摘要
We review the controllability research on spacecraft attitude based on nonlinear geometry control theory.The existing studies on attitude controllability are mostly concerning the global controllability and small time local controllability(STLC).A presentation of study methods and connotation in both aspects is briefly carried out.As a necessary condition of reconfigurability,the controllability of the faulty attitude control system is studied.Moreover,two reconfigurability conditions based on controllability results that consider the actuator faults for a pyramid configuration spacecraft are provided.
We review the controllability research on spacecraft attitude based on nonlinear geometry control theory.The existing studies on attitude controllability are mostly concerning the global controllability and small time local controllability(STLC). A presentation of study methods and connotation in both aspects is briefly carried out. As a necessary condition of reconfigurability,the controllability of the faulty attitude control system is studied. Moreover,two reconfigurability conditions based on controllability results that consider the actuator faults for a pyramid configuration spacecraft are provided.
基金
supported by the National Natural Science Foundation of China (Nos. 61622304,61773201)
the Natural Science Foundation of Jiangsu Province(No.BK20160035)
the Fundamental Research Funds for the Central Universities (Nos. NE2014202,NE2015002)
