An approach is presented for attitude determination of a three axis stabilized spacecraft. The employment of two independent vectors is described whose components with respect to two reference coordinate axes can be known. Such two coordinate axes are right-handed three mutually orthogonal axes systems of which one is fixed in the spacecraft and the other has known orientation in space. The relationship between the two systems are then expressed as mathematical equations with the use of the two reference vectors. By computing the derived equations, the attitude of the spacecraft can be obtained.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    The attitude determination of a three axes stabilized spacecraft


    Contributors:
    Fang, A. C. (author)

    Publication date :

    1971-09-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :




    Three-axes attitude determination of spacecraft using a laser

    Aruga, T. / Igarashi, T. | Tema Archive | 1977


    Attitude Control of Three-Axes Stabilized Spacecraft with Flexible Appendages, Volume 2

    R. S. Harris / D. C. Todman / M. J. Hammond et al. | NTIS | 1977


    Multirate three axes attitude stabilization of spacecraft

    Monaco, S. / Normand-Cyrot, D. / Stornelli, S. | Tema Archive | 1989