公开(公告)号：US20240253809A1

公开(公告)日：2024-08-01

申请号：US18629575

申请日：2024-04-08

Applicant: GOODRICH CORPORATION

Inventor： Jason Bradley Allen

IPC: B64D41/00 ,  B64C25/50 ,  F03B5/00 ,  F03B11/00 ,  F03B15/02

CPC classification number: B64D41/00 ,  B64C25/50 ,  F03B5/00 ,  F03B11/004 ,  F03B15/02

Abstract: A system for extracting energy for landing gear retraction may comprise a wheel pump rotationally coupled to a wheel via a pinion gear. A landing gear control valve assembly may be fluidly coupled to an output of the wheel pump. A secondary pump may be fluidly coupled to the landing gear control valve assembly, and an electric motor may be operationally coupled to the secondary pump.

公开(公告)号：US20240025536A1

公开(公告)日：2024-01-25

申请号：US17870365

申请日：2022-07-21

Applicant: Blended Wing Aircraft, Inc.

Inventor： Mark Allan Page

IPC: B64C25/50 ,  B64C25/06

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.

公开(公告)号：US11834157B2

公开(公告)日：2023-12-05

申请号：US16720870

申请日：2019-12-19

Applicant: SAFRAN LANDING SYSTEMS

Inventor： Julien Fraim ,  Laurent Boissard ,  Denis Telhadas

IPC: B64C25/40 ,  B64C25/32 ,  B64C19/02 ,  B64C25/50 ,  F16H61/28 ,  F16H61/32

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.

公开(公告)号：US20230264810A1

公开(公告)日：2023-08-24

申请号：US17679598

申请日：2022-02-24

Applicant: GOODRICH CORPORATION

Inventor： Korey Michael Reber

IPC: B64C25/50

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.

公开(公告)号：US10053210B2

公开(公告)日：2018-08-21

申请号：US15045328

申请日：2016-02-17

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Carlo Necci

IPC: B64C25/14 ,  B64C25/34 ,  B64C25/50 ,  B64C25/62 ,  B64C25/58 ,  F16F6/00

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.

公开(公告)号：US10000280B2

公开(公告)日：2018-06-19

申请号：US14904931

申请日：2014-07-17

Applicant: Beringer Aero

Inventor： Rémi Beringer

IPC: B64C25/00 ,  B64C25/50 ,  B60B33/00 ,  B60B33/02

CPC classification number: B64C25/50 ,  B60B33/0055 ,  B60B33/0057 ,  B60B33/0065 ,  B60B33/0068 ,  B60B33/0073 ,  B60B33/025 ,  B60B33/026 ,  B60B2900/351

Abstract: A device for mounting an aircraft tail wheel includes a support plate having, on the one hand, an articulation shaft with an arm and, on the other hand, an articulation shaft with a fork receiving the freely rotating tail wheel, while the articulation shaft of the plate is positioned near a rotation shaft of the tail wheel.

公开(公告)号：US09802696B2

公开(公告)日：2017-10-31

申请号：US15016677

申请日：2016-02-05

Applicant: Airbus Operations Limited ,  Airbus Operations SAS

Inventor： Cecile Garaygay ,  Louis-Emmanuel Romana ,  Matthieu Mayolle

IPC: B64C25/50 ,  G05D1/02 ,  B64C19/00

CPC classification number: B64C25/50 ,  B64C19/00 ,  G05D1/0202

Abstract: A slip-reduction control unit for an aircraft having a steerable landing gear. The control unit receives steering input signals from which a target steering command output may be ascertained and additional input signals (a) the motion of the aircraft, (b) a steering angle, or (c) a parameter relating to the slip sustained by the steerable landing gear. The slip-reduction control unit determines, based on the additional input signals, reduces the rate of change of steering angle that would otherwise be commanded. The reduction in the rate of change may reduce vibration on the aircraft that might be caused by a greater rate of change in the steering angle.

公开(公告)号：US20170297683A1

公开(公告)日：2017-10-19

申请号：US15374232

申请日：2016-12-09

Applicant: SIKORSKY AIRCRAFT CORPORATION

Inventor： William E. Hovan ,  Andrew Varga ,  Christopher A. Bresh ,  Jeffrey E. Hunt ,  John Boath ,  Peter Kummer ,  David Klusek ,  David A. Houser ,  Ramon Estevez ,  Jay Hurley ,  Todd Haeg

IPC: B64C25/50 ,  B64C27/04

CPC classification number: B64C25/50 ,  B64C27/04 ,  B64F1/221 ,  B64F1/222

Abstract: A steering assembly includes a movable anchor. Movement of the anchor in a first direction is restricted. A first linkage is coupled to the anchor and a second linkage it rotatably coupled to the first linkage. The second linkage is configured to couple to a contactor. A drive mechanism moves the second linkage relative to the first linkage. At least one of moving the second linkage and moving the anchor maneuvers the contactor to a desired position.

公开(公告)号：US09696148B2

公开(公告)日：2017-07-04

申请号：US14701151

申请日：2015-04-30

Applicant: THE BOEING COMPANY

Inventor： John Wesley Crow, Jr.

IPC: G01B11/275 ,  B64F5/00 ,  B64C25/50 ,  B64F5/60

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.

公开(公告)号：US20170043865A1

公开(公告)日：2017-02-16

申请号：US15231921

申请日：2016-08-09

Applicant: SAFRAN LANDING SYSTEMS

Inventor： Marc QUENERCH'DU ,  Bertrand EUZET

IPC: B64C25/50 ,  B64C25/34

CPC classification number: B64C25/50 ,  B64C25/34 ,  F16H19/04 ,  F16H25/2204 ,  F16H55/285 ,  F16H2025/2075

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。