A considerably large four point bending test box was avialable simulating the curved integrally stiffened CFC fuselage skin of a fighter aircraft. This box was used for a skin repair trial with subsequent testing. The repair was performed in the environment of an external test laboratory, i.e. abroad of the original shop or maintenance facilities. On Aircraft conditions have been simulated with all the referring access, tooling and quality assurance difficulties. The repaired test box demonsstrated during static testing, loading the repair in tension, compression and shear, that the applied repair procedure is feasible to be applied on CFC structures. The repair procedure and the subsequent testing will be presented and the results will be discussed.
Airccraft Repair Verification of a Fighter A/C Injtegrally Stiffened Fuselage Skin
1995
14 pages
Report
Keine Angabe
Englisch
Aircraft , Composite Materials , Aircraft maintenance , Bend tests , Fiber composites , Fuselages , Load tests , Skin (Structural member) , Static tests , Tensile tests , Aircraft construction materials , Aircraft structures , Bending , Carbon fibers , Fighter aircraft , Quality control , Foreign technology
"On-Aircraft" Repair Verification of a Fighter A/C Integrally Stiffened Fuselage Skin
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