The present invention refers to a technique for coupling the run-out section of stringers (5) with ribs, frames or other structural elements (1). A structural element (1) of an aircraft composite structure comprises at least one pair of cleats (13a,13a') integrally formed with the structural element (1), wherein the cleats (13a,13a') are configured and relatively arranged with respect to each other, to copy the cross-sectional shape of the stringer (5) run-out section, so that the run-out section of the stringer can be placed within a space defined between the cleats (13a,13a'), and the stringer (5) foot, at its run-out section, is sandwiched between a part of the cleats (13a,13a') and the skin cover (12). The load transfer at the interface between stringer (5) run-outs and the structural element (1) is enhanced, and de-bonding or peeling problems at the stringer (5) run-out section are minimized. The invention applies preferably to a horizontal tail plane having upper and lower skin covers (12,12') obtained as unitary bodies.


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    Title :

    Stringer stiffened aircraft composite structures


    Additional title:

    Trägerversteifte Flugzeugverbundstrukturen
    Structures composites d'aéronef renforcées par des radisseurs



    Publication date :

    2016-07-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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