Open AccessFinite‐time fault tolerant attitude control for over‐activated spacecraft subject to actuator misalignment and faults
Author(s) -
Zhang Aihua,
Hu Qinglei,
Friswell Michael I.
Publication year - 2013
Publication title -
iet control theory and applications
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.059
H-Index - 108
eISSN - 1751-8652
pISSN - 1751-8644
DOI - 10.1049/iet-cta.2013.0133
Subject(s) - control theory (sociology) , actuator , reachability , attitude control , controller (irrigation) , spacecraft , compensation (psychology) , inertia , computer science , fault tolerance , fault (geology) , engineering , control (management) , control engineering , algorithm , physics , aerospace engineering , distributed computing , artificial intelligence , seismology , geology , psychology , agronomy , classical mechanics , psychoanalysis , biology
A finite‐time attitude compensation control scheme is developed for an over‐activated rigid spacecraft subject to actuator faults, misalignment, external disturbances and uncertain inertia parameters. The controller is synthesised based on the sliding mode control theory, and guarantees the finite‐time reachability of the system states. A sufficient condition for the controller to accommodate misalignment and faults of actuator is presented. An optimised control allocation algorithm based on the Karush–Kuhn–Tucker condition is then applied to distribute the commanded control to each actuator, and optimise the consumption of energy. Numerical simulation results are presented that highlight the performance benefits of the control law.