During the aerospace missions for the on-orbiting spacecraft, actuator faults are frequently encountered such that the control system performance may be degraded, even the unstable ACS may result in the completely collapse, immeasurable losses or catastrophic consequences. Thus, the spacecraft ACS should be capable of dealing with or tolerating possible actuator faults, while at the same time guaranteeing an acceptable performance in the presence of actuator faults. There exist some main approaches to improve the stability and reliability of the spacecraft ACS, such as high reliable control system design with redundant devices, FDD based FTC system design, CA based FTC system design and so on. Recently, CA techniques have drawn significant interests in the aircraft and spacecraft control [1–13], especially in the FTC system design. Gui et al. [14] introduced an adaptive SMC law to dynamically compensate the perturbations due to actuator faults and other uncertainties, in which the real time CA algorithm delivers the control command to actuators. In [15], a novel dynamic near-optimal CA scheme with combination of a saturated baseline controller for spacecraft attitude control using single-gimbal control moment gyros. This dynamic control allocation is implemented with online update law, which has a modest computational complexity. All these methods can primarily generate commands to control effectors to achieve some demand moment or acceleration. Some of them take in account the position and rate limits, while some also allow for satisfying a secondary objective. Generally speaking, all the aforementioned CA can be implemented practically to address the concerned constraints and objectives. However, the authors in [16] illustrated that different CA algorithms can lead to different closed-loop maneuver performances owing to the CA errors between the designed signal and actual input. Usually, this CA error is treated as small and neglectable in the control design, which, in fact, may lead to a degraded performance or even potential closed-loop instability. In all the aforementioned references, it is assumed that the system state trajectories are governed by the baseline controller, and CA algorithms have no/little effect on the closed-loop performance.


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    Titel :

    Closed-Loop Based Control Allocation for Spacecraft Attitude Stabilization with Actuator Faults


    Beteiligte:
    Hu, Qinglei (Autor:in) / Li, Bo (Autor:in) / Xiao, Bing (Autor:in) / Zhang, Youmin (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2021-03-14


    Format / Umfang :

    33 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






    Robust control allocation for spacecraft attitude stabilization under actuator faults and uncertainty

    Zhang, Aihua / Wang, Yongchao / Zhang, Zhiqiang et al. | BASE | 2014

    Freier Zugriff

    Robust control allocation for spacecraft attitude stabilization under actuator faults and uncertainty

    Zhang, Aihua / Wang, Yongchao / Zhang, Zhiqiang et al. | BASE | 2014

    Freier Zugriff