کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
6479415 1428536 2017 9 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Compressive strength of composite laminates with delamination-induced interaction of panel and sublaminate buckling modes
ترجمه فارسی عنوان
استحکام فشاری ورقه های کامپوزیتی با تعامل ناشی از خلل و خم حالت های خمشی پانل و تحت فشار
کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه سایر رشته های مهندسی مهندسی عمران و سازه
چکیده انگلیسی

Compression After Impact (CAI) strength is critical to the safety and weight of carbon fibre aircraft. In this paper, the standard aerospace industry practice of using separate analyses and tests for panel buckling and CAI strength is challenged. Composite panels with a range of stacking sequences were artificially delaminated and subject to compression testing in a fixture that allowed local sublaminate and global panel buckling modes to interact. Compared to panels without delamination, interaction of buckling modes reduced panel buckling strains by up to 29%. Similarly, compared to delaminated panels restrained against panel buckling, interaction reduced delamination propagation strains by up to 49%. These results are the first to indicate that restriction of interaction during CAI testing is unconservative and therefore potentially unsafe. A novel integration of an analytical Strip model, for sublaminate buckling driven delamination propagation, and a Shanley model, for determining increased local strain due to sublaminate-buckling-induced panel curvature, is used to calculate the reduction in strength due to buckling mode interaction. Assuming a typical sublaminate post to pre-buckling stiffness ratio of 0.65, the difference in integrated model and experimental results is <11% - a level of accuracy that will allow the integrated model to drive initial design studies.

ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Composite Structures - Volume 171, 1 July 2017, Pages 326-334
نویسندگان
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