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Pin puller impact shock attenuationDesign of a pin arresting mechanism for a pyrotechnically actuated pin puller is reviewed. The investigative approach is discussed and the impact shock test results for various candidate designs are presented. The selected pin arresting design reduced the peak value of the shock response spectrum by five to one.
Document ID
19760021191
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Auclair, G. F. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Leonard, B. S. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Robbins, R. E. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Proffitt, W. L. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Date Acquired
August 8, 2013
Publication Date
July 1, 1976
Publication Information
Publication: JPL 10th Aerospace Mech. Symp.
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
76N28279
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19760021184Collected WorksTenth Aerospace Mechanisms Symposium
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