| タイトル | Applications of a damage tolerance analysis methodology in aircraft design and production |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950022062 |
| 著者（英） | Woodward, M. R.; Owens, S. D.; Law, G. E.; Mignery, L. A. |
| 著者所属（英） | General Dynamics Corp. |
| 発行日 | 1992-09-01 |
| 言語 | eng |
| 内容記述 | Objectives of customer mandated aircraft structural integrity initiatives in design are to guide material selection, to incorporate fracture resistant concepts in the design, to utilize damage tolerance based allowables and planned inspection procedures necessary to enhance the safety and reliability of manned flight vehicles. However, validated fracture analysis tools for composite structures are needed to accomplish these objectives in a timely and economical manner. This paper briefly describes the development, validation, and application of a damage tolerance methodology for composite airframe structures. A closed-form analysis code, entitled SUBLAM was developed to predict the critical biaxial strain state necessary to cause sublaminate buckling-induced delamination extension in an impact damaged composite laminate. An embedded elliptical delamination separating a thin sublaminate from a thick parent laminate is modelled. Predicted failure strains were correlated against a variety of experimental data that included results from compression after impact coupon and element tests. An integrated analysis package was developed to predict damage tolerance based margin-of-safety (MS) using NASTRAN generated loads and element information. Damage tolerance aspects of new concepts are quickly and cost-effectively determined without the need for excessive testing. |
| NASA分類 | COMPOSITE MATERIALS |
| レポートNO | 95N28483 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/106931 |
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