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Prediction of Composite Laminate Fracture: Micromechanics and Progressive FractureThis report describes an investigation to predict first-ply failure and final fracture in selected composite laminates subjected to inplane loads. The laminates were composed of glass fiber and graphite fibers in epoxy matrices. Failure envelopes based on first-ply failure and laminate fracture were generated for combined loading of these laminates. Predictions were evaluated by micromechanics-based theory and progressive fracture. The results show that, for most cases, combined tensile loading significantly enhanced the laminate fracture stress in comparison to the uniaxial loading.
Document ID
19970010089
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Gotsis, P. K. (NASA Lewis Research Center Cleveland, OH United States)
Chamis, C. C. (NASA Lewis Research Center Cleveland, OH United States)
Minnetyan, L. (Clarkson Univ. Potsdam, NY United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1996
Subject Category
Structural Mechanics
Report/Patent Number
NAS 1.15:107331
E-10456
NASA-TM-107331
Accession Number
97N15324
Funding Number(s)
PROJECT: RTOP 505-63-5B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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