以某型空空导弹为对象,对初始段敏捷转弯控制方法进行研究。建立了气动力/推力矢量复合控制空空导弹的姿态控制系统模型,利用时标分离的思想将其分为快、慢子系统,并利用动态逆方法对子系统分别进行控制律的设计,最后在考虑导弹各个环节非理想因素的情况下,对导弹进行了全耦合状态下三通道联合数字仿真。仿真结果表明,所提出的控制方法使系统具有较好的跟踪性能,实现了通道间的解耦,说明了该方法的正确性和有效性。

The control method for agile turn phase of some certain air-to-air missile was investigated. The dynamic model of air-to-air missile using aerodynamic/thrust vector complex control was established. With the idea of time scale separation, the attitude kinematical and dynamical systems of the missile were divided into fast subsystem and slow subsystem. Then the control law of each subsystem was designed using the dynamic inversion control. Finally, under the condition that each portion of the missile was true, and three channels were complete coupling, simulation tests were made. The simulation shows that the control system has preferably tracking performance, and proves the correctness and effectiveness of the method.