Design of guidance law with multiple constraints considering maneuvering efficiency

被引：0
|
作者：
Wang C. [1 ]
Xue L. [1 ]
Yan X. [1 ]
机构：
[1] The Second Academy of China Aerospace Science & Industry Corp., Beijing
来源：
Beijing Hangkong Hangtian Daxue Xuebao | / 8卷 / 1594-1601期
基金：
中国国家自然科学基金;
关键词：
Air-defense missile; Guidance law; Maneuvering efficiency; Multiple constraints; Optimal control; Terminal intercept angle;
D O I：
10.13700/j.bh.1001-5965.2016.0567
中图分类号：
学科分类号：
摘要：
Due to the guidance law with terminal intercept angle which will cause big angle error when available payload is insufficient, a guidance law considering time-varying overload constraint has been elicited, which would bring on more energy loss when much maneuver is achieved at the same time. Given this, this paper elicits a guidance law with multiple constraints considering maneuvering efficiency. First, a closed-loop guidance law with time-varying control weight coefficient is elicited according to optimal quadratic theory. Second, drag coefficient when maneuvering is introduced into time-varying control weight coefficient, and the constraint boundaries of available payload and maneuvering efficiency are obtained through iterations. Finally, the time-varying weight coefficient is changed into function of time-to-go, and the trajectories are simulated with guidance law considering available payload and maneuvering efficiency. The simulation results indicate that both the two guidance laws can meet the requirement of trajectory shaping, and the acceleration command of guidance law with constraint considering maneuvering efficiency is more reasonable, which reduces the velocity loss effectively and enhances the guidance accuracy and damage effect. Moreover, balance solution of time-varying weight coefficient is not necessary with this method, so iteration speed will be highly improved when accuracy is guaranteed. © 2017, Editorial Board of JBUAA. All right reserved.
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页码：1594 / 1601
页数：7
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