Author(s)

N.K. Salgado & M.H. Aliabadi

Abstract

This paper describes an object oriented interactive system for dam- age tolerance design of Aircraft panels. The use of the Dual Boundary Element Method allows for the solution of single or multi-site dam- age problems under mixed mode conditions. Examples of application featuring multi-site damage problems in stiffened panels and fuselage lap joints are presented. 1 Introduction Aircraft structural components such as stiffened panels must satisfy damage tolerance requirements. A structural component is damage tolerant if it can withstand reasonable loads without catastrophic failure or excessive defor- mation after the occurrence of serious fatigue damage. Fatigue crack growth analysis is central to damage tolerance assessm

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