A nacelle for an aircraft turbojet engine includes a fixed internal structure intended to receive an aircraft turbojet engine and an external structure. The fixed internal structure and external structure defines a flow channel for a secondary air flow. A set of lower and upper beams are linked together by the fixed internal structure. An external wall of the lower beam is designed to partially define an external aerodynamic surface of the nacelle, intended to come into contact with an outer air flow. The external wall of the lower beam is further designed to tolerate the damage caused by the outer air flow.


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    Title :

    ENSEMBLE PROPULSIF POUR AÉRONEF À TRAÎNÉE AÉRODYNAMIQUE RÉDUITE


    Additional title:

    AIRCRAFT PROPULSION UNIT HAVING REDUCED AERODYNAMIC DRAG
    FLUGZEUGTRIEBWERKSEINHEIT MIT VERRINGERTEM LUFTWIDERSTAND


    Contributors:

    Publication date :

    2019-04-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    French


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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