Study is made of attitude errors of satellite in equatorial orbit at altitudes for which solar radiation pressure is dominant disturbance; there are two methods to minimize solar induced attitude errors and their limitations are examined; attitude errors of split-damper are compared with those of slotted one-piece damper whose hinge is at top or bottom of stabilized package; latter scheme also avoids slot, but violates symmetry; it is shown that chief disadvantage of split-damper scheme stems from design constraints needed to minimize excitation of additional mode of motion introduced by split.


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    Title :

    Split-damper inertially coupled passive gravity-gradient attitude control system


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1967


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    A split-damper inertially coupled passive gravity-gradient attitude control system.

    Merrick, V. K. / Tinling, B. E. / Watson, D. M. | NTRS | 1966


    A split-damper inertially coupled passive gravity-gradient attitude control system.

    Merrick, V. K. / Tinling, B. E. / Watson, D. M. | NTRS | 1967


    A split-damper inertially coupled passive gravity-gradient attitude control system.

    MERRICK, V. K. / TINLING, B. E. / WATSON, D. M. | AIAA | 1967