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Comparison of Separation Shock for Explosive and Nonexplosive Release Actuators on a Small Spacecraft PanelFunctional shock, safety, overall system costs, and emergence of new technologies, have raised concerns regarding continued use of pyrotechnics on spacecraft. NASA Headquarters-Office of Chief Engineer requested Langley Research Center (LaRC) study pyrotechnic alternatives using non-explosive actuators (NEA's), and LARC participated with Lockheed Martin Missile and Space Co. (LMMSC)-Sunnyvale, CA in objectively evaluating applicability of some NEA mechanisms to reduce small spacecraft and booster separation event shock. Comparative tests were conducted on a structural simulator using five different separation nut mechanisms, consisting of three pyrotechnics from OEA-Aerospace and Hi-Shear Technology and two NEA's from G&H Technology and Lockheed Martin Astronautics (LMA)-Denver, CO. Multiple actuations were performed with preloads up to 7000 pounds, 7000 being the comparison standard. All devices except LMA's NEA rotary flywheel-nut concept were available units with no added provisions to attenuate shock. Accelerometer measurements were recorded, reviewed, processed into Shock Response Spectra (SRS), and comparisons performed. For the standard preload, pyrotechnics produced the most severe and the G&H NEA the least severe functional shock levels. Comparing all results, the LMA concept produced the lowest levels, with preload limited to approximately 4200 pounds. Testing this concept over a range of 3000 to 4200 pounds indicated no effect of preload on shock response levels. This report presents data from these tests and the comparative results.
Document ID
19970010358
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Lucy, M. H. (NASA Langley Research Center Hampton, VA United States)
Buehrle, R. D. (NASA Langley Research Center Hampton, VA United States)
Woolley, J. P. (Lockheed Martin Missile and Space Sunnyvale, CA United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1996
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:110257
NASA-TM-110257
Report Number: NAS 1.15:110257
Report Number: NASA-TM-110257
Accession Number
97N15548
Funding Number(s)
PROJECT: RTOP 233-10-14-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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