Penetration of carbon-fabric-reinforced composites by edge cracks during thermal aging
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Penetration of carbon-fabric-reinforced composites by edge cracks during thermal aging

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Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English


  • Aging (Materials).,
  • Carbon fiber reinforced plastics.,
  • Crack initiation.,
  • Crack propogation.,
  • Cracks.,
  • Edges.,
  • Fracture mechanics.,
  • Laminates.,
  • Microstructure.,
  • Microstructure.,
  • Thermal degradation.,
  • Voids.

Book details:

Edition Notes

Other titlesPenetration of carbon fabric reinforced ...
StatementKenneth J. Bowles and John E. Kamvouris.
SeriesNASA technical memorandum -- 106530.
ContributionsKamvouris, John E., United States. National Aeronautics and Space Administration.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL15404208M

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The U.S. Department of Energy's Office of Scientific and Technical Information. A study was conducted to determine the effects of long-term isothermal thermo-oxidative aging on the compressive properties ofT fabric reinforced PMR composites. The temperatures that were studied were , , , , and 0c. Specimens of different geometries were evaluated. Cut edge-to-surface ratios of. the tested specimens show valid failure modes for composites used in aeronautical industry. Keywords: composites, epoxy resin, carbon fibers, tensile test 1. Introduction Carbon fabric reinforced polymeric composites are very used for manufacturing components as flaps, aileron, landing-gear doors, and other artifacts used in aeronautical. The results show that the three carbon fiber composites with the same resin matrix possess different hygrothermal resistances of interface and the interfacial fracture energy after water aging .

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