The design of aircraft composite stiffened structures subjected to dynamic and impact loadings requires several experimental testing scenarios on the full-size structure. The present paper deals with investigating the feasibility of the use of sub-size test specimens under vertical and lateral impacts on the stiffener free flange based on finite element (FE) models. Simulations were performed on sub-size specimens carefully extracted from the full-size (26.4 × 48.4 × 2.4 in3) impact test panels. The main required specifications of an in-house falling weight impact tester were also determined, discussing the required fixture/jig configuration.


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    Title :

    Damage tolerance coupon sizing of composite stiffened panels under impact


    Contributors:


    Publication date :

    2016-07-01


    Size :

    852779 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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