The objective of this work was the development a secondary impact protection system, which successfully protect CFRP composite parts (e. g. fuselage, wing) against runway debris during take-off and landing. Therefore a multilayer lightweight sandwich structure was developed; which consists of Kevlar, Dyneema, glass fibers in combination with a lightweight foam core. The attachment on the CFRP parts was realized either by adhesive bonding or by specially designed brackets. Impacts can easily visual inspected by deformation of the impact protection system. The tested 2 mm thick CFRP laminates withstand an impact of 19 Joule under an impact angle of 30 deg, but inside of CFRP sandwiches buckling failure of the honeycomb core are detectable. Better results were verified for comparable CFRP sandwiches with fold core material. For lightning fire attack the impact protection system need an additional covering with a conductive material. Copper mesh and an anti-static paint successfully protects the impact protection as well as the CFRP panels during lightning fire testing. A repair procedure for impacted protection layers was developed. Promising results exhibited a mobile grinding unit. This grinding unit can be attached by vacuum on the fuselage and remove the damaged protection layer down to the CFRP surface.


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    Title :

    Impact protection structures for composite fuselage application


    Contributors:


    Publication date :

    2008


    Size :

    7 Seiten, 7 Bilder, 6 Quellen



    Type of media :

    Conference paper


    Type of material :

    Storage medium


    Language :

    English




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