NON-COUPLED LANDING GEAR APPARATUS AND METHODS OF USE

    公开(公告)号:US20240025536A1

    公开(公告)日:2024-01-25

    申请号:US17870365

    申请日:2022-07-21

    Inventor: Mark Allan Page

    CPC classification number: B64C25/50 B64C25/06

    Abstract: A non-coupled landing gear for an aircraft includes at least a nose gear and at least a main gear. The at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and the at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are uncoupled from each other.

    Landing gear motorizing control device

    公开(公告)号:US11834157B2

    公开(公告)日:2023-12-05

    申请号:US16720870

    申请日:2019-12-19

    CPC classification number: B64C25/405 B64C19/02 B64C25/50 F16H61/2807 F16H61/32

    Abstract: The invention relates to a motorizing device (1) for moving an aircraft (A) provided with a landing device (L) having wheels (W) on the ground, the motorizing device comprising at least one electric motor (2) having an output shaft provided with means for its rotational connection to at least one of the wheels (W) of the landing device for driving said wheel in rotation, and an electronic control unit (3) connected on the one hand to the motor to control it and on the other hand to a control interface (4) from which the aircraft pilot can transmit control signals which the electronic control unit (3) is arranged to transform into motor control signals, characterized in that the control unit is arranged to implement a first control law having determined dynamics to promote an aircraft movement speed and a second control law having dynamics to promote aircraft manoeuvrability.

    INTEGRAL STEERING MOTOR AND COLLAR FOR LANDING GEAR

    公开(公告)号:US20230264810A1

    公开(公告)日:2023-08-24

    申请号:US17679598

    申请日:2022-02-24

    CPC classification number: B64C25/50

    Abstract: A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.

    Aircraft undercarriage including a telescopic linear rod

    公开(公告)号:US10053210B2

    公开(公告)日:2018-08-21

    申请号:US15045328

    申请日:2016-02-17

    Inventor: Carlo Necci

    CPC classification number: B64C25/34 B64C25/50 B64C25/58 B64C25/62 F16F6/00

    Abstract: An aircraft undercarriage comprising a telescopic linear rod (0, 0′, 0″) comprising first and second sliding rod portions. The undercarriage further comprises: a first permanent magnet set (1a, 1a′, 1a″) fastened to the first rod portion (1, 1′, 1″); and a second permanent magnet set (2a, 2a′, 2a″) fastened to the second rod portion (2, 2′, 2″); the first and second permanent magnet sets (1a, 1a′, 1a″, 2a, 2a′, 2a″) generating a magnetic repulsion force between the first rod portion (1, 1′, 1″) and the second rod portion (2, 2′, 2″) and maintaining a first annular space (E1) between the first rod portion and the second rod portion.

    Nose landing gear rigging alignment tool holding fixture

    公开(公告)号:US09696148B2

    公开(公告)日:2017-07-04

    申请号:US14701151

    申请日:2015-04-30

    CPC classification number: G01B11/275 B64C25/50 B64F5/60

    Abstract: Method and apparatus for providing an alignment indication for a nose landing gear of an aircraft. The apparatus includes surfaces that abut certain features of the nose landing gear. When the surfaces of the fixture and the features of the nose landing gear abut, the fixture is aligned with the nose landing gear and oriented such that a coherent light source emits a coherent light beam that impinges on an alignment scale. The coherent light beam can be sufficiently small that a mechanic or other user can discern the alignment of the nose landing gear to within one or two degrees. After the nose landing gear has been moved to a centered position, control rigging that communicates steering inputs from pilots to a hydraulic actuation system can be adjusted so that the steering inputs are also centered.

    DEVICE AIRCRAFT UNDERCARRIAGE LEG INCLUDING RACK-AND -PINION TYPE MEANS FOR CONTROLLING THE ORIENTATION OF THE WHEELS OF THE UNDERCARRIAGE LEG
    10.
    发明申请
    DEVICE AIRCRAFT UNDERCARRIAGE LEG INCLUDING RACK-AND -PINION TYPE MEANS FOR CONTROLLING THE ORIENTATION OF THE WHEELS OF THE UNDERCARRIAGE LEG 审中-公开
    装置飞机底盘装置,包括用于控制底盘标志车轮方向的机架式和类型装置

    公开(公告)号:US20170043865A1

    公开(公告)日:2017-02-16

    申请号:US15231921

    申请日:2016-08-09

    Abstract: An aircraft undercarriage leg having an orientation control for wheels that causes a sliding rod to pivot. The orientation control has a rotating member mounted on the strut assembly having a toothed sector forming a pinion and is rotationally coupled to the sliding rod, and a rack mounted to slide on the strut assembly along a sliding axis perpendicular to the pivot axis to mesh with the pinion, the rack being moved by drive means. The drive include a rotary drive inside the rack adapted to turn about the sliding axis and to cooperate via a helicoidal coupling with the rack,. The rotary drive is immobilized axially by two opposite axial thrust bearings allowing angular tilting of the rotary drive. The thrust bearings are carried by at least one elongate support inside the rack having a proximal end fixed to an end of a cylinder in which the rack slides.

    Abstract translation: 具有使滑动杆枢转的轮的定向控制的飞机起落架腿。 取向控制装置具有安装在支柱组件上的旋转构件,该旋转构件具有形成小齿轮的齿形扇形部分,并且旋转地联接到滑动杆上;以及齿条,其安装成沿垂直于枢转轴线的滑动轴线在支柱组件上滑动以与 小齿轮,齿条由驱动装置移动。 该驱动器包括适于围绕滑动轴线转动的齿条内的旋转驱动器,并通过与机架的螺旋联轴器协作。 旋转驱动器通过两个相反的轴向推力轴承轴向固定,允许旋转驱动器的角度倾斜。 推力轴承由机架内的至少一个细长支承件承载,其具有固定到气缸的端部的近端,其中齿条滑动。

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