On the second flight of the INTELSAT V spacecraft the time required for successful deployment of the north solar array was longer than originally predicted. The south solar array deployed as predicted. As a result of the difference in deployment times a series of experiments was conducted to locate the cause of the difference. Deployment rate sensitivity to hinge friction and temperature levels was investigated. A digital computer simulation of the deployment was created to evaluate the effects of parameter changes on deployment. Hinge design was optimized for nominal solar array deployment time for future INTELSAT V satellites. The nominal deployment times of both solar arrays on the third flight of INTELSAT V confirms the validity of the simulation and design optimization.


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    Titel :

    Design and analysis considerations for deployment mechanisms in a space environment


    Beteiligte:
    Vorlicek, P. L. (Autor:in) / Gore, J. V. (Autor:in) / Plescia, C. T. (Autor:in)


    Erscheinungsdatum :

    01.05.1982


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Design Considerations and Deployment Simulations of Spinning Space Webs

    Gärdsback, Mattias / Tibert, Gunnar / Izzo, Dario | AIAA | 2007




    Deployment Mechanisms

    Sebestyen, George / Fujikawa, Steve / Galassi, Nicholas et al. | Springer Verlag | 2018


    Space Habitat Design Considerations Related to Different Gravity Environment

    Bannova, O. / American Society of Civil Engineers | British Library Conference Proceedings | 2004