摘要
针对执行机构发生故障时的航天器姿态控制问题,提出了一种基于自适应快速终端滑模的容错控制设计方法。该方法通过选择具有快速终端特性的滑模面,提高航天器容错控制的收敛速率,实现系统有限时间稳定;利用自适应控制方法在线调整控制器参数,消除对故障最小值信息的依赖。仿真结果表明,与基于普通滑模控制器的容错控制相比,所提出的方法在保证系统鲁棒性和稳定性的同时,三轴姿态角和姿态角速度收敛时间可分别降低约54.5%和50%,实现快速有效的航天器容错控制。
Aiming at the attitude control problem of spacecraft with actuator faults,a novel method for designing fault-tolerant controller is proposed based on adaptive fast terminal sliding mode control.The method could improve the convergent rate of the spacecraft fault-tolerant controller and guarantee the finite-time stability by selecting the sliding mode surface with fast terminal feature.Furthermore,an adaptive control method is designed with the outcome of regulating controller parameters online and eliminating the dependence of fault-minimum-information.Numerical simulation demonstrates that the proposed method could achieve effective spacecraft fault-tolerant control.Specifically,when compared with the traditional sliding mode method,the convergent rates of attitude angle and angle rate decreased by 54.5% and 50% respectively,as well as the improvement of the robustness.
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2012年第5期982-988,共7页
Systems Engineering and Electronics
基金
国家自然科学基金(60974104
61001155)资助课题
关键词
容错控制
终端滑模
自适应控制
执行器故障
fault tolerant control
terminal sliding mode
adaptive control
actuator faultve radar
