Journal
AEROSPACE SCIENCE AND TECHNOLOGY
Volume 42, Issue -, Pages 176-186Publisher
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/j.ast.2015.01.020
Keywords
Attitude stabilization; Finite-time stability; Homogeneous; Input saturation; Inertia uncertainty
Categories
Funding
- National Natural Science Foundation of China [11272028]
- Innovation Foundation of the National Laboratory of Space Intelligent Control
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The problem of finite-time attitude stabilization of a rigid spacecraft is investigated. Homogeneous system theory is utilized to design a simple nonlinear proportional-derivative-type (PD-type) saturated finite-time controller (SFTC), which can accommodate its form to different attitude parameterizations, such as quaternion, Rodrigues parameters (RP) and modified Rodrigues parameters (MRP). The proposed SFIC is inertia-independent and yields bounded control torques, in addition to finite-time convergence. Specially, the quatemion-based SFTC avoids the unwinding phenomenon associated with traditional continuous quaternion-based control laws and achieves, as shown by the Monte Carlo analysis, a faster convergence than a previous quaternion-based finite-time attitude stabilization law. Numerical examples are presented to verify the efficacy of the proposed method. (C) 2015 Elsevier Masson SAS. All rights reserved.
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