一种带有末端弹体姿态角约束的非线性制导律  

Nonlinear guidance law with terminal body angle constraints

作　　者：李新三 汪立新[1] 刘国辉[2] 闫循良 王明建[2] 丁邦平[2] 

机构地区：[1]第二炮兵工程大学三系,西安710025 [2]第二炮兵工程大学士官学院,青州262500

出　　处：《中国惯性技术学报》2015年第2期232-237,共6页Journal of Chinese Inertial Technology

基　　金：国家自然科学基金(61203354)

摘　　要：针对带有末端多约束的三维非线性制导问题,设计了一种通用模型预测静态规划制导算法。该制导算法通过向后迭代求解权矩阵微分方程对控制量进行更新,将动态优化问题转化为静态优化问题,计算效率得以提高。阐述了通用模型预测静态规划制导算法的基本原理,详细给出了基于通用模型预测静态规划算法的制导律设计过程。所设计的制导律满足末端法向加速度约束,因此,间接满足末端弹体姿态角约束。仿真时考虑目标的机动方式和落角约束,仿真结果表明,末端位移偏差小于0.5 m,末端落角可控制在0.01°范围内,末端法向加速度小于0.01 m/s2,该制导律能够很好地满足末端位移、落角和法向加速度约束。In view of 3D nonlinear guidance problems with terminal multi-constraints, a guidance algo- rithm based on predictive static programming of a generalized model is designed. A key feature of the technique is backward propagation of weighted matrix dynamics, which is used to update the control his- tory and transfer dynamic optimization into static one with high computational efficiency. The basic prin- ciple of the technique is given, and the design of the guidance law is presented. The designed guidance law satisfies the terminal lateral-acceleration constraints, and hence indirectly satisfies the terminal body angle constraints. Various maneuvering accelerations and impact angles of targets are considered in simu- lations, and the results show that final miss displacement is less than 0.5 m, terminal impact angle errors are less than 0.01°, and terminal lateral accelerations are less than 0.01m/s^2, adequately meeting the con- straints of terminal displacement, impact angle, and lateral acceleration.

关 键 词：通用模型预测静态规划 制导律 落角约束 法向加速度约束 弹体姿态角约束 

分 类 号：V448[航空宇航科学与技术—飞行器设计]