An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).


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    Title :

    AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE



    Publication date :

    2018-06-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    AIRCRAFT STABILIZER LEADING EDGE INTEGRATION WITH TORSION BOX AND FUSELAGE

    ARANA HIDALGO ALBERTO / MARTINO GONZÁLEZ ESTEBAN / VÁZQUEZ CASTRO JESÚS JAVIER et al. | European Patent Office | 2019

    Free access

    Fuselage Torsion of a CT4 Aircraft

    P. M. Cox / A. Goldman | NTIS | 1983