Mechanics of Widespread Fatigue Damage & Life Enhancement Methodologies for Aging Aerospace Structures.
Final technical rept. 15 Apr 93-14 Dec 96,
GEORGIA INST OF TECH ATLANTA COMPUTATIONAL MECHANICS CENTER
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The major aircraft structural situation considered in this research is that of a thin skin stiffened by orthogonal frames and stringers, with the possibility of a lap joint. Effects on this situation considered in this research are 1 impact by foreign objects, 2 fatigue damage due to repetitive loading, and 3 corrosion damage. Various theoretical models, pertaining to the response of the subject aircraft structure to these effects, have been considered 1 the Finite Element Alternating Method FEAM applied to a single crack, 2 FEAM applied to Multiple Site Damage MSD, and others. An analysis is also presented which pertains to the repair of cracks by application of a composite patch using adhesive.
- Civilian Aircraft