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Adaptive finite‐time attitude stabilization for rigid spacecraft with actuator faults and saturation constraints
Author(s) -
Lu Kunfeng,
Xia Yuanqing,
Fu Mengyin,
Yu Chunmei
Publication year - 2015
Publication title -
international journal of robust and nonlinear control
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.361
H-Index - 106
eISSN - 1099-1239
pISSN - 1049-8923
DOI - 10.1002/rnc.3289
Subject(s) - control theory (sociology) , terminal sliding mode , actuator , spacecraft , attitude control , inertial frame of reference , sliding mode control , context (archaeology) , computer science , terminal (telecommunication) , trajectory , singularity , engineering , control engineering , control (management) , mathematics , physics , nonlinear system , aerospace engineering , artificial intelligence , paleontology , telecommunications , mathematical analysis , quantum mechanics , astronomy , biology
Summary The attitude stabilization problem for rigid spacecraft in the presence of inertial uncertainties, external disturbances, actuator saturations, and actuator faults is addressed in this paper. First, a novel fast terminal sliding mode manifold is designed to avoid the singularity problem while providing high control ability. In addition, fast terminal sliding mode control laws are proposed to make the spacecraft system trajectory fast converge onto the fast terminal sliding mode surface and finally evolve into small region in finite time, which cannot be achieved by the previous literatures. Based on the real sliding mode context, a practical adaptive fast terminal sliding mode control law is presented to guarantee attitude stabilization in finite time. Also, simulation results are presented to illustrate the effectiveness of the control strategies. Copyright © 2015 John Wiley & Sons, Ltd.