Mechanical properties and failure mechanisms of carbon fiber reinforced epoxy laminated composites
The mechanical behavior of quasi-isotropic and unidirectional epoxy-matrix carbon-fiber laminated composites subjected compressive loading at strain rates of 10{sup {minus}3} and 2000 s{sup {minus}1} are described. Failure in the studied composites was dominated by delamination which proceeded by brittle fracture of the epoxy-matrix. The matrix-fiber bonding in these composites is very strong and prevented the occurrence of significant fiber-pullout. The mode I delamination strain energy release rate of the unidirectional composites was determined using the double cantilever beam and hole in plate compression method. The DCB method indicated a significant R curve effect attributed to fiber bridging while the presently available hole in plate analytical methods show questionable validity for highly anisotropic materials.
- Research Organization:
- Los Alamos National Lab. (LANL), Los Alamos, NM (United States)
- Sponsoring Organization:
- Department of Defense, Washington, DC (United States)
- DOE Contract Number:
- W-7405-ENG-36
- OSTI ID:
- 101065
- Report Number(s):
- LA-UR-95-2772; CONF-950846-26; ON: DE95016943
- Resource Relation:
- Conference: American Physical Society biennial conference on shock compression of condensed matter, Seattle, WA (United States), 13-18 Aug 1995; Other Information: PBD: [1995]
- Country of Publication:
- United States
- Language:
- English
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