Vanguard I Satellite Structure and Separation Mechanism

Vanguard I Satellite Structure and Separation Mechanism PDF

Author: John T. Shea

Publisher:

Published: 1961

Total Pages: 22

ISBN-13:

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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

Vanguard I Satellite Structure and Separation Mechanism PDF

Author: John T. Shea

Publisher:

Published: 1961

Total Pages: 26

ISBN-13:

DOWNLOAD EBOOK →

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 Satellite Separation Mechanisms

Vanguard Satellite Separation Mechanisms PDF

Author: Robert C. Baumann

Publisher:

Published: 1961

Total Pages: 28

ISBN-13:

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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 Spin-reduction Mechanism

Vanguard Satellite Spin-reduction Mechanism PDF

Author: Robert C. Baumann

Publisher:

Published: 1961

Total Pages: 28

ISBN-13:

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The Cloud Cover Satellite flown in Vanguard vehicles SLV-3 and SLV-4 required a spin rate of 55 r.p.m. when entering orbit. Since the third-stage rocket was spin-stabilized in flight, and because other considerations required that the satellite remain attached long enough to acquire more than the desired 55 r.p.m., a satellite spin-reduction mechanism was developed. Although the mechanisms functioned properly in both flights, the desired spin rate was not achieved owing to uncontrollable flight effects. These effects make the prediction of satellite spin rates after a long pre-separation coasting period extremely difficult. To meet future requirements a control system is needed which can orient a payload according to a predetermined scheme and maintain that orientation for the desired period.

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