Abstract
Consideration is given to failure of filament-dominated laminates subjected to compression loading. Of particular interest is the interaction between longitudinal compression loading and transverse loading (tension and compression). Data obtained in conjunction with a mini-sandwich specimen are used to generate failure stresses. Classical lamination theory, including thermal residual stresses due to cure is utilized for determining ply stresses. Residual stresses are based on initial elastic properties, while mechanical stresses are based on secant modulus at failure (compression stress-strain curve for both unidirectional and laminated composites is nonlinear at high strain levels). Experimental results reveal little interaction between longitudinal compression and transverse stresses as long as matrix-dominated modes such as transverse cracking and delamination are suppressed.
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