Journal
INTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL
Volume 26, Issue 1, Pages 28-46Publisher
WILEY
DOI: 10.1002/rnc.3289
Keywords
finite-time control; fast terminal sliding mode control; adaptive control; attitude stabilization; actuator faults
Funding
- National Basic Research Program of China (973 Program) [2012CB720000]
- National Natural Science Foundation of China [61225015, 61105092, 61403355]
- Foundation for Innovative Research Groups of the National Natural Science Foundation of China [61321002]
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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 (C) 2015 John Wiley & Sons, Ltd.
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