The fuselage panel test facility at NLR offers the possibility to subject fuselage skin sections to residual strength and fatigue tests. The fatigue test loads simulate cabin pressurization in radial and axial direction and axial loads representative of fuselage bending. To verify the test methodology and the specifications of the test set-up, the performance of the test set-up is evaluated using a GLARE panel designed by Fokker Aircraft. The test results indicate the suitability of the biaxial load introduction systems to load a panel comparable to a panel in a pressurized fuselage subjected to bending. In addition, the tests show that compared to conventional fuselages, the designed GLARE Panel combines a substantial weight reduction with an excellent fatigue behavior and sufficient static strength. Test on fuselage panels designed by Shorts, DASA and Alenia are used to demonstrate the technological feasibility of GLARE fuselages also with window cut-outs, to study the growth of multiple site damage in stiffended lap-joints of aluminum curved panels and to determine the effect of multiple site damage on the residual strength of such panels.
Full-Scale Fuselage Panel Tests
1998
18 pages
Report
Keine Angabe
Englisch
Aircraft , Test Facilities & Equipment , Fuselages , Curved panels , Full scale tests , Structural design , Aerodynamic loads , Axial loads , Bending , Cyclic loads , Fatigue life , Residual strength , Fiber reinforced composites , Laminates , Damage assessment , Weight reduction , Test facilities , Foreign technology
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