Influence of interface ply orientation on delamination growth in composite laminates
نویسندگان
چکیده
The standard experimental procedures for determining the interlaminar fracture toughness are designed delamination propagation in unidirectional specimens. However, aerospace structural components, usually occurs between plies at different orientations resulting damage mechanisms which can increase value of as propagates. Generally, numerical analyses employ measured onset, leading to conservative results since resistance is neglected. In this paper, and R-curves carbon/epoxy IM7/8552 experimentally evaluated coupons with positioned 0°/0° 45°/?45° interfaces using Double Cantilever Beam (DCB) Mixed-Mode Bending (MMB) tests. A simplified approach based on Virtual Crack Closure Technique (VCCT) developed simulate variable length within a Finite Element code predefined field variable. compared data terms load-displacement curves demonstrate effectiveness proposed technique simulating interface.
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ژورنال
عنوان ژورنال: Journal of Composite Materials
سال: 2021
ISSN: ['1530-793X', '0021-9983']
DOI: https://doi.org/10.1177/00219983211031636