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.
Vanguard I Satellite Structure and Separation Mechanism
1961-03-01
Miscellaneous
No indication
English
Vanguard I satellite structure and separation mechanism
TIBKAT | 1961
|Vanguard I Satellite Structure and Separation Mechanism
NTIS | 1961
|Vanguard I satellite structure and separation mechanism
Engineering Index Backfile | 1961
|Vanguard satellite separation mechanisms
Engineering Index Backfile | 1961
|Vanguard Satellite Separation Mechanisms
NTRS | 1961
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