TY - JOUR
T1 - The characterization of Mode I delamination failure in non-woven, multidirectional laminates
AU - Chai, H.
N1 - Funding Information:
The majority of this work was carried out under the in-house programme of the Nonmetallic Division, Materials Laboratory, AFWAL/MLBM, Wright-Patterson Air Force Base, OH. The first phase of this work was supported by NASA-Langley under grant NSG-1483. Both of these supports are greatly appreciated. The author is grateful to Dr C.D. Babcock of Caltech and Dr S.W. Tsai of the Air Force Materials Laboratory for their encouragemenL support and fruitful discussions. Thanks are also due to Mr R.J. Bacon of Systems Research Laboratories for his assistance in the SEM wore
PY - 1984/10
Y1 - 1984/10
N2 - The Mode I delamination failure of fibre-reinforced epoxy laminates was characterized using the uniform double cantilever beam test specimen and scanning electron microscopy. Generally, this failure appeared in a variety of forms, depending on ply orientation, test-specimen geometry and matrix toughness. The calculated fracture energy heavily depended on the fracture surface morphology. By defining interlaminar fracture strictly as an interlaminar separation including no fibre breakage, pull-out, etc, a material property independent of test-specimen geometry and orientation of the plies constituting the delaminating interface was elucidated. Since this quantity dissipated the least amount of energy possible during crack growth, it is the controlling factor for laminate toughness.
AB - The Mode I delamination failure of fibre-reinforced epoxy laminates was characterized using the uniform double cantilever beam test specimen and scanning electron microscopy. Generally, this failure appeared in a variety of forms, depending on ply orientation, test-specimen geometry and matrix toughness. The calculated fracture energy heavily depended on the fracture surface morphology. By defining interlaminar fracture strictly as an interlaminar separation including no fibre breakage, pull-out, etc, a material property independent of test-specimen geometry and orientation of the plies constituting the delaminating interface was elucidated. Since this quantity dissipated the least amount of energy possible during crack growth, it is the controlling factor for laminate toughness.
KW - Mode I fracture energy
KW - composite materials
KW - delamination
KW - matrix toughness
KW - ply orientation
UR - http://www.scopus.com/inward/record.url?scp=0021505859&partnerID=8YFLogxK
U2 - 10.1016/0010-4361(84)90708-0
DO - 10.1016/0010-4361(84)90708-0
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AN - SCOPUS:0021505859
VL - 15
SP - 277
EP - 290
JO - Composites - Part A: Applied Science and Manufacturing
JF - Composites - Part A: Applied Science and Manufacturing
SN - 1359-835X
IS - 4
ER -