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Composites airframe panel design for post-buckling - An experimental investigation

机译：后屈曲的复合材料机身面板设计-实验研究

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摘要

Three series of airframe composite panels with T-stiffener, I-stiffener and J-stiffener are designed and optimized to have the same local skin buckling load and weight. All the panels are designed to undergo local skin buckling between Design Limit Load (DLL) and Design Ultimate Load (DUL), approximately at 120% of DLL to utilize the reserve strength in structures. Additionally, identical panels are designed and fabricated from each series to study the effect of various extrinsic parameters such as disbond, delamination, impact damage and repeated loading to identify the best performing series for post-buckling design. All the panels are tested under compression to demonstrate no onset of damage before DUL. The influence of defects such as disbond, delamination and impact damage on the post-buckling behavior is also demonstrated. One pristine panel of each series is repeatedly loaded 1000 times beyond buckling to determine the onset of damage if any. The panels with I-stiffener and J-stiffener found to be the potential design choices for post-buckling design philosophy due to the high margin between skin buckling and collapse load even in the presence of damage. The results from this study would help in moving closer to the post-buckled composite design philosophy for airframe structure.
机译：设计并优化了三个系列的带有T型加劲肋，I型加劲肋和J型加劲肋的机身复合板，以具有相同的局部蒙皮屈曲载荷和重量。所有面板的设计均在设计极限载荷（DLL）和设计极限载荷（DUL）之间进行局部屈曲，大约为DLL的120％，以利用结构中的储备强度。此外，每个系列均设计和制造相同的面板，以研究各种外部参数（例如剥离，分层，冲击破坏和反复加载）的影响，从而确定屈曲后设计最佳性能系列。所有面板均经过压缩测试，以证明在DUL之前没有损坏开始。还证明了诸如脱胶，分层和冲击损伤等缺陷对屈曲后行为的影响。每个系列的一个原始面板被反复加载超过屈曲1000次，以确定是否发生损坏。发现具有I型加劲肋和J型加劲肋的面板是屈曲后设计理念的潜在设计选择，因为即使在存在损坏的情况下，蒙皮屈曲和坍塌载荷之间的裕度也很高。这项研究的结果将有助于进一步接近机身结构的后屈曲复合设计理念。

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