A reevaluation of the Vanguard program objectives in January 1957 resulted in the production of the Vanguard I Satellite, a 6.44-inch-diameter, 3.25-pound sphere with six equally spaced solar cell clusters and six equally spaced antennas mounted on its surface. Experiment requirements necessitated the development of a mechanism to separate the satellite from the third-stage rocket. On the basis of the existing standard separation mechanism, a strap pull-pin girth-ring arrangement was developed. Both the satellite and the separation mechanism were fully tested prior to flight. Successful orbiting and flight operation proved the adequacy of the design.


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    Title :

    Vanguard I Satellite Structure and Separation Mechanism


    Contributors:

    Publication date :

    1961-03-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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    Shea, John T. / Baumann, Robert C. | TIBKAT | 1961


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    J. T. Shea / R. C. Baumann | NTIS | 1961


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    Shea, J.T. / Baumann, R.C. | Engineering Index Backfile | 1961


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    Baumann, Robert C. | NTRS | 1961