Attitude control method of air defense missile based on large command change rate

被引：0
|
作者：
Yan S. [1 ]
Wei M. [1 ,2 ]
Zheng Y. [1 ]
机构：
[1] Beijing Institute of Electronic System Engineering, Beijing
[2] Beijing Simulation Center, Beijing
来源：
Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | 2024年 / 46卷 / 07期
关键词：
air defense missile; attitude control; differentiator; steady-state effect index; trigger control;
D O I：
10.12305/j.issn.1001-506X.2024.07.28
中图分类号：
学科分类号：
摘要：
Aiming at the problem of poor attitude control quality caused by strong target maneuverability of air defense missile, an event-triggered control method is proposed. Firstly, the unknown command change rate caused by the strong maneuverability of the target and the reason of the large steady-state error caused by the excessive command change rate are analyzed. To solve this problem, a nonlinear fastest tracking differentiator is introduced to obtain the command change rate, the relationship between the command change rate and the attitude angle error is studied, the steady-state effect index is defined, and the new event-based control quantity is designed based on this index. By using sliding mode control and disturbance observer, the steady-state error of the system is suppressed within 5% error band under the condition of higher command change rate. In the background of engineering practice, the numerical simulation takes into account the deviation of aerodynamic parameters and the limiting of actuator, and the simulation results verify the effectiveness of the designed control system. © 2024 Chinese Institute of Electronics. All rights reserved.
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页码：2465 / 2474
页数：9
相关论文
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