An aircraft drive shaft including an outer shaft having a first diameter configured to couple a first gearbox and a second gearbox to provide power transfer between the two gearboxes, an inner shaft concentric with the outer shaft and having a second diameter configured to provide structural support to the outer shaft, a gap defined between an outer peripheral surface of the inner shaft and an inner peripheral surface of the outer shaft, wherein the gap is sized according to a ballistic projectile cross-section size that the aircraft is considered to encounter on an upcoming mission, and a sleeve located at least at first end of the outer shaft connecting the outer shaft to the inner shaft.


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    Titel :

    DRIVE SHAFT WITH INCREASED BALLISTIC TOLERANCE


    Beteiligte:
    GURVICH MARK R (Autor:in) / KING MICHAEL (Autor:in) / REED BRAYTON (Autor:in) / SCHAEFER JOYEL M (Autor:in)

    Erscheinungsdatum :

    2023-01-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F16C SHAFTS , Wellen



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