An atmospheric flight vehicle in hover is typically controlled by varying its thrust vector. Achieving both levitation and control with the propulsion system places considerable demands on it for agility and precision, particularly if the vehicle is statically unstable, or nearly so. These demands can be relaxed by introducing an appropriately sized angular momentum bias about the vehicle's yaw axis, thus providing an additional margin of attitude stability about the roll and pitch axes. This paper describes an approach for specifying the appropriate size of such angular momentum bias, based on the vehicle s physical parameters and its disturbance environment. It also describes several simplifications that provide a more physical and intuitive understanding of the dynamics. This will enhance the possibility of practically applying this technology to a flying vehicle.


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    Titel :

    Bias Momentum Sizing for Hovering Dual-Spin Platforms


    Beteiligte:
    Lim, K. B. (Autor:in) / Shin, J-Y. (Autor:in) / Moerder, D. D. (Autor:in)

    Kongress:

    AIAA Guidance, Navigation, and Control Conference and Exhibit ; 2005 ; San Francisco, CA, United States


    Erscheinungsdatum :

    01.01.2005


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch




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    Bias Momentum Sizing for Hovering Dual-Spin Platforms

    K. B. Lim / J. Y. Shin / D. D. Moerder | NTIS | 2006


    Bias Momentum Sizing for Hovering Dual-Spin Platforms

    Lim, Kyong / Shin, Jeong-Yeop / Moerder, Daniel | AIAA | 2005



    Hovering Dual-Spin Vehicle Groundwork for Bias Momentum Sizing Validation Experiment

    Rothhaar, Paul M. / Moerder, Daniel D. / Lim, Kyong B. | NTRS | 2008