Design of an integral wing box fuel tank to withstand penetration and detonation of an exploding round is a challenging endeavor. Questions arise concerning the build-up of motion and loads due to the propagation of shock waves emanating from the explosive source. One of the critical objectives is to understand the loading history acting on the skin-spar interface leading to 'pull-off' of the skin. The philosophy was to build a section of representative structure with suitable instrumentation to investigate shock wave loading and to record strain in the spars and skin that could provide dynamic data for design purposes. To provide a kinematic constraint to the skin-spar reaction, a dual beam laser interferometer in the VISAR mode was used to measure the out-of-plane motion of the skin at the spar attachment location. The outboard spar was designed as a dynamic load cell and was robustly fastened to the skin such that the skin would fail before the joint itself. In practice this limited the damage, but did provide a complete strain history for the outboard spar including the velocity of skin attachment point. These measurements provided an ideal opportunity for comparison with calculations using the DYNA-3D finite element code.


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    Title :

    Explosive loading of lightweight aircraft structures


    Additional title:

    Explosionslast von Leichtflugzeugkonstruktionen


    Contributors:
    Schmidt, R.M. (author) / Voss, M.E. (author) / Karl, S.E. (author) / Shrader, J.E. (author)


    Publication date :

    1995


    Size :

    10 Seiten, 23 Bilder, 1 Tabelle, 6 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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