کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
10628211 | 990176 | 2005 | 13 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Stiffener debonding mechanisms in post-buckled CFRP aerospace panels
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کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه
مهندسی مواد
سرامیک و کامپوزیت
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چکیده انگلیسی
This paper describes the fractographic analysis of five CFRP post-buckled skin/stringer panels that were tested to failure in compression. The detailed damage mechanisms for skin/stiffener detachment in an undamaged panel were characterised and related to the stress conditions during post-buckling; in particular the sites of peak twist (at buckling nodes) and peak bending moments (at buckling anti-nodes). The initial event was intralaminar splitting of the +45° plies adjacent to the skin/stiffener interface, induced by high twist at a nodeline. This was followed by mode II delamination, parallel to ±45° plies and then lengthwise (0°) shear along the stiffener centreline. The presence of defects or damage was found to influence this failure process, leading to a reduction in strength. This research provides an insight into the processes that control post-buckled performance of stiffened panels and suggests that 2D models and element tests do not capture the true physics of skin/stiffener detachment: a full 3D approach is required.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Composites Part A: Applied Science and Manufacturing - Volume 36, Issue 7, July 2005, Pages 934-946
Journal: Composites Part A: Applied Science and Manufacturing - Volume 36, Issue 7, July 2005, Pages 934-946
نویسندگان
Charlotte Meeks, Emile Greenhalgh, Brian G. Falzon,