Thermal elastic shock (TES) is a twice per orbit impulsive disturbance torque experienced by low-Earth orbiting spacecraft. The fundamental equations used to model the TES disturbance torque for typical spacecraft appendages (e.g., solar arrays and antenna booms) are derived in detail. In particular, the attitude-pointing performance of the TOPEX spacecraft, when subjected to the TES disturbance, is analyzed using a three-axis nonlinear time-domain simulation. Results indicate that the TOPEX spacecraft could exceed its roll-axis attitude-control requirement during penumbral transitions, and remain in violation for approximately 150 sec each orbit until the umbra collapses. A localized active-control system is proposed as a solution to minimize and/or eliminate the degrading effects of the TES disturbance.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Thermal elastic shock and its effect on TOPEX spacecraft attitude control


    Beteiligte:


    Erscheinungsdatum :

    01.01.1991


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Dynamic attitude command and control of the TOPEX/Poseidon spacecraft

    ZIMBELMAN, D. / LEE, B. / WELCH, R. | AIAA | 1991


    Dynamic attitude command and control of the TOPEX/Poseidon spacecraft

    Zimbelman, D. F. / Lee, B. B. / Welch, R. V. | NTRS | 1991



    Attitude determination and control subsystem for the TOPEX satellite

    Dennehy, C. J. / Welch, R. V. / Kia, T. | NTRS | 1988


    Attitude determination and control subsystem for the TOPEX satellite

    DENNEHY, C. / WELCH, R. / KIA, T. | AIAA | 1988