A GLARE fuselage panel, representative of the crown section of the Fokker 100 fuselage just in front of the wing, has been tested in the curved fuselage panel test facility that was recently commissioned at NLR. Panels are loaded by internal air pressure resulting in tangential stresses in the panel and by axial loading representative of both the cabin pressure and the fuselage bending due to taxing and gust loading. A fatigue test was performed in which 180,00 flights (two lifetimes) were simulated. After the fatigue test no damage was observed. The fatigue test was followed by the static test to Limit Load and to Ultimate Load. Finally the panel was laded to failure at 1.32 Ultimate Load. This paper will describe the test set-up in some detail, demonstrate the obtained uniform strain distribution in the panel, show the fatigue loads applied at high test frequency, and present the results of the GLARE fuselage panel tests which proof that the use of GLARE leads to a substantial weight reduction without affecting the fatigue or static strength.
Full Scale GLARE Fuselage Panel Tests
1996
22 pages
Report
No indication
English
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