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首页> 外文期刊>Journal of guidance, control, and dynamics >Fault-Tolerant Attitude Control for Flexible Spacecraft Without Angular Velocity Magnitude Measurement
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Fault-Tolerant Attitude Control for Flexible Spacecraft Without Angular Velocity Magnitude Measurement

机译：没有角速度幅度测量的挠性航天器的容错姿态控制

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摘要

SINCE some catastrophic faults or failures may be induced due to the aging or damage of actuators and sensors during the mission of a spacecraft, those faults would lead to performance degradation of the spacecraft attitude control system or even result in the specified aerospace mission failure. Therefore, fault tolerance of the spacecraft attitude control system is one of the key issues that needs to be addressed. With a view to tackle such a challenge, fault-tolerant control (FTC) has received considerable attention in order to enhance the spacecraft reliability and to guarantee the attitude control performance [1-5]. In [5], an adaptive FTC is developed for the flexible spacecraft attitude tracking system where the persistent bounded disturbances, unknown inertia parameter, and even two types of reaction wheel faults are successfully accommodated.
机译：由于在航天器执行任务期间可能会由于致动器和传感器的老化或损坏而引发某些灾难性故障或故障，这些故障将导致航天器姿态控制系统的性能下降，甚至导致指定的航天任务故障。因此，航天器姿态控制系统的容错性是需要解决的关键问题之一。为了应对这种挑战，为了提高航天器的可靠性并保证姿态控制性能，容错控制（FTC）受到了广泛的关注。在[5]中，为挠性航天器姿态跟踪系统开发了一种自适应FTC，该系统成功地适应了持续的有界干扰，未知惯性参数，甚至两种反作用轮故障。

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  • 来源
    《Journal of guidance, control, and dynamics》 |2011年第5期|p.1556-1561|共6页
  • 作者

    Bing Xiao; Qinglei Hu; Youmin Zhang;

  • 作者单位

    Harbin Institute of Technology,150001 Harbin, People's Republic of China;

    Harbin Institute of Technology,150001 Harbin, People's Republic of China;

    Concordia University, Montreal, QuebecH3G2W1, Canada;

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