Early in the Vanguard program it became apparent that a thoroughly reliable means of separating the satellite packages from the third-stage rocket would be required. A completely self -contained standard mechanism was developed with redundant firing circuits for use on both test vehicles and satellite-launching vehicles. A change in the experimental objectives of the test-vehicle payload units necessitated modification of some of the standard separation mechanisms. A strap, pull-pin, girth-ring separation device was developed which employed the basic actuation of the standard mechanisms. Evidence of residual burning of the third stage made it necessary to delay separation longer than the time designed into the long-delay separation device. The standard separation mechanism was modified and integrated with the satellite command receiver system so that a ground command after third-stage burnout would cause separation. Flight performance of the various separation mechanisms proved their reliability; they performed without failure in all Vanguard launchings.
Vanguard Satellite Separation Mechanisms
1961
26 pages
Report
No indication
English
Unmanned Spacecraft , Manned Spacecraft , Vanguard satellites , External store separation , Mechanism , Mechanical devices , Fabrication , Test vehicles , Straps , Spacecraft launching , Reliability , Receivers , Pins , Payloads , Flight characteristics , Fire control circuits , Failure , Delay circuits , Combustion , Burnout
Vanguard Satellite Separation Mechanisms
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|Vanguard satellite separation mechanisms
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|Vanguard I Satellite Structure and Separation Mechanism
NTRS | 1961
|Vanguard I satellite structure and separation mechanism
TIBKAT | 1961
|Vanguard I Satellite Structure and Separation Mechanism
NTIS | 1961
|