Research on Integrated Design of Aircraft Spiral Maneuver, Guidance and Control Based on Sliding Mode Control

被引：0
|
作者：
Wu Y. [1 ]
Lu X. [1 ]
Wang Z. [1 ]
机构：
[1] School of Mechatronic Engineering, Beijing Institute of Technology, Beijing
来源：
Beijing Ligong Daxue Xuebao/Transaction of Beijing Institute of Technology | 2022年 / 42卷 / 05期
关键词：
Aircraft control; Ballistic maneuver; Integrated guidance and control; Sliding mode control;
D O I：
10.15918/j.tbit1001-0645.2021.089
中图分类号：
学科分类号：
摘要：
To solve the problems of the capability deficiency of air-to-ship aircraft in the terminal guidance process and the inefficient control due to the separation of guidance and control loop design with unsatisfied assumption of bandwidth separation, an integrated design method was proposed for the guidance and control loop of the aircraft. Taking a ballistic maneuvering form with three-dimensional spiral maneuver, the design method was arranged to achieve spiral maneuvering, guidance and control integration. Firstly, an integrated model was established for the guidance and control loops at the end of the flight. And then, a sliding mode control method was applied to complete the control law design for guidance and control integration. Finally, introducing a period inclination rate of the line of sight obliquity and the line of sight deflection rate, the integrated design was carried out for spiral maneuvering, guidance and control integration. The simulation results show that the control law designed in this paper can improve the strike accuracy and provide a ballistic spiral maneuverability in the attack process. Copyright ©2022 Transaction of Beijing Institute of Technology. All rights reserved.
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页码：523 / 529
页数：6
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