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Effects of thermal and moisture cycling on the internal structure of stitched RTM laminatesConventional aerospace composites are strong and stiff in the directions parallel to the carbon fibers, but they are prone to delaminations and damage in the through-the-thickness directions. Recent research has shown that substantial improvements in damage tolerance are obtained from textile composites with Z-direction reinforcement provided by stitching, weaving, or braiding. Because of the mismatch in thermal and moisture expansion properties of the various material components, there is a potential for microcracks to develop in the resin matrix. These cracks can form to relieve the mechanical stresses that are generated during curing or in-service temperature cycles.
Document ID
19950022627
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Walker, Jeff (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Roundy, Lance (McDonnell Aircraft Co. Saint Louis, MO., United States)
Goering, Jon (McDonnell Aircraft Co. Saint Louis, MO., United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1993
Publication Information
Publication: NASA. Langley Research Center, Third NASA Advanced Composites Technology Conference, Volume 1, Part 1
Subject Category
Composite Materials
Accession Number
95N29048
Funding Number(s)
CONTRACT_GRANT: NAS1-18580
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19950022402Collected WorksThird NASA Advanced Composites Technology Conference, volume 1, part 2
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