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Multi-Functional Sandwich Composites for Spacecraft Applications: An Initial AssessmentCurrent spacecraft implement relatively uncoupled material and structural systems to address a variety of design requirements, including structural integrity, damage tolerance, radiation protection, debris shielding and thermal insulation. This investigation provided an initial assessment of multi-functional sandwich composites to integrate these diverse requirements. The need for radiation shielding was addressed through the selection of polymeric constituents with high hydrogen content. To provide increased damage tolerance and debris shielding, manufacturing techniques were developed to incorporate transverse stitching reinforcement, internal layers, and a self-healing ionomer membrane. To assess the effects of a space environment, thermal expansion behavior of the candidate foam materials was investigated under a vacuum and increasing temperature. Finally, a thermal expansion model was developed for foam under vacuum conditions and its predictive capability assessed.
Document ID
20070022458
Document Type
Contractor Report (CR)
Authors
Adams, Daniel O. (Utah Univ. Salt Lake City, UT, United States)
Webb, Nicholas Jason (Utah Univ. Salt Lake City, UT, United States)
Yarger, Cody B. (Utah Univ. Salt Lake City, UT, United States)
Hunter, Abigail (Utah Univ. Salt Lake City, UT, United States)
Oborn, Kelli D. (Utah Univ. Salt Lake City, UT, United States)
Date Acquired
August 23, 2013
Publication Date
June 1, 2007
Subject Category
Composite Materials
Report/Patent Number
NASA/CR-2007-214880
Funding Number(s)
CONTRACT_GRANT: NAG1-03085
WBS: WBS 732759.07.09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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