스트랩다운 탐색기를 탑재한 유도탄의 유도루프 연구

초록

This paper addresses the method of guidance loop design for missiles with a strapdown seeker. Firstly, the angular acceleration and the rate for look angle are estimated by the      filter. The look angle rate is then compensated by using the estimated angular acceleration and the time delay due to the seeker processing. By adding the compensated look angle rate to the body rate measured the rate, we produce the delay compensated line-of-sight rate. The guidance loop includes PID controller to guarantee the stability even if the errors in the seeker time delay is introduced. After the stability analysis for the linear guidance loop, the performance of the designed guidance loop is verified through full nonlinear 6-DOF simulations.