基于最优误差动力学的时间角度控制制导律

doi:10.7527/S1000-6893.2018.22215

电子电气工程与控制

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基于最优误差动力学的时间角度控制制导律

李斌^1,2, 林德福^1,2, 何绍溟^1,2, 白冰³

1. 北京理工大学宇航学院, 北京 100081;
2. 北京理工大学无人机自主控制技术北京市重点实验室, 北京 100081;
3. 北京宇航系统工程研究所, 北京 100076

收稿日期:2018-04-17 修回日期:2018-05-16 出版日期:2018-11-15 发布日期:2018-08-01
通讯作者: 李斌 E-mail:3120150050@bit.edu.cn
基金资助:
国家自然科学基金（U1613225）

Time and angle control guidance law based on optimal error dynamics

LI Bin^1,2, LIN Defu^1,2, HE Shaoming^1,2, BAI Bing³

1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
2. Beijing Key Laboratory of UAV Autonomous Control, Beijing Institute of Technology, Beijing 100081, China;
3. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China

Received:2018-04-17 Revised:2018-05-16 Online:2018-11-15 Published:2018-08-01
Supported by:
National Natural Science Foundation of China (U1613225)

摘要/Abstract

摘要： 针对带有攻击时间和终端攻击角度约束的导弹制导问题，设计了一种基于最优误差动力学的时间角度控制制导律，并给出了明确的性能指标。推导广义最优角度控制制导律作用下的剩余飞行时间估算表达式，在广义最优角度控制制导律的基础上增加攻击时间误差反馈项，将攻击时间误差看做跟踪误差，设计的制导律使跟踪误差以最优模式在有限时间内收敛到零，最终实现攻击时间和终端攻击角度的共同控制。对不同参数下的情况进行仿真，验证了所提制导律的有效性。

关键词: 攻击时间控制, 攻击角度控制, 最优误差动力学, 剩余飞行时间, 跟踪误差收敛模式

Abstract: To solve the missile guidance with constraints of impact time and terminal impact angle, a time and angle control guidance law based on optimal error dynamics is designed, and a definite performance index is given. The expression of time to go estimation under generalized optimal angle control guidance law is derived. To reach zero tracking error in the finite time with the optimal convergence pattern, the designed guidance law adds the feedback of impact time error to the generalized guidance law of optimal angle control and considers the impact time error as the tracking error, achieving the joint control of the impact time and the terminal impact angle. The effectiveness of the proposed guidance law is validated through numerical simulations under different conditions.

Key words: impact time control, impact angle control, optimal error dynamics, time to go, tracking error convergence pattern

中图分类号:

李斌, 林德福, 何绍溟, 白冰. 基于最优误差动力学的时间角度控制制导律[J]. 航空学报, 2018, 39(11): 322215-322225.

LI Bin, LIN Defu, HE Shaoming, BAI Bing. Time and angle control guidance law based on optimal error dynamics[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(11): 322215-322225.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于最优误差动力学的时间角度控制制导律

Time and angle control guidance law based on optimal error dynamics

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