Adaptability Research of Time-frequency Characteristics on Actuator and Flight Control System at High Angle of Attack Missile

The control ability of the missile is the main factor limiting the performance of system, the requirements for the rudder system must be completed in the early stage of missile flight control design stage, otherwise, it will lead to the performance index of rudder system and flight control system does not match. This paper is based on the law of the autopilot structure to overload, firstly, a method of composite loop index demonstration of minimum phase systems and non-minimum phase system is given, the maximum rudder angle and the maximum rudder angle velocity are obtained, the relationship between the stabilization loop bandwidth, frequency bandwidth of actuator and a flexible mode are given. With the help of Matlab computer simulation method, the fixed-point calculation results typical condition are given, the result can be used as the initial design stage of missile flight control of rudder system design constraints and control margin reference.