A damage tolerance design requirement for composite fuselage structures is investigated. The displacement compatibility model, a method used extensively in the design of metallic fuselage structures, is extended for application to a laminated composite structure. Generalized anisotropic elasticity solutions are required, as well as a suitable composite fracture criterion. Two types of damaged structures are investigated, one in which a crack is centered between intact stringers and a second in which a crack is centered over a broken center stringer.
Damage tolerance design of composite structures
Schadenstoleranzentwurf für Verbundkonstruktionen
1994
11 Seiten, 10 Bilder, 17 Quellen
Conference paper
English
Damage tolerance design of composite structures
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