An aircraft with a fuselage has landing gear 6 with a main strut 8 coupled to the aircraft, and a sidestay assembly 22,30 connected at a first end joint 24,26 to the main strut, and at a second end to the aircraft by second and third joints 34,36, at least one of which is mounted on the fuselage. The main strut may be coupled to a rear spar of the aircraft wing via a spherical bearing 16, located forward of the main strut, permitting movement in all three rotational degrees of freedom. The sidestay assembly may be inboard, with forward 22a,30a and rear 22b,30b stays; preferably cross-bracing, such as a shear web or panel 28,32 extends between the stays to limit movement between them. The forward strut may be connected the aircraft wing at its root, or to the fuselage. Each stay may have upper 30 and lower 22 portions which fold as the landing gear retracts, with a recess 29 in the lower shear web 28 receiving a portion of the main strut when the landing gear is retracted. The main strut may be rotated about an axis parallel to the longitudinal axis of the aircraft.


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    Titel :

    Landing Gear


    Beteiligte:

    Erscheinungsdatum :

    2019-01-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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