The good agreement between detailed FE models of composite foldcore and the metallic lattice cores demonstrated above validates the CELPACT methodology at the micromechanics scale. Here failure modes are complex and highly nonlinear with progressive damage and collapse. These detailed cell models have now been applied to model basic core compression and shear behaviour and used to design improved and optimised core structures which are now being fabricated and tested. For example the weight savings with titanium over stainless steel in the SLM lattice cells have been studied and foldcore geometries optimised to increase specific compression strength, leading to new improved cores. In ongoing work the micromechanics computational methods are being combined with homogenised core models and multiscale modelling techniques to simulate impact damage and failure in sandwich structures, as discussed in more detail in. Impact performance is critical for sandwich aircraft structures and the validated simulation tools may be used to design more efficient impact resistant aircraft structures. Structural integrity of these improved sandwich structures are being assessed in CELPACT by drop tower and gas gun impact tests on sandwich beam and panel structures under high velocity impact conditions relevant to aircraft structures.


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    Title :

    Novel structural core sandwich materials for aircraft applications: CELPACT project overview


    Additional title:

    Neue Sandwich-Werkstoffe mit strukturellem Kern für Luftfahrtanwendungen: Übersicht über das CELPACT-Projrkt


    Contributors:


    Publication date :

    2009


    Size :

    8 Seiten, 8 Bilder, 12 Quellen



    Type of media :

    Conference paper


    Type of material :

    Storage medium


    Language :

    English




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