| タイトル | Full scale GLARE fuselage panel tests |
| 著者（英） | Vercammen, Roland W. A.; Ottens, Harold H. |
| 著者所属（英） | National Aerospace Lab. |
| 発行日 | 1996-08-27 |
| 言語 | eng |
| 内容記述 | A GLARE fuselage panel, representative of the crown section of the Fokker 100 fuselage in front of the wing, was tested. The panels were loaded by air pressure resulting in tangential stress in the panel by axial loading, representative of both the cabin pressure and the fuselage bending due to taxiing and gust loading. A fatigue test, simulating 180000 flights, followed by static tests were performed. The panel was loaded to failure at 1.32 ultimate load. The test set-up, the uniform strain distribution of the panel, and the fatigue loads applied at high test frequency are described. The use of GLARE leads to a substantial weight reduction without affecting the fatigue static strength. |
| NASA分類 | Aircraft Design, Testing and Performance |
| レポートNO | NLR-TP-96530-U |
| 権利 | No Copyright, Distribution within the U.S. granted by agreement |
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