| タイトル | Structural Efficiency of Stitched Rod-Stiffened Composite Panels with Stiffener Crippling |
| 本文（外部サイト） | http://hdl.handle.net/2060/20080015741 |
| 著者（英） | Velicki, Alexander; Hansen, Daniel A.; Jegley, Dawn C. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2008-04-07 |
| 言語 | eng |
| 内容記述 | The structural efficiency of rod-stiffened stitched specimens is evaluated to determine their weight saving potential if the stiffeners were allowed to buckle at less than or equal to design ultimate load. Analytical and experimental results from rod-stiffened and blade-stiffened single-stiffener specimens are presented. In both cases, skin and flanges were stitched together through-the-thickness prior to curing. No mechanical fasteners were used for the assembly. Specimens were loaded to failure in axial compression. Failure modes are discussed. Finite element and experimental results agree for the response of the structures. For some specimen configurations, improved structural efficiency can be obtained by allowing stiffeners to buckle at design limit load rather than requiring that buckling not occur prior to design ultimate load. In addition, through-the-thickness stitching can change the failure mechanism by suppressing delamination between skin and flange. A parametric study is presented herein which describes the possible weight savings with this approach. |
| NASA分類 | Structural Mechanics |
| レポートNO | AIAA Paper 2008-2170 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
