Adaptive Sliding-mode Control of Launch Vehicle with Actuator Failures

被引：0

作者：

Wang P. ^{[1
]}

Qu D. ^{[1
]}

Ran M. ^{[2
,3
]}

Dong C. ^{[1
]}

机构：

[1] School of Aeronautic Science and Engineering, Beihang University, Beijing

[2] School of Automation Science and Electrical Engineering, Beihang University, Beijing

[3] Zhongguancun Laboratory, Beijing

来源：

Yuhang Xuebao/Journal of Astronautics | 2023年 / 44卷 / 08期

关键词：

Actuator failures; Extended state observer (ESO); Fault-tolerant control; Launch vehicle; Sliding-mode control;

D O I：

10.3873/j.issn.1000-1328.2023.08.005

中图分类号：

学科分类号：

摘要：

Aiming at the attitude command tracking control problem of launch vehicle with actuator failures, an adaptive sliding mode fault-tolerant controller based on a novel extended state observer(ESO) is designed, considering the effects of internal unmodeled dynamics and external uncertain disturbances. Firstly, a new cascaded reduced-order ESO is presented to estimate the unmodeled dynamics and external uncertain disturbances of the system. Based on this, an adaptive sliding mode control law with fixed time convergence is designed, which can obtain the upper bound information of the disturbance estimation error and eliminate the chattering phenomenon of sliding mode control. The stability of the closed-loop system is proved by the Lyapunov method. The simulation results show that the proposed adaptive sliding mode fault-tolerant controller based on the new ESO has good tracking performance and disturbance immunity in the case of actuator failures. © 2023 China Spaceflight Society. All rights reserved.

引用

页码：1160 / 1170

页数：10

共 26 条

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