Modeling and simulation of aircraft guidance with over-gravity compensation

In order to improve the attack effect from the top of maneuver target for air-to-ground missile, three-dimensional proportional navigation model with over-gravity compensation is established based on the relative motion equations. Three-dimensional ballistic trajectory of the missile attacking target is simulated based on the guidance and control closed-loop circuit. The effect of the over-gravity compensation proportional navigation parameters on the flight characteristics is evaluated. The simulation results indicate the effectiveness of the proposed navigation law. In addition, the theoretical analysis results are also verified.