Closed-Loop Optimization of Guidance Gain for Constrained Impact

作     者：Liu, Xinfu Shen, Zuojun Lu, Ping 

作者机构：Beijing Inst Technol Sch Aerosp Engn Beijing 100081 Peoples R China Beihang Univ Sch Aeronaut Sci & Engn Beijing 100191 Peoples R China San Diego State Univ Dept Aerosp Engn San Diego CA 92182 USA 

出 版 物：《JOURNAL OF GUIDANCE CONTROL AND DYNAMICS》 (制导、控制和动力学杂志)

年 卷 期：2017年第40卷第2期

页      面：453-460页

核心收录：

学科分类：12[管理学] 1201[管理学-管理科学与工程(可授管理学、工学学位)] 08[工学] 0804[工学-仪器科学与技术] 0825[工学-航空宇航科学与技术] 

基　　金：National Natural Science Foundation of China 

主　　题：Closed Loop Trajectory Optimization Flight Path Angle Guidance Laws Engagement Kinematics Nonlinear Programming Proportional Navigation Velocity Profiles Aerodynamic Drag Optimization Algorithm 

摘      要：The tightly constrained guidance problem of impact on a stationary target is considered, subject to look-angle and lateral-acceleration limits, as well as final impact-angle and look-angle constraints. Proportional-navigation guidance with a time-varying gain is proposed to address this problem. The problem has been formulated as an optimal-control problem, where the time-varying PN gain is regarded to be the control, subject to nonlinear engagement kinematics and all the inequality and terminal constraints. A successive solution approach is proposed to solve this nonlinear optimal-control problem as a sequence of convex optimal-control problems that can be numerically solved as second-order cone programs. Compared with standard direct-trajectory-optimization approaches based on general nonlinear-programming methods, the proposed method can solve the problem two orders of magnitude faster in terms of computational time. Compared with existing PN guidance approaches, the proposed method provides a more rigorous and systematic guidance approach, and assures the satisfaction of all guidance objectives in highly constrained but feasible scenarios.