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- W2373313184 abstract "A method for design optimization considering damage tolerance requirements in the aircraft structure preliminary design process is introduced.Firstly,damage tolerance design requirements are defined by fatigue stress allowables and applied in the preliminary design optimization as new design constraints.Then,the global/local finite element approach is used to consider the local fatigue requirements in the global design optimization.A new strength criterion for design life requirements is provided through fatigue crack growth analysis(by AFGROW).Finally,the COMPASS optimization program is simultaneously used to treat these damage tolerance constraints and von Mises stress constraints to optimize cracked skin panels on the lower wing panels of an aircraft.The research shows that for some parts such as the lower wing panels of aircraft,the optimization is driven by the damage tolerance constraint and,therefore,damage tolerance requirements could be dominative for some parts in preliminary aircraft design." @default.
- W2373313184 created "2016-06-24" @default.
- W2373313184 creator A5083168237 @default.
- W2373313184 date "2011-01-01" @default.
- W2373313184 modified "2023-09-25" @default.
- W2373313184 title "Research on Damage Tolerance Design Optimization in Aircraft Structure Preliminary Design Optimization" @default.
- W2373313184 hasPublicationYear "2011" @default.
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