کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
253307 502996 2008 8 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Failure analysis in postbuckled composite T-sections
موضوعات مرتبط
مهندسی و علوم پایه سایر رشته های مهندسی مهندسی عمران و سازه
پیش نمایش صفحه اول مقاله
Failure analysis in postbuckled composite T-sections
چکیده انگلیسی

Blade-stiffened skin designs made of composite materials have the potential to produce highly efficient structures, when the large strength reserves in the postbuckling range are utilised. This paper investigates the failure under postbuckling deformations of T-section specimens cut from a blade-stiffened panel, by comparing experimental results to finite element models. In the experimental work, T-section specimens with a particular lay-up and geometry were tested to failure in antisymmetric and symmetric loading rigs. These loading rigs simulate deformations on skin-stiffener interfaces during panel postbuckling. For the numerical analysis, two-dimensional models of the interface cross-section were used with a strength-based criterion that monitored failure within each ply. The use of a zero-thickness layer of cohesive elements has also been investigated in order to simulate the delamination behaviour. The numerical predictions are compared to the experimental results in terms of the failure load, specimen stiffness and specimen behaviour. The analysis approach is shown to be capable of predicting the critical damage locations and initiation loads for both antisymmetric and symmetric loadings. The successful prediction of failure in skin-stiffener interfaces can be linked to a global-local approach for efficient analysis of large, fuselage-representative composite structures.

ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Composite Structures - Volume 86, Issues 1–3, November 2008, Pages 146–153
نویسندگان
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