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PROCEEDINGS OF THE FAA-NASA SYMPOSIUM ON THE CONTINUED AIRWORTHINESS OF AIRCRAFT STRUCTURES: FAA CENTER OF EXCELLENCE IN COMPUTATIONAL MODELING OF AIRCRAFT STRUCTURES, ATLANTA, GEORGIA, AUGUST 28-30, 1996..

This paper presents the analytical fatigue life estimation of the curved full-scale fuselage panel which was tested by Foster-Miller, Inc. In the analysis, a hierarchical finite element based on global-intermediate-local modeling strategy has been used for determining the stress state in the crack area. The relevant crack tip parameters that govern the onset of fracture and crack growth are evaluated using the finite element alternating method (FEAM) in the local analysis. Then the load cycles from the initial cracks to local failure are estimated. This analytical result was verified against the result obtained from the full-scale testing of fuselage panel. It is found that the analytical results were in good agreement with the test results.