A computational formulation for the dynamic analysis of spacecraft with deploying appendages is presented. The appendage model is based on a geometrically nonlinear beam formulation which accurately accounts for large rotational and large deformation motions. A moving finite element reference grid is incorporated within the nonlinear beam formulation to model the deployment motion. Hamilton's Law is used to formulate the general equations of motion, and a transient integration solution procedure is derived from a space-time finite element discretization of the Hamiltonian variational statement. Computational results of the methodology are presented for a classical gravity gradient stabilized satellite configuration.


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    Titel :

    Dynamics of spacecraft with deploying flexible appendages


    Beteiligte:
    Downer, Janice D. (Autor:in) / Park, K. C. (Autor:in)

    Kongress:

    AIAA Dynamics Specialists Conference ; 1992 ; Dallas, TX, United States


    Erscheinungsdatum :

    1992-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Dynamics of spacecraft with deploying flexible appendages

    DOWNER, JANICE / PARK, K. | AIAA | 1992


    Approximate Solutions for Attitude Dynamics of a Spacecraft with Deploying Flexible Appendages

    Li, J. / Wang, Z. / International Federation of Automatic Control et al. | British Library Conference Proceedings | 1997