Gliding Extended Range Projectile Flight Control And Power Steering Gear Performance Analysis

Gliding extended range projectile is one of the long-range precision munitions in the world. This paper is aiming at a type of gliding extended range projectile. The corresponding coordinates are defined. The six-free degree rigid body trajectory equations are established, based on the analysis of the forces and the moments acted on the projectile. And also the ballistic simulation program is provided. The disturbed motion equations are obtained by linearzing and simplifying the ballistic equations by the method of small disturbance. Under some assumptions, the disturbance of the gliding extended range projectile can be divided into longitudinal disturbed motion and lateral disturbed motion according to the actual flight conditions. The transfer functions of two channels are induced by the coefficient freezing method. Take longitudinal disturbed motion for example, the stability and the controllability of the gliding extended range projectile are investigated. According to the requirement of the control of the projectile, an appropriate model of the electric actuator is established. And the parameters of electric actuator are chosen. At last, the close loop of the electric actuator system is formed. And it was brought into the longitudinal control system. PD controlling strategy is adopted in the pitch angle close loop; while PID controlling strategy is adopted in the height close loop. Simulink Response Optimization Block is used to choose the coefficient of the PD/PID controller. Time domain analysis The corrector is determined by the frequency domain analysis. Simulation results show that the electric actuator system designed above satisfy the targets of time-domain and frequency domain, and also the longitudinal control system. They are all applicable for the control of gliding extended range projectile.