| タイトル | Structural Stability of a Stiffened Aluminum Fuselage Panel Subjected to Combined Mechanical and Internal Pressure Loads |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040085782 |
| 著者（英） | Young, Richard D.; Rouse, Marshall; Gehrki, Ralph R. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2003-01-01 |
| 言語 | eng |
| 内容記述 | Results from an experimental and analytical study of a curved stiffened aluminum panel subjected to combined mechanical and internal pressure loads are presented. The panel loading conditions were simulated using a D-box test fixture. Analytical buckling load results calculated from a finite element analysis are presented and compared to experimental results. Buckling results presented indicate that the buckling load of the fuselage panel is significantly influenced by internal pressure loading. The experimental results suggest that the stress distribution is uniform in the panel prior to buckling. Nonlinear finite element analysis results correlates well with experimental results up to buckling. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | AIAA Paper 2003-1423 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/88806 |
