書誌事項
- タイトル別名
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- Face Sheet Buckling Behavior of a CFRP/Honeycomb Sandwich Panel for Aircraft Interiors Subjected to Edgewise Compression
- 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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抄録
<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>
収録刊行物
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- 日本複合材料学会誌
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日本複合材料学会誌 49 (2), 33-40, 2023-03-15
一般社団法人 日本複合材料学会
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詳細情報 詳細情報について
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- CRID
- 1390017965044150912
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- NII書誌ID
- AN00196748
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- ISSN
- 18848559
- 03852563
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- NDL書誌ID
- 032775382
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- NDL
- Crossref
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- 抄録ライセンスフラグ
- 使用不可