气动力/直接力复合导弹鲁棒控制器设计

Design of Robust Controller for the Aerodynamic/Reaction-jet Compound Control Missile

提出了一种气动力/直接力复合控制导弹在舵机层面进行复合控制的鲁棒控制器设计方法,即空气舵与直接力喷流机构看作是复合舵系统模型.该方法在完成复合舵系统建模的基础上,利用参数空间方法对等效舵机系统进行设计,以确保在喷流因子变化时的鲁棒性。最后,通过仿真验证了该方法的可行性。

A new method of design multi-controller missile by using aerodynamic/reaction-jet is presented. This multi-control system can be used as a multiple actuator which includes an aerodynamic actuator and reaction-jet actuator. In the first part, the model of the multiple actuators is given, then, the method of designing the multiple actuators by using parameter method is demonstrated. Finally it is proved that this multiple actuator has robust performace for the parameter change by simulation.