Manufacturing and performance issues associated with the assembly of an advanced composite commercial transport aircraft fuselage were examined as part of the NASA-sponsored Advanced Technology Aircraft Structures (ATCAS) program. Three mechanically fastened splices associated with the assembly of a fuselage crown panel were examined using filled hole tension, pure bearing, and bearing-bypass interaction specimens. Results demonstrated that relationships between failure strain and stress concentration at the hole perimeter for two-placed and braided laminates are consistent with those exhibited by conventional tape and fabric laminates. Tow-placed graphite-glass/epoxy intraply hybrid laminates demonstrated bearing and bypass strengths similar to those of graphite/epoxy except when hybrid tows were strictly aligned through the laminate thickness. Bearing-bypass interaction results demonstrated good correlation with predictions produced using the Boeing-developed BEARBY computer code.


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    Title :

    Mechanical assembly of commercial transport fuselage utilizing tow-placed and textile composites


    Additional title:

    Mechanischer Zusammenbau eines kommerziellen Transportflugzeug-Rumpfes mit Verbundwerkstoffen auf Basis von Textilien und Tauen


    Contributors:
    Sawicki, A.J. (author) / Grant, P. (author) / Mabson, G.E. (author)


    Publication date :

    1994


    Size :

    15 Seiten, 19 Bilder, 7 Tabellen, 11 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





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