Integrated Design of Maneuvering Penetration and Guidance Based on Line Deviation Control

被引：0
|
作者：
Zhao B. [1 ]
Liu T. [1 ]
机构：
[1] Institute of Precision Guidance and Control, Northwestern Poly Technical University, Xi'an
来源：
Yuhang Xuebao/Journal of Astronautics | 2022年 / 43卷 / 10期
关键词：
Command filter; Line deviation; Maneuvering penetration; Overload constraint; Spiral maneuvering signal;
D O I：
10.3873/j.issn.1000-1328.2022.10.006
中图分类号：
学科分类号：
摘要：
The trajectory design of missile maneuvering penetration is closely related to the terminal guidance correction capability. Under the constraints of available overload and impact angle, an integrated design method of maneuvering penetration and guidance based on line deviation control is proposed. Firstly, the integrated design model of maneuvering penetration and guidance is established. Secondly, a virtual guidance trajectory guidance law with available overload and terminal angle constraints is designed. Thirdly, a spiral maneuvering line deviation command signal with motion overload constraint is proposed, and the relative maneuvering trajectory guidance law is designed. The problems of input constraints and interference estimation are solved respectively by using command filtering and extended state observers. The stability of closed-loop system is proved based on Lyapunov stability theory. The penetration simulation results under different overload constraints show that the proposed method can meet the requirements of maneuvering penetration and precise strike, and the single penetration success rate of PAC-3 interceptor in typical scenarios reaches 96. 2% . © 2022 China Spaceflight Society. All rights reserved.
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页码：1333 / 1344
页数：11
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