The primary function of a spacecraft attitude control subsystem is the attitude determination and, more generally, the state estimation (attitude of the main body, appendages and flexible modes). The so-called optical-inertial concept is first described with application to a number of modern spacecraft; an example of implementation using space-qualified microprocessors is given in detail; the state estimation of a flexible spacecraft is then considered, a technique which can be readily implemented on existing hardware. The extension of this concept to autonomous orbit control of an orbiting spacecraft is then considered for future development. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Multifunction Spacecraft Attitude Estimation and Navigation System


    Beteiligte:
    J. C. Amieux (Autor:in) / B. Claudinon (Autor:in)

    Erscheinungsdatum :

    1984


    Format / Umfang :

    17 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Attitude Determination and Attitude Estimation in Aircraft and Spacecraft Navigation. A survey

    Dhahbane, Djamel / Nemra, Abdelkrim / Sakhi, Samir | IEEE | 2021


    Spacecraft Attitude Estimation Under Agility Constraints

    Schiemenz, Fabian | BASE | 2015

    Freier Zugriff

    ATTITUDE ESTIMATION FOR DOCKING OF SPACECRAFT

    JIN WOO SONG / DONG YUN HWANG / JIN HYEON PARK et al. | Europäisches Patentamt | 2025

    Freier Zugriff