SHAFT DRIVEN SELF-POWERED LANDING GEAR WITH HUBCAP MOUNTED GEAR REDUCTION

    公开(公告)号:US20220219813A1

    公开(公告)日:2022-07-14

    申请号:US17147337

    申请日:2021-01-12

    IPC分类号: B64C25/40 F16H1/28 F16D11/14

    摘要: A landing gear system includes wheel rotatably coupled to an axle. A driveshaft extends through a cavity formed in the axle and is rotatable about an axis. A planetary gear includes a sun gear operably coupled to the drive shaft and a planet gear operably engaging the sun gear. The planetary gear further includes a ring gear that surrounds and is operably coupled to the planet gear so that rotation of the drive shaft rotates the ring gear. A clutch assembly is selectively moveable between an engaged state and a disengaged state. The clutch assembly transfers rotation of the ring gear to the wheel when the clutch assembly is in the engaged state, and the clutch assembly does not transfer rotation of the wheel to the ring gear when the clutch assembly is in the disengaged state.

    AIRCRAFT LANDING GEAR ASSEMBLY
    5.
    发明申请

    公开(公告)号:US20230124974A1

    公开(公告)日:2023-04-20

    申请号:US17908747

    申请日:2021-02-26

    摘要: An aircraft landing gear assembly having a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.

    Landing gear door installation
    6.
    发明授权

    公开(公告)号:US11919624B2

    公开(公告)日:2024-03-05

    申请号:US17695214

    申请日:2022-03-15

    摘要: An aircraft has retractable landing gear configured to reciprocate between a deployed position and a stowed position. A landing gear door installation includes a first door rotatably coupled to the aircraft about a first axis for movement between a raided position and lowered position. The door installation further includes a second door located aft of the first door and coupled to the aircraft for movement between a first position when the landing gear is in the stowed position, and a second position when the landing gear is in the deployed position. A portion of the first door overlaps a portion of the second door when the first door is in the raised position and the second door is in the first position so that the first door blocks deployment of the second door to the second position.

    Shaft driven self-powered landing gear with friction drive

    公开(公告)号:US11603189B2

    公开(公告)日:2023-03-14

    申请号:US17147294

    申请日:2021-01-12

    IPC分类号: B64C25/40 B64C25/36

    摘要: A landing gear system includes a drive shaft extending through an axle. A wheel with a drive surface is rotatably coupled to the axle. A drive assembly, which has disengaged and engaged states, includes a drive element and an idler element. The drive element, which has an engagement feature, is coupled to the drive shaft for rotation about an axis. The engagement feature has first and second diameters when the drive assembly is in the disengaged and engaged states, respectively. The idler element is frictionally engaged with the engagement feature of the drive element to transfer rotation of the drive element to the wheel when the drive assembly is in the engaged state. The idler element is disengaged from at least one of the engagement feature of drive element and the wheel when the drive assembly is in the disengaged state.

    PYROTECHNIC WHEEL ACCELERATION SYSTEM

    公开(公告)号:US20220234726A1

    公开(公告)日:2022-07-28

    申请号:US17160202

    申请日:2021-01-27

    IPC分类号: B64C25/40

    摘要: Wheel acceleration systems are disclosed that provide a motive force to at least one wheel of an aircraft, in order to accelerate the aircraft to takeoff speed with the assistance of main engine thrust. The wheel acceleration system includes a pyrotechnic unit configured to generate expanding gases by combusting a propellant, and a rotary propulsion unit pneumatically coupled to the pyrotechnic unit. The rotary propulsion unit includes an impeller configured to be driven by the expanding gases and to deliver torque to the wheel.

    TEMPERATURE COMPENSATED SHOCK ABSORBER

    公开(公告)号:US20220221021A1

    公开(公告)日:2022-07-14

    申请号:US17147254

    申请日:2021-01-12

    IPC分类号: F16F9/52 B64C25/60

    摘要: A shock absorber includes a housing and an end wall slidably disposed within the housing. The end wall and the housing cooperate to define at least a portion of a cavity within the housing. The cavity is filled with a fluid, and a piston is slidably disposed within the cavity. Movement of the piston within the cavity compresses the fluid to provide a spring force. The shock absorber further includes a compensator coupled to the end wall. The compensator positions the end wall within the housing to change a volume of the cavity in response to a change in a temperature of a first element of the compensator.