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    Contouring Retractable Landing Gear Systems
    1.
    发明申请
    Contouring Retractable Landing Gear Systems 有权

    公开(公告)号：US20210039774A1

    公开(公告)日：2021-02-11

    申请号：US16532347

    申请日：2019-08-05

    Applicant: Bell Textron Inc.

    Inventor： Mark Loring Isaac ,  James Everett Kooiman ,  Charles David Hogue

    IPC: B64C25/12 ,  B64C25/20 ,  B64C25/34

    Abstract: A retractable landing gear system configured to contour an aircraft fuselage includes a landing wheel having an axle, a wheel rotation strut assembly coupling the landing wheel to the aircraft fuselage and an actuation strut assembly configured to move the wheel rotation strut assembly between various positions including a deployed position and a stowed position. The axle of the landing wheel is pivotably coupled to a distal end of the wheel rotation strut assembly and configured to pivot relative to the wheel rotation strut assembly as the actuation strut assembly moves the wheel rotation strut assembly between the deployed and stowed positions such that the landing wheel generally contours the aircraft fuselage when the wheel rotation strut assembly is in the stowed position.

    Landing gear with caster and variable shimmy damping
    2.
    发明授权
    Landing gear with caster and variable shimmy damping 有权

    公开(公告)号：US12221206B2

    公开(公告)日：2025-02-11

    申请号：US18342123

    申请日：2023-06-27

    Applicant: Bell Textron Inc.

    Inventor： Mark Loring Isaac

    IPC: B64C25/34 ,  B64C25/50

    Abstract: An aircraft landing gear shimmy damping device for aircraft landing gear with castering may include a centering cam engaged in a curvic slot in an internal diameter of an aircraft landing gear wheel spindle when the landing gear wheel is aligned with forward ground travel of the aircraft, engaging a landing gear wheel shimmy dampener. The centering cam may be pushed out of the curvic slot when the aircraft begins to turn, disengaging the landing gear wheel shimmy dampener, and may slide back into the curvic slot and (re)engage the shimmy dampener, when the landing gear wheel is realigned with forward ground travel of the aircraft.

    LANDING GEAR WITH CASTER AND VARIABLE SHIMMY DAMPING
    4.
    发明申请
    LANDING GEAR WITH CASTER AND VARIABLE SHIMMY DAMPING 有权

    公开(公告)号：US20250002142A1

    公开(公告)日：2025-01-02

    申请号：US18342123

    申请日：2023-06-27

    Applicant: Bell Textron Inc.

    Inventor： Mark Loring Isaac

    IPC: B64C25/50 ,  B64C25/34

    Abstract: An aircraft landing gear shimmy damping device for aircraft landing gear with castering may include a centering cam engaged in a curvic slot in an internal diameter of an aircraft landing gear wheel spindle when the landing gear wheel is aligned with forward ground travel of the aircraft, engaging a landing gear wheel shimmy dampener. The centering cam may be pushed out of the curvic slot when the aircraft begins to turn, disengaging the landing gear wheel shimmy dampener, and may slide back into the curvic slot and (re)engage the shimmy dampener, when the landing gear wheel is realigned with forward ground travel of the aircraft.

    ADJUSTABLE LANDING GEAR ASSEMBLY FOR USE IN AIRCRAFT
    6.
    发明申请
    ADJUSTABLE LANDING GEAR ASSEMBLY FOR USE IN AIRCRAFT 有权

    公开(公告)号：US20210094675A1

    公开(公告)日：2021-04-01

    申请号：US16589201

    申请日：2019-10-01

    Applicant: Bell Textron Inc.

    Inventor： Mark Loring Isaac ,  Kent Edwards Donaldson

    IPC: B64C25/14 ,  B64C25/00

    Abstract: A landing gear assembly for an aircraft includes a landing member and an actuation mechanism coupled to the landing member. The actuation mechanism is configured to selectively actuate the landing member into a first landing position and a second landing position. The landing member is configured to support the aircraft in either the first landing position or the second landing position.

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