摘要
This paper investigates fault tolerant attitude control theory and experiment for underactuated spacecraft with one reaction wheel completely broken and two others suffering actuator faults of partial loss of effectiveness or bias.A non-smooth robust adaptive fault tolerant control law is proposed under the zero-momentum and input saturation conditions.It shows that the available reaction wheels need to produce sufficient control torque for the fault tolerance.Such a new control method is implemented in a semi-physical simulation system of an air-bearing platform.Experimental results show the effectiveness of the proposed method in spacecraft practical engineering.
基金
supported by the National Natural Science Foundation of China(Nos.62073165 and 62233009)
the 111 Project,China(No.B20007).
作者简介
Corresponding author:Hao YANG.E-mail address:haoyang@nuaa.edu.cn。
