Coordinated attitude control for flexible spacecraft formation with actuator configuration misalignment  

作　　者：Xiaomei CHENG Yuan LIU Yi QIN Feng WANG Junjie ZHANG 

机构地区：[1]School of Astronautics,Harbin Institute of Technology,Harbin 150080,China [2]China Academy of Launch Vehicle Technology,Beijing 100000,China [3]Center for Precision Engineering,Harbin Institute of Technology,Harbin 150001,China

出　　处：《Chinese Journal of Aeronautics》2021年第3期176-186,共11页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(Nos.61833009,61690212 and 51875119);the National Key Research and Development Project(No.2016YFB0501203)。

摘　　要：This paper investigates the coordinated attitude control problem for flexible spacecraft formation with the consideration of actuator configuration misalignment.First,an integral-type sliding mode adaptive control law is designed to compensate the effects of flexible mode,environmental disturbance and actuator installation deviation.The basic idea of the Integral-type Sliding Mode Control(ISMC)is to design a proper sliding manifold so that the sliding mode starts from the initial time instant,and thus the robustness of the system can be guaranteed from the beginning of the process and the reaching phase is eliminated.Then,considering the nominal system of spacecraft formation based on directed topology,an attitude cooperative control strategy is developed for the nominal system with or without communication delay.The proposed control law can guarantee that for each spacecraft in the spacecraft formation,the desired attitude objective can be achieved and the attitude synchronization can be maintained with other spacecraft in the formation.Finally,simulation results are given to show the effectiveness of the proposed control algorithm.

关 键 词：Actuator configuration misalignment Adaptive control Attitude control Integral-type sliding mode control Spacecraft formation flying 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]