The failure mechanisms of a woven 2-D carbon/polyimide (C/P) laminate have been determined under in-plane uniaxial and biaxial compressive loads, and the associated failure envelopes that account for the effect of loading directions were obtained. The overall failure was primarily in the form of axial interply delaminations aligned with the principal axis of loading, with only a few isolated events of kinking in the bundles. While the biaxial strength varied significantly with the ratio of in-plane stresses, R, there was no variation in the local failure mechanisms. Accordingly, it was found that the composite fails upon achieving a maximum strain along the primary axis of loading.
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