高超声速飞行器拦截中制导律设计  

Design of midcourse guidance law for intercepting hypersonic vehicle

作　　者：王禄 王志刚[1,2] WANG Lu;WANG Zhi-gang(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Aerospace Flight Dynamics,Xi’an 710072,China)

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]航天飞行动力学技术国家重点实验室,陕西西安710072

出　　处：《飞行力学》2019年第6期58-62,78,共6页Flight Dynamics

摘　　要：针对拦截高超声速飞行器的要求,基于最优控制理论,利用积分滑模的思想设计了拦截高超声速飞行器的中制导律。分析了拦截弹的中制导与末制导交班条件,利用二次型最优控制方法求得最优制导律;面对目标的机动情况,利用积分滑模控制方法对最优制导律进行改进,最终得到积分滑模最优中制导律。仿真结果表明,所设计的中制导律不但能够满足最优制导律的约束条件,还能够降低过载的需求,抑制视线角速度的波动,具有良好的制导性能。According to the requirement of intercepting hypersonic vehicle, the midcourse guidance law of intercepting hypersonic vehicle is designed based on optimal control theory and integral sliding mode. The handover conditions of interceptor’s midcourse guidance and terminal guidance are analyzed, and the optimal guidance law is obtained by using quadratic optimal control method. Aiming at the target maneuvering situation, the optimal guidance law is improved by using the integral sliding mode control method. Thus the integral sliding mode optimal midcourse guidance law is finally obtained. Simulation results show that the integrated sliding mode guidance law can not only satisfy the constraint conditions of the optimal guidance law, it can also reduce the requirement of overload, suppress the fluctuation of line-of-sight angular velocity. So the integrated sliding mode optimal midcourse guidance law has good guidance performance.

关 键 词：高超声速飞行器 中制导律 最优控制 积分滑模控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]