Guidance and Control System Design of a Surface-to-Air Missile Based on 122 mm Rocket
DOI:
https://doi.org/10.55981/ijoa.2025.9041Keywords:
proportional navigation, flight control, flight dynamics, missile, guidanceAbstract
This paper applies and analyzes the design of a proportional navigation guidance
and control system for a 122 mm rocket platform. The research involves modeling missile
dynamics, guidance systems, and control systems. The missile dynamics model relies on
the 6 DOF (Degrees of Freedom) equation for a rigid body, with aerodynamic data obtained
from the Missile Datcom program. The propulsion model is generated by a generic
thrust profile of a 122 mm unguided rocket. The guidance system model is based on the
proportional navigation guidance law, and the control system model employs the Linear
Quadratic Regulator (LQR) method. Modeling is conducted using Simulink software, and
simulations encompass various scenarios. The analysis considers aspects such as missile
trajectory, acceleration command, actual acceleration, control surface deflection, and the
time required to hit the target. The simulation results indicate the missile’s capability to
intercept targets under numerous conditions, although limitations are observed in specific
target scenarios where interception is not achievable.
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