Design of aeroload simulator for the test of guided missile servoactuation system

유도무기 구동장치의 동특성 실험을 위한 공력부하 시뮬레이타의 설계

A design of aeroload simulator is proposed which is used for the dynamic test of guided missile servoactuation system. Since the simulator is linked to the servoactuation system, it is a two-input one-output system. The mathematical model of the aeroload simulator is derived and the root-locus method is applied to design compensator to improve the stability, response speed and accuracy of the system. Computer simulations are done to verify the goodness of the system design.