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.


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    Title :

    Damage tolerance design of composite structures


    Additional title:

    Schadenstoleranzentwurf für Verbundkonstruktionen


    Contributors:


    Publication date :

    1994


    Size :

    11 Seiten, 10 Bilder, 17 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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