Face Sheet Buckling Behavior of a CFRP/Honeycomb Sandwich Panel for Aircraft Interiors Subjected to Edgewise Compression
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- YOSHINAGA Hajime
- Graduate Student, Tokyo University of Agriculture and Technology Jamco Corporation
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- OGASAWARA Toshio
- Professor, Tokyo University of Agriculture and Technology
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- OGURI Tsuyoshi
- Jamco Corporation
Bibliographic Information
- Other Title
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- 航空機内装用CFRP/ハニカムサンドイッチパネルのエッジワイズ圧縮試験における表面材座屈挙動
- コウクウキ ナイソウヨウ CFRP/ハニカムサンドイッチパネル ノ エッジワイズ アッシュク シケン ニ オケル ヒョウメンザイザクツキョドウ
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Abstract
<p> As an alternative evaluation method to the four-point bending test, a strength evaluation and prediction method for carbon-fiber-reinforced polymer (CFRP)/Nomex honeycomb sandwich panels for aircraft interiors was investigated using edgewise compression tests. The failure mode of the edgewise compression test was experimentally demonstrated to be identical to that of the four-point bending test, that is, the delamination between the face sheet (CFRP) and core originated from face sheet local buckling. The same origin of failure was confirmed by buckling eigenvalue analysis. Furthermore, it was demonstrated that the calculation accuracy of buckling load analysis can be improved by using postbuckling analysis, which considers the initial irregularity. The computation time for buckling eigenvalue analysis by edgewise compression can be reduced to 1/100 of that required for bending analysis. Therefore, it is expected to reduce the development cost for optimizing the material configuration of sandwich panels using edgewise compression analysis.</p>
Journal
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- Journal of the Japan Society for Composite Materials
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Journal of the Japan Society for Composite Materials 49 (2), 33-40, 2023-03-15
The Japan Society for Composite Materials
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Keywords
Details 詳細情報について
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- CRID
- 1390017965044150912
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- NII Book ID
- AN00196748
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- ISSN
- 18848559
- 03852563
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- NDL BIB ID
- 032775382
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- Text Lang
- en
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- Data Source
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- JaLC
- NDL
- Crossref
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- Abstract License Flag
- Disallowed