空地导弹滑模制导方法研究  

Research on sliding mode guidance method for air-to-ground missile

作　　者：尹永鑫[1] 杨明[2] 吴鹏[2] 

机构地区：[1]中国航天空气动力技术研究院第11总体设计部,北京100074 [2]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《飞行力学》2010年第1期44-46,52,共4页Flight Dynamics

基　　金：国家自然科学基金资助(60434010);黑龙江省杰出青年基金资助(JC200606)

摘　　要：针对空地导弹的制导规律设计问题,给出了滑模制导方法,建立了纵向平面内的弹-目相对运动方程。基于滑模控制理论,设计了空地导弹的制导规律,以同时保证脱靶量和弹道倾角要求,并针对固定目标,给出了相对距离和相对速度的解算方法,介绍了针对移动目标的相对距离和相对速度估算方法。仿真结果表明,该制导方法具有较高的制导精度,并且满足弹道倾角约束。The sliding mode guidance method is presented for guidance problems of an air-to-ground missile. The missile-target relative geometry relation is constituted in the lengthways plane. With a view to ensure miss distance and flight path angle, the sliding mode guidance method is presented. According to this method, the guidance law of air-to-ground missile is designed. In order to attack the ground immobile target, the method to compute relative distance between a missile and a target is summarized. And the method to compute relative distance between a missile and a target is given for the ground mobile target. Simulation results show that this guidance method can implement efficiently the flight path angle constraint mission for missiles as well as preferable guidance precision.

关 键 词：空地导弹 滑模制导 机动目标 相对距离 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]