# US 9,868,518 B2 · Landing gear assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,868,518 B2 - Document ID: US9868518B2 - Status: Granted - Kind: B2 - Application number: 14/830,909 - Filed: 2015-08-20 - Published: 2016-02-25 - Granted: 2018-01-16 - Earliest claimed: 2014-08-22 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations Limited - Inventors: Nicholas Elliott - Web page: https://patentgrep.com/patent/US9868518B2 ## CPC - B64C 25/18: Operating mechanisms - B64C 25/14: fore-and-aft - B64C 25/22: fluid - B64C 25/34: wheeled type, e.g. multi-wheeled bogies - B64C 25/50: Steerable undercarriages; Shimmy-damping - B64C: AEROPLANES; HELICOPTERS ## Abstract The present invention provides a landing gear assembly for an aircraft landing gear, the assembly comprising a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, and an actuator arranged to actuate both the steering mechanism and the deployment mechanism. The invention also provides an aircraft landing gear, an aircraft and methods of operating an aircraft landing gear. ## Claims ### Claim 1 A landing gear assembly for an aircraft landing gear, the assembly comprising: a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, an actuator arranged to actuate both the steering mechanism and the deployment mechanism, and wherein the actuator is the only actuator used for actuating both the steering mechanism and the deployment mechanism. ### Claim 2 (depends on 1) The landing gear assembly as claimed in claim 1, wherein the landing gear assembly further comprises a coupling mechanism for coupling the actuator to the steering mechanism and the deployment mechanism, wherein the coupling mechanism is arranged to couple the actuator to only one of the steering mechanism and the deployment mechanism at any one time. ### Claim 3 A landing gear assembly for an aircraft landing gear, the assembly comprising: a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, an actuator arranged to actuate both the steering mechanism and the deployment mechanism, wherein the actuator is the only actuator used for actuating both the steering mechanism and the deployment mechanism, wherein the landing gear assembly further comprises a coupling mechanism for coupling the actuator to the steering mechanism and the deployment mechanism, wherein the coupling mechanism is arranged to couple the actuator to only one of the steering mechanism and the deployment mechanism at any one time, and wherein the coupling mechanism is arranged to automatically couple the actuator to only one of the steering mechanism and the deployment mechanism at any one time. ### Claim 4 (depends on 2) The landing gear assembly as claimed in claim 2, wherein the coupling mechanism is arranged to couple the actuator to the steering mechanism when the wheel is in a “weight on wheel” situation and to couple the actuator to the deployment mechanism when the wheel is in a “weight off wheel” situation. ### Claim 5 (depends on 4) The landing gear assembly as claimed in claim 4, wherein the coupling mechanism comprises a locking mechanism, comprising a locking element moveable between a steering locked position, in which the steering mechanism is prevented from steering the wheel, and a steering unlocked position, in which the steering mechanism is able to steer the wheel, wherein when the wheel is in a “weight on wheel” situation the locking element is moved to the steering unlocked position and when the wheel is in a “weight off wheel” situation, the locking element is moved to the steering locked position. ### Claim 6 (depends on 5) The landing gear assembly as claimed in claim 5, wherein the locking element moves from the steering locked position to the steering unlocked position under the action of the wheel being moved from a dropped position to a raised position relative to the locking element when the wheel changes from a “weight off wheel” to a “weight on wheel” situation and moves from the steering unlocked position to the steering locked position under the action of the wheel being moved from the raised position to the dropped position relative to the locking element when the wheel changes from a “weight on wheel” to a “weight off wheel” situation. ### Claim 7 (depends on 6) The landing gear assembly as claimed in claim 6, wherein the coupling mechanism comprises a crank arm rotatable between first and second rotation positions by the actuator when the locking element is in the steering unlocked position, and prevented from rotating when the locking element is in the steering locked position. ### Claim 8 (depends on 7) The landing gear assembly as claimed in claim 7, wherein the crank arm is connected to the steering mechanism such that when the crank arm is in the first rotation position, the steering mechanism steers the wheel in a first direction and when the crank arm is in the second rotation position, the steering mechanism steers the wheel in a second different direction. ### Claim 9 (depends on 8) The landing gear assembly as claimed in claim 8, wherein the crank arm is connected to the steering mechanism by a bevel gear arrangement such that rotational movement of the crank arm is converted to rotational movement of the steering mechanism. ### Claim 10 A landing gear assembly for an aircraft landing gear, the assembly comprising: a steering mechanism for steering at least one wheel of the landing gear, a deployment mechanism for moving a leg of the landing gear between a stowed position and a deployed position, an actuator arranged to actuate both the steering mechanism and the deployment mechanism, wherein the actuator is the only actuator used for actuating both the steering mechanism and the deployment mechanism, wherein the landing gear assembly further comprises a coupling mechanism for coupling the actuator to the steering mechanism and the deployment mechanism, wherein the coupling mechanism is arranged to couple the actuator to only one of the steering mechanism and the deployment mechanism at any one time, wherein the coupling mechanism is arranged to couple the actuator to the steering mechanism when the wheel is in a “weight on wheel” situation and to couple the actuator to the deployment mechanism when the wheel is in a “weight off wheel” situation, wherein the coupling mechanism comprises a locking mechanism, comprising a locking element moveable between a steering locked position, in which the steering mechanism is prevented from steering the wheel, and a steering unlocked position, in which the steering mechanism is able to steer the wheel, wherein when the wheel is in a “weight on wheel” situation the locking element is moved to the steering unlocked position and when the wheel is in a “weight off wheel” situation, the locking element is moved to the steering locked position, wherein the locking element moves from the steering locked position to the steering unlocked position under the action of the wheel being moved from a dropped position to a raised position relative to the locking element when the wheel changes from a “weight off wheel” to a “weight on wheel” situation and moves from the steering unlocked position to the steering locked position under the action of the wheel being moved from the raised position to the dropped position relative to the locking element when the wheel changes from a “weight on wheel” to a “weight off wheel” situation, wherein the coupling mechanism comprises a crank arm rotatable between first and second rotation positions by the actuator when the locking element is in the steering unlocked position, and prevented from rotating when the locking element is in the steering locked position, wherein the crank arm is connected to the steering mechanism such that when the crank arm is in the first rotation position, the steering mechanism steers the wheel in a first direction and when the crank arm is in the second rotation position, the steering mechanism steers the wheel in a second different direction, wherein the crank arm is connected to the steering mechanism by a bevel gear arrangement such that rotational movement of the crank arm is converted to rotational movement of the steering mechanism, and wherein, when in the steering locked position, the locking element acts on the bevel gear arrangement to prevent its rotation. ### Claim 11 (depends on 7) The landing gear assembly as claimed in claim 7, wherein, when in the steering locked position, the locking element acts on the steering mechanism to prevent its rotation. ### Claim 12 (depends on 11) The landing gear assembly as claimed in claim 11, wherein the locking element is part of a centring arrangement for centring the steering mechanism, such that the wheel is steered in a central direction when the wheel is in a “weight off wheel” situation. ### Claim 13 (depends on 7) The landing gear assembly as claimed in claim 7, wherein the coupling mechanism comprises a lever arm connected at a first end of the lever arm to the actuator and moveable by the actuator between extended and retracted positions. ### Claim 14 (depends on 13) The landing gear assembly as claimed in claim 13, wherein the lever arm is rotatably connected at a second end of the lever arm to the crank arm such that when the lever arm is caused to extend and retract by the actuator, the crank arm is caused to rotate by the lever arm. ### Claim 15 (depends on 14) The landing gear assembly as claimed in claim 14, wherein, when the crank arm is prevented from rotating by the locking element in the steering locked position, movement by the actuator of the lever arm between extended and retracted positions instead causes the landing gear leg to move between the deployed and stowed positions. ### Claim 16 (depends on 1) The landing gear assembly as claimed in claim 1, wherein the steering mechanism comprises a steering collar connected to the actuator and one or more torque links connected to the wheel. ### Claim 17 (depends on 1) The landing gear assembly as claimed in claim 1, wherein the deployment mechanism comprises a number of moveable links, including an over-center uplock, connected between the actuator and the landing gear leg. ### Claim 18 (depends on 17) The landing gear assembly as claimed in claim 17, wherein the deployment mechanism further comprises a second actuator for moving the over-center uplock. ### Claim 19 (depends on 1) The aircraft landing gear comprising the landing gear arrangement of claim 1. ### Claim 20 (depends on 1) The aircraft comprising the aircraft landing gear or the landing gear arrangement of claim 1. ### Claim 21 (depends on 1) The method of operating an aircraft landing gear comprising the step of providing a landing gear arrangement, aircraft landing gear or aircraft of claim 1.