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.
Full scale GLARE fuselage panel tests
FAA-NASA Symposium on Continued Airworthiness of Aircraft Structures ; 1996
1996-08-27
Miscellaneous
No indication
English
Full Scale GLARE Fuselage Panel Tests
NTIS | 1996
|Full-scale glare fuselage panel tests
TIBKAT | 1997
|Full Scale GLARE Fuselage Panel Tests
British Library Conference Proceedings | 1997
|Full-Scale Glare Fuselage Panel Tests
NTIS | 1997
|Full-scale fuselage panel tests
TIBKAT | 1998
|