Abstract In the mid-1980s Fokker Aircraft began a full-scale fatigue test of the fuselage and wings of the F100 aircraft [140]. During the test, which ran to 126,250 simulated flights, fatigue cracking occurred along one of the pressure cabin longitudinal lap splices, see Fig. 9.1. The lap slice had been assembled by adhesive bonding and riveting, and cracking extended over several frame bays that had poor adhesive bonds.
Fokker 100 Fuselage Test: Lap Joints Exponential FCG Analysis
Fatigue Crack Growth Failure and Lifing Analyses for Metallic Aircraft Structures and Components ; 71-76
2019-01-01
6 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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