The considered program has the objective to develop and validate repair procedures for composite structures which are adaptable to commercial airline maintenance operations. Questions concerning the design and the fabrication of repairs are discussed, taking into account a vertical fin cover panel, a wing cover panel, and a vertical fin spar. The test results indicate that the use of graphite patch repairs, either precured bonded or employing cure-in-place, is satisfactory for the repair of lightly loaded and highly loaded parts. The use of bolted repairs is satisfactory for lightly loaded structural components. The repair of composite substructures can be accomplished using comparable approaches to those evaluated for skin cover repairs in many previous programs.


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    Titel :

    Demonstration of repairability and repair quality on graphite/epoxy structural subelements


    Beteiligte:
    Knauss, J. F. (Autor:in) / Stone, R. H. (Autor:in)

    Kongress:

    In: National SAMPE Symposium and Exhibition ; 1982 ; San Diego, CA


    Erscheinungsdatum :

    1982-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    FEM subelements conserve computer resources

    Havas,T. | Kraftfahrwesen | 1984



    Improving the repairability of aircraft composite structures

    Air Transport Association; Commercial Aircraft Composite Repair Committee / International Air Transport Association; Commercial Aircraft Composite Repair Committee / Society of Automotive Engineers; Commercial Aircraft Composite Repair Committee | British Library Conference Proceedings | 1993