Compression behavior of ultra-high modulus carbon/epoxy composites using ASTM D6641 and SACMA SRM 1R-94

Abstract

The compression modulus and compression strength of a proprietary ultra-high modulus carbon/epoxy composite are experimentally determined using SACMA SRM 1R-94 and ASTM D6641 for laminates with stacking sequences of [(0/ ± 60)_s]₂ and [(+60/0/−60)_s]₂. The moduli of both laminates are experimentally shown to be statistically equivalent; the strength of the [(0/ ± 60)_s]₂ laminate is shown to be significantly less than the [(+60/0/−60)_s]₂ laminate. A finite element model is developed for each compression test to predict the compression modulus and compression strength using the built-in damage progression algorithm in Abaqus. Premature end crushing is predicted in the modulus specimen of SACMA SRM 1R-94 for the [(+60/0/60)_s]₂ laminate. End crushing in the modeled SACMA SRM 1R-94 strength specimen is predicted to occur immediately after ultimate laminate failure for the [(+60/0/60)_s]₂ laminate. Fiber misalignment is found to significantly affect the predicted compression modulus and compression strength of the ultra-high modulus carbon/epoxy composite analyzed.

Keywords

ASTM D6641 SACMA SRM 1R-94 ANOVA finite element analysis nonlinear damage fracture energy compression modulus compression strength Abaqus

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