During service life structures made of laminated composites are subjected to complex combinations of thermo-mechanical and environmental loads. The final macroscopic failure of composite laminate is preceded by initiation and evolution of several microdamage modes in layers. This is because the transverse tensile strain to failure of unidirectional composites is lower than other failure strain components. Therefore transverse cracking of layers with off-axis orientation with respect to the main load direction, caused by combined action of transverse tensile stress and shear stress, is usually the first mode of damage (Parvizi and Bailey, J. Mater. Sci. 13:2131–2136, 1978 [1]; Jamison et al., ASTM STP 836:21–55, 1984 [2]).
Microdamage Modeling in Laminates
Springer Aerospace Techn.
2015-01-08
33 pages
Article/Chapter (Book)
Electronic Resource
English
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