Compression response of laminated composites containing an open hole
Journal Article
·
· SAMPE Q.; (United States)
OSTI ID:6599048
An analytical and experimental investigation was performed to study the inplane failure and laminated composites containing an open hole and subjected to compressive loadings. A progressive damage model was developed during the investigation to predict both the types, as well as size, of internal damage in the laminates and the complete response of the laminates from initial loading to final collapse. In the model, stresses and strains inside the laminates were calculated by a nonlinear finite element analysis which is based on the finite deformation theory with consideration of material and geometric nonlinearities. The types and size of damage were predicted by a failure analysis which includes a set of proposed failure criteria and material degradation models for the damaged area. In order to verify the model, experiments were also conducted. T300/976 graphite/epoxy prepregs were selected for the tests. An excellent agreement was found between the test results and the calculations based on the model. 35 references, 8 figures.
- Research Organization:
- Stanford Univ., CA (USA)
- OSTI ID:
- 6599048
- Journal Information:
- SAMPE Q.; (United States), Journal Name: SAMPE Q.; (United States) Vol. 19:4; ISSN SAMQA
- Country of Publication:
- United States
- Language:
- English
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