Abstract 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 SFTC is inertia-independent and yields bounded control torques, in addition to finite-time convergence. Specially, the quaternion-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.


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    Title :

    Simple finite-time attitude stabilization laws for rigid spacecraft with bounded inputs


    Contributors:
    Gui, Haichao (author) / Jin, Lei (author) / Xu, Shijie (author)

    Published in:

    Publication date :

    2015-01-22


    Size :

    11 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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