基于线性二次型高斯(LQG)理论的最优制导规律  

An Optimal Guidance Law Based on Linear Quadratic Gaussian (LQG) Theory

作　　者：雷虎民[1] 梁颖亮[2] 杨强国 

机构地区：[1]西安交通大学电信学院,陕西西安710049 [2]空军工程大学导弹学院,陕西三原713800 [3]陕西新华书店,陕西西安710003

出　　处：《空军工程大学学报（自然科学版）》2002年第2期27-30,共4页Journal of Air Force Engineering University(Natural Science Edition)

摘　　要：以线性二次型高斯 (LQG)理论为基础 ,研究一种最小化末端脱靶量和拦截周期内控制能量消耗的具有可变有效导航比的LQG最优制导规律。分析了这种制导规律的有效导航比及其在战术导弹上的应用。应用伴随方法对这种制导规律进行制导性能仿真计算。结果表明 :这种制导规律的控制精度高。Based on linear quadratic Gaussian (LQG) theory, this paper shows a study of a LQG optimal guidance law that minimizes the terminal miss distance and control energy consumption within the intercepting period. This paper also gives an analysis of the law's effective navigation ratio and these ratio's applications to the tactical missiles. The results obtained by using adjoint methods show that the optimal LQG guidance law has an advantage over the traditional one in control accuracy and maneuver overload.

关 键 词：线性二次型高斯 最优制导规律 比例导引规律 战术导弹 

分 类 号：V448[航空宇航科学与技术—飞行器设计]