Such vehicles, typified by Orbiting Solar Observatory satellites, have applicability to missions for which simplicity, reliability, and longevity of spin stabilization combine with requirement for unidirectional pointing of component, such as antenna or solar panel; analysis reveals possibility of obtaining passive stable spin-axis attitude by spinning vehicle about its axis of greatest or least inertia, providing only that effective energy dissipation device is attached to counter-rotating platform which has greatly reduced "spin".


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    Title :

    Attitude stability criteria for dual spin spacecraft


    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 :