Journal
ISA TRANSACTIONS
Volume 49, Issue 1, Pages 57-69Publisher
ELSEVIER SCIENCE INC
DOI: 10.1016/j.isatra.2009.08.003
Keywords
Adaptive backstepping; Sliding mode control; Attitude control; Fault tolerant; Flexible spacecraft
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Funding
- Scientific Research Foundation for Returned Overseas Chinese Scholars of State Education Ministry
- Scientific Research Foundation for Returned Overseas Chinese Scholars of Heilongjiang Province [LC08C01]
- National Natural Science Foundation of China [60774062]
- Doctoral Program of Higher Education of China [20070213061]
- Innovation Fund of China Academy of Space Technology (CAST)
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In this paper, a robust adaptive fault-tolerant control approach to attitude tracking of flexible spacecraft is proposed for use in situations when there are reaction wheel/actuator failures, persistent bounded disturbances and unknown inertia parameter uncertainties. The controller is designed based on an adaptive backstepping sliding mode control scheme, and a sufficient condition under which this control law can render the system semi-globally input-to-state stable is also provided such that the closed-loop system is robust with respect to any disturbance within a quantifiable restriction on the amplitude as, well as the set of initial conditions, if the control gains are designed appropriately. Moreover in the, design, the control law does not need a fault detection and isolation mechanism even if the failure time instants, patterns and values on actuator failures are also unknown for the designers as motivated from, a practical spacecraft control application. In addition to detailed derivations of the new controller design and a rigorous sketch of all the associated stability and attitude error convergence proofs, illustrative simulation results of an application to flexible spacecraft show that high precise attitude control and vibration suppression are successfully achieved using various scenarios of controlling effective failures. (C) 2009, ISA. Published by Elsevier Ltd. All rights reserved.
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