包含弹体动力学的终端角约束弹道成型制导律  

Trajectory Shaping Guidance Law with Terminal Impact Angle Constraint Including Missile Body Dynamics

作　　者：刘大卫[1,2] 夏群利[1] 左媞媞 何镜[2] 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]中国兵器科学研究院,北京100089

出　　处：《北京理工大学学报》2013年第4期363-368,共6页Transactions of Beijing Institute of Technology

基　　金：航空科学基金资助项目(20060112123)

摘　　要：针对侵彻型导弹弹道终端对命中位置和入射角度提出严格约束的制导问题,引入弹体动力学环节,采用Schwartz不等式方法推导了最优制导律.在小角假设基础上,将其表述为便于工程实现的包含弹体动力学的终端角约束弹道成型制导律.分别利用Schwartz不等式和伴随函数法研究了制导律量纲一化制导指令解析解、位置脱靶量及角度偏差特性.结果表明,该制导律不但能同时满足终端位置和角度约束,而且可确保终端过载指令归零,从而为侵彻型制导武器末端攻角控制提供了一种可行的制导策略.To meet the terminal guidance requirement of penetrating guided weapon with both impact position and angle constraints, optimal guidance law with first-order guidance system dynamics was deduced by Schwartz inequality method. Then, Trajectory shaping guidance law with missile body dynamics（TSGL-D）was obtained based on small angle assumption in order to be accomplished in engineering easily. Further, the non-dimensional guided command, miss distance and impact angle error of the guidance law were studied by Schwartz inequality and adjoint-method. Simulation demonstrates that the guidance law is not only satisfied with the demands of the impact position and angle constrains, but also can make the overload at impact point return to zero, which could provide a feasible guidance strategy for controlling the impact attack angle of penetrating guided weapon.

关 键 词：弹体动力学 终端角约束 弹道成型 

分 类 号：V448.133[航空宇航科学与技术—飞行器设计]