Dynamics and 3-axes control of a spacecraft with flexible structures

M. Nohmi, M. Uchiyama

    Research output: Chapter in Book/Report/Conference proceedingChapter

    Abstract

    This paper describes the dynamics and control of a spacecraft with flexible structures in gravitational field. We propose a simple model of the spacecraft. The motion of the model is controlled only by reaction wheels. Focusing especially on the time for damping, the effect of control gains for suppressing the vibrations is examined. The effect of three-axes attitude control of the model at various attitudes in gravitational field is clarified, considering the gravity gradient torques. Simulation results of orbital motion suggest two important conclusions. One is that the orbital periodic vibrations occur due to the reaction wheels at a certain attitude. The other is that the amplitude of the orbital periodic vibrations depends on the control gains for the attitude angles of the rigid body.

    Original languageEnglish
    Title of host publicationProceedings of the IEEE Conference on Decision and Control
    Editors Anon
    Pages2355-3592
    Number of pages1238
    Publication statusPublished - 1996 Dec 1
    EventProceedings of the 1996 35th IEEE Conference on Decision and Control. Part 3 (of 4) - Kobe, Jpn
    Duration: 1996 Dec 111996 Dec 13

    Publication series

    NameProceedings of the IEEE Conference on Decision and Control
    Volume3
    ISSN (Print)0191-2216

    Other

    OtherProceedings of the 1996 35th IEEE Conference on Decision and Control. Part 3 (of 4)
    CityKobe, Jpn
    Period96/12/1196/12/13

    ASJC Scopus subject areas

    • Control and Systems Engineering
    • Modelling and Simulation
    • Control and Optimization

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  • Cite this

    Nohmi, M., & Uchiyama, M. (1996). Dynamics and 3-axes control of a spacecraft with flexible structures. In Anon (Ed.), Proceedings of the IEEE Conference on Decision and Control (pp. 2355-3592). (Proceedings of the IEEE Conference on Decision and Control; Vol. 3).