The missile can use the direct force control of orbit control engine to compensate for the shortage of aerodynamic force or use the direct force of attitude control engine to improve the response speed of aerodynamic overload. Attitude control engine and orbit control engine installed on the missile body can make full use of the efficiency of direct force, reduce the use restriction and improve the missile performance. The problem to be solved is the mutual interference between attitude and orbit control engines. This paper presents a design method of composite controller, which can realize the stability control of missile under the working conditions of attitude control engine and orbit control engine. The control mode of air defense missile in the world has changed fundamentally, that is, from the control mode using only aerodynamic force to the compound control mode of aerodynamic force and direct lateral force. For example, the PAC-3 missile defense system developed by the United States, the 9M96E/9M96E2 equipped by the Russian S-300 missile defense system and the Aster-30, thermostatic element a new generation of European air defense missile, all of these missiles adopt the combined control of aerodynamic force and direct lateral force.
Compared with the traditional aerodynamic control method, the composite control method has many advantages.
The most important thing is to improve the response time of the interceptor, increase its limit available overload and increase its maneuverability, so as to improve the guidance accuracy. The direct force control mode of moment type is mainly used to improve the dynamic response speed of missile attitude and ultimately to improve the dynamic response speed of missile control force. The jet device of force control mode is installed in the centroid position, and the thrust regulation has the form of proportional regulation and pulse width modulation. Pulse width modulation can be equivalent to proportional form. Based on the data of model surface-to-air missile, this paper studies the design of a composite controller for pitch loop with the participation of a proportional control attitude-orbit control engine. From the above simulation figures, it can be seen that adding attitude control engine can improve the corresponding speed of aerodynamic overload, increase the rail control engine, and make up for the lack of aerodynamic power. The design method does not change the stability of the system.