Indonesian Journal of Aerospace; Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara; 154-162 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12507/9807 Copyright (c) 2025 Ardiansyah, Arif Hidayat, Panji Rachman Ramadhan, STA. Munawar https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12511 2025-10-03T07:30:33Z ijoa:PRE

Preface -, - - BRIN Publishing 2025-07-09 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion application/pdf https://ejournal.brin.go.id/ijoa/article/view/12511 Indonesian Journal of Aerospace; Vol. 11 No. 2 Desember (2013): Jurnal Teknologi Dirgantara 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12511/9843 Copyright (c) 2025 - - https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12529 2025-10-03T07:30:34Z ijoa:ART

STABILITY AND CONTROLABILITY ANALYSIS ON LINEARIZED DYNAMIC SYSTEM EQUATION OF MOTION OF LSU 05-NG USING KALMAN RANK CONDITION METHOD Septiyana, Angga Hidayat, Kurnia Rizaldi, Ardian Suseno, Prasetyo Ardi Probo Jayanti, Eries Bagita Atmasari, Novita Ramadiansyah, M. Luthfi Ramadhan, Redha Akbar Stability Controlability equation of motion Dinamical System UAV This paper discusses the stability, control and observation of the dynamic system of the Lapan Surveillance UAV 05-NG (LSU 05-NG) aircraft equation. This analysis is important to determine the performance of aircraft when carrying out missions such as photography, surveillance, observation and as a scientific platform to test communication based on satellite. Before analyzing the dynamic system, first arranged equations of motion of the plane which includes the force equation, moment equation and kinematics equation. The equation of motion of the aircraft obtained by the equation of motion of the longitudinal and lateral directional dimensions. Each of these equations of motion will be linearized to obtain state space conditions. In this state space, A, B and C is linear matrices will be obtained in the time domain. The results of the analysis of matrices A, B and C show that the dynamic system in the LSU 05-NG motion equation is a stable system on the longitudinal dimension but on the lateral dimension directional on the unstable spiral mode. As for the analysis of the control of both the longitudinal and lateral directional dimensions, the results show that the system is controlled. BRIN Publishing 2020-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12529 10.30536/j.jtd.2020.v18.a3318 Indonesian Journal of Aerospace; Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara; 81-92 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12529/9853 Copyright (c) 2020 Angga Septiyana, Kurnia Hidayat, Ardian Rizaldi, Prasetyo Ardi Probo Suseno, Eries Bagita Jayanti, Novita Atmasari, M. Luthfi Ramadiansyah, Redha Akbar Ramadhan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12533 2025-10-03T07:30:34Z ijoa:ART

NUMERICAL INVESTIGATION ON THE FUSELAGE AIRFRAME OF LSU 05 NG AIRCRAFT Hafid, M. Nurrohmad, Abian Ramadhan, Redha Akbar finite element method stress analysis fuselage unmanned aircraft In this paper, numerical investigation on the fuselage structure of LSU 05 NG was carried out. This fuselage is designed to carry the payload up to 30 kg. Statical numerical analysis using finite element method was done using Simulia Abaqus. The fuselage structure that has been design consists of frame, longeron, and skin that can also be semi-monocoque structure. This airframe use combination of balsa and GFRP type of composite as the material. There are three load case: take-off condition, cruise condition, and landing condition. Tsai-hill failure criteria is used to investigate the strength of the composite structure due to the load that applied. Maximum stress from this calculation is 48 Mpa at the ground condition (take-off and landing) while the cruise stress analysis is 16 Mpa. The maximum tsai-hill criterion is 0,83. With such simulation results it can be said that the fuselage structure is still safe when operated and can also be optimized for several components so that the weight of the aircraft can be reduced. BRIN Publishing 2020-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12533 10.30536/j.jtd.2020.v18.a3327 Indonesian Journal of Aerospace; Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara; 93-104 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12533/9854 Copyright (c) 2020 M. Hafid, Abian Nurrohmad, Redha Akbar Ramadhan https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12538 2025-10-03T07:30:34Z ijoa:ART

A FINITE ELEMENT ANALYSIS OF CRITICAL BUCKLING LOAD OF COMPOSITE PLATE AFTER LOW VELOCITY IMPACT Ramadhan, Redha Akbar Suada, M. Giri Syamsudin, Hendri composite laminate delamination buckling Composite is a material formed from two or more materials that macroscopically alloyed into one material. Nowadays, composite has been generally applied as lightweight structure of aircraft. This is due to the fact that composites having high strength-to-weight ratio. It means the composites have the capability to take on various loads, despite their lightweight property. Laminate composite is one type of composite that has been generally used in aircraft industries. This type of composite is susceptible to low-velocity impact induced damage. This type of damage can be happening in manufacture, operation, or even in maintenance. Low-velocity impact could cause delamination. Delamination happens when the plies of laminated composites separated at the interface of the plies. This type of damage is categorized as barely visible damage, means that the damage couldn’t be detected with visual inspection. Special method and tool would be needed to detect the damage. Delamination will decrease the strength of the laminated composite. Delamination can be predicted with numerical simulation analysis. With increasing capability of computer, it is possible to predict the delamination and buckling of laminated composite plate. This research presents the comparisons of buckling analysis results on laminated plate composite and damaged laminated plate composite. By the result of LVI simulation, it is shown that low velocity impact of 19.3 Joule causing 6398 mm2 C-Scan delamination area inside the laminated composite. The delamination causing structural instability that will affect buckling resistance of the plate. The result of analysis shows that the existence of delamination inside laminate composite will lower its critical buckling load up to 90% of undamaged laminate’s critical buckling load. BRIN Publishing 2020-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12538 10.30536/j.jtd.2020.v18.a3328 Indonesian Journal of Aerospace; Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara; 105-116 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12538/9855 Copyright (c) 2020 Redha Akbar Ramadhan, M. Giri Suada, Hendri Syamsudin https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12540 2025-10-03T07:30:34Z ijoa:ART

Effect of Isomer Composition of Hydroxy Terminated Polybutadiene (HTPB) in Low Shear Flow Behavior (Efek dari Komposisi Isomer dari Hydroxy Terminated Polybutadiene (HTPB) terhadap Sifat Alir dalam Geseran Rendah) Restasari, Afni Abdillah, Luthfia Hajar Ardianingsih, Retno Ardianingsih Budi , Rika Suwana Microstructure Viscosity Hydroxy Terminated Polybutadiene Flow behaviour Shear thickening HTPB is the ultimate component of matrix builder for high-filled composite materials. Flow behavior of HTPB in low shear is crucial in casting the composite. Considering the characteristics of hydrocarbon, this work aims to investigate the effect of microstructure composition of HTPB on its flow behavior. In this work, HTPB with different composition of 1,4-cis, 1,2-vinyl and 1,4-trans microstructures were used. Fourier-Transform Infra-Red spectroscopy (FT-IR) was used to determine the composition. It was calculated as a ratio of peak area of 710, 910 and 970 cm-1 for 1,4-cis, 1,2-vinyl, 1,4-trans isomers respectively. Viscosity was measured using a rotational viscometer at various low shear rates. It is found that HTPB with high 1,2-vinyl/1,4-trans isomers shows shear thickening behaviour, distinguished significantly from Newtonian flow of the others. It is suggested that mechanism of shear thickening involves a certain configuration of 1,2-vinyl and 1,4-trans isomers that builds different degrees of flow resistance from one to other shear layers. The configuration and flow resistance changes among layers as shear increases.   BRIN Publishing 2020-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12540 10.30536/j.jtd.2020.v18.a3341 Indonesian Journal of Aerospace; Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara; 118-128 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12540/9856 Copyright (c) 2020 Afni RestasariAfni Restasari, Luthfia Hajar Abdillah, Retno Ardianingsih, Rika Suwana Budi https://creativecommons.org/licenses/by-sa/4.0

oai:ejournal.brin.go.id:article/12546 2025-10-03T07:30:34Z ijoa:ART

COMPARATIVE STUDY OF WING LIFT DISTRIBUTION ANALYSIS USING NUMERICAL METHOD Septiyana, Angga Hidayat, Kurnia Rizaldi, Ardian Wijaya, Yusuf Giri Wing Lift Distribution CFD 3D Panel Methode LLT VLM Numerical Methode This research focuses on calculating the force distribution on the wings of the LSU 05-NG aircraft by several numerical methods. Analysis of the force distribution on the wing is important because the wing has a very important role in producing sufficient lift for the aircraft. The numerical methods used to calculate the lift force distribution on the wings are Computational Flow Dynamics (CFD), Lifting Line Theory, Vortex Lattice Method and 3D Panel Method. The numerical methods used will be compared with each other to determine the accuracy and time required to calculate wing lift distribution. Because CFDs produce more accurate estimates, CFD is used as the main comparison for the other three numerical methods. Based on calculations performed, 3D Panel Method has an accuracy that is close to CFD with a shorter time. 3D Panel Method requires 400 while CFD 1210 seconds with results that are not much different. While LLT and VLM have poor accuracy, however, shorter time is needed. Therefore to analyze the distribution of lift force on the wing it is enough to use the 3D Panel Method due to accurate results and shorter computing time.   BRIN Publishing 2020-12-27 info:eu-repo/semantics/article info:eu-repo/semantics/publishedVersion Peer-reviewed Article application/pdf https://ejournal.brin.go.id/ijoa/article/view/12546 10.30536/j.jtd.2020.v18.a3349 Indonesian Journal of Aerospace; Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara; 129-139 3032-0895 eng https://ejournal.brin.go.id/ijoa/article/view/12546/9859 Copyright (c) 2020 Angga Septiyana, Kurnia Hidayat, Ardian Rizaldi, Yusuf Giri Wijaya https://creativecommons.org/licenses/by-sa/4.0 02881917b0c63eb788d1ea9a1a594a11