This chapter models the attitude stabilization of spacecraft during partial loss of actuator effectiveness by a multiplicative factor. It provides an adaptive fault‐tolerant strategy for spacecraft attitude control when there is partial loss of actuator effectiveness. Specifically, by applying an adaptive backstepping control technique, a normal attitude controller is first derived for the rigid spacecraft system in the presence of external disturbances, in which all the actuators are fault‐free and operating normally. The chapter presents spacecraft‐attitude mathematical model and control problems. In the chapter, for the normal system without an actuator fault, a baseline attitude controller based on the adaptive backstepping technique is developed. Then, using the baseline controller, the fault‐tolerant controller is derived. This guarantees that the actual outputs of the faulty actuators can still follow the normal command inputs, and the fault can be compensated online.
Adaptive Fault‐tolerant Attitude Control for Spacecraft Under Loss of Actuator Effectiveness
2017-04-03
22 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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