Actions for Testing for Random Limit Load Versus Static Limit Load

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Testing for Random Limit Load Versus Static Limit Load

Author
Lee, H. M.
Published
Sep. 1997.
Physical Description
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
This document is an effort to report the basic test findings in an ongoing quest for understanding how random load factors should be applied to structural components in order to verify the strength of space flight hardware. A Spacelab experiment known as the Atmospheric Emission Photometric Imager (AEPI) was subjected to both an expected flight random environment and the associated Miles' equation equivalent static load. During each of these tests, the fiberglass pedestal was instrumented with 16 triaxial strain gauges around its base. Component strains and invariant stresses were compared. As seen previously in other hardware tests, the stress distribution from the random environment was an order of magnitude below the comparable static stresses. With a proposed data acquisition system, a strain database will be developed that will quantify an empirical relationship between dynamic and static limit stresses. This event will allow a more accurate estimate of launch environment effects on new technology structural components.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19970028919.
Accession ID: 97N27636.
NASA-TM-108542.
NAS 1.15:108542.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15647295