Twistor-based synchronous sliding mode control of spacecraft attitude and position

查看全文 作　　者：Qing [1]LI;Lei [1]LIU;Yifan [2]DENG;Shuo [1]TANG;Yanbin [2]ZHAO

机构地区：[1]Shaanxi Aerospace Flight Vehicle Design Key Laboratory, School of Astronautics, Northwestern Polytechnical University,Xi'an 710072, China;[2]Shanghai Institute of Satellite Engineering, Shanghai 200240, China

出　　处：《Chinese Journal of Aeronautics》索引2018年第31卷第5期,共12页

基　　金：supported by the National Natural Science Foundation of China(Nos.51675430,11402044,and U1537213) 摘　　要：A synchronous control of relative attitude and position is required in separated ultraquiet spacecraft, such as drag-free, disturbance-free, and distributed spacecraft. Thus, a twistorbased synchronous sliding mode control is investigated in this paper to solve the control problem of relative attitude and position among separated spacecraft modules. The twistor-based control design and the stability proof are implemented using the Modified Rodrigues Parameter(MRP).To evaluate the effectiveness of the proposed control method, this paper presents a case study of separated spacecraft flying control considering the mass uncertainty and external disturbances. In addition, a simulation study of the Proportional-Derivative(PD) control is also presented for comparison. The results indicate that the twistor-based sliding mode controller can ensure global asymptotic stability. The states converge fast with ultra-precision and ultra-stability in both the attitude and position. Moreover, the proposed twistor-based sliding mode control system is robust to the mass uncertainty and external disturbances. 关键词：滑动模式控制同步控制太空船位置极端稳定性控制问题控制设计控制系统

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Twistor-based synchronous sliding mode control of spacecraft attitude and position

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