Abstract
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.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
