Abstract The attitude dynamics of a fast rotating triaxial satellite under gravity-gradient is revisited. The essentially unique reduction of the Euler-Poinsot Hamiltonian, which can be performed in different sets of variables, provides a suitable set of canonical variables that expedites the perturbation approach. Two canonical transformations reduce the perturbed problem to its secular terms. The secular Hamiltonian and the transformation equations of the averaging are computed in closed form of the triaxiality coefficient, thus being valid for any triaxial body. The solution depends on Jacobi elliptic functions and integrals, and applies to non-resonant rotations under the assumption that the rotation rate is much higher than the orbital or precessional motion.


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    Titel :

    Closed form perturbation solution of a fast rotating triaxial satellite under gravity-gradient torque


    Beteiligte:
    Lara, M. (Autor:in) / Ferrer, S. (Autor:in)

    Erschienen in:

    Cosmic Research ; 51 , 4 ; 289-303


    Erscheinungsdatum :

    2013




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    50.93 Weltraumforschung / 39.00 Astronomie: Allgemeines / 55.60 Raumfahrttechnik
    Lokalklassifikation TIB:    770/3520/8000




    Complete Closed Form Solution of a Tumbling Triaxial Satellite Under Gravity-Gradient Torque (AAS 12-119)

    Lara, M. / Ferrer, S. / American Astronautical Society et al. | British Library Conference Proceedings | 2012



    Appendix C Gravity Gradient Torque

    Ramnath, Rudrapatna V. | AIAA | 2010