基于最优控制解析解的直接入轨自适应制导律  

An Adaptive Guidance Method of Directly Injecting Rocket Based on Optimal Analytical Solution

作　　者：王智 李佳峰 张婕 王鹏 李强 Wang Zhi;Li Jiafeng;Zhang Jie;Wang Peng;Li Qiang(Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《航天控制》2018年第2期37-41,共5页Aerospace Control

摘　　要：研究了直接入轨飞行器基于最优控制解析解的显式制导问题。在入轨速度最大指标约束下,推导出了一种直接入轨飞行器基于最优控制理论的显式解析制导律,并对该制导方法进行了仿真验证。仿真结果表明,所得制导方法具有较高的制导精度和较强的自适应性和鲁棒性,同时该制导方法计算简单、计算实时性强,具有较好的工程应用价值。An explicit guidance of the directly injecting rocket based on analytic solutions of the optimal control is studied. Under the constraints of the maximum injection velocity,an explicit analytic guidance law is derived,and the guidance is verified and analyzed by simulation. The simulation results show that the obtained guidance method has high guidance precision performance,strong adaptability and robustness.At the same time,the guidance method is simple and real-time during calculation,and has fairly good application value in engineering.

关 键 词：最优轨迹 直接入轨 显式制导 解析解 

分 类 号：V448.232[航空宇航科学与技术—飞行器设计]