# US 8,770,514 B2 · Landing gear > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,770,514 B2 - Document ID: US8770514B2 - Status: Granted - Kind: B2 - Application number: 11/421,726 - Filed: 2006-06-01 - Published: 2011-02-03 - Granted: 2014-07-08 - Earliest claimed: 2005-06-03 - Assignees: Airbus Operations GmbH - Applicants: Trevor Anthony Brighton; Martin John Elms; Maxwell William Jones - Inventors: Trevor Anthony Brighton; Martin John Elms; Maxwell William Jones - Web page: https://patentgrep.com/patent/US8770514B2 ## CPC - B64C 25/26: Control or locking systems therefor - B64C 25/20: mechanical - B64C 25/22: fluid - B64C 25/24: electric - F15B 11/024: by means of differential connection of the servomotor lines, e.g. regenerative circuits - F15B 2211/3133: Regenerative position connecting the working ports or connecting the working ports to the pump, e.g. for high-speed approach stroke - F15B 2211/7128: the chambers being connected in parallel - B64C: AEROPLANES; HELICOPTERS - F15B: SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR ## Abstract In the retracted position, aircraft landing gear of an aircraft is supported by an uplock hook. The deployment of the aircraft landing gear includes the steps of supporting at least part of the weight of the landing gear by a releasable catch in the form of an uplock hook, applying a lifting force to the landing gear to remove at least part of the load sustained by the releasable catch, releasing the catch and effecting the downward movement of the landing gear to the deployed position. ## Claims ### Claim 1 A method of deploying an aircraft landing gear movable between a stowed position and a deployed position, the method comprising the steps of: providing an aircraft including he landing ear assembly including the aircraft landing gear and a deployment mechanism, the deployment mechanism including a releasable catch, supporting at least part of the weight of the aircraft landing gear by way of the releasable catch, applying a lifting force to the aircraft landing gear to relieve at least part of the load sustained by the releasable catch, and then releasing the catch, and effecting downward movement of the aircraft landing gear to the deployed position. ### Claim 2 (depends on 1) A method according to claim 1, wherein, during the step of effecting the downward movement of the landing gear to the deployed position, a lowering force is applied to the landing gear. ### Claim 3 (depends on 1) A method according to claim 1, wherein the lifting force applied to the landing gear is insufficient to move the landing gear upwards during landing gear deployment. ### Claim 4 (depends on 1) A method according to claim 1, wherein the releasable catch is an uplock hook. ### Claim 5 (depends on 1) A method according to claim 1, wherein the steps are performed in the recited order. ### Claim 6 (depends on 1) A method according to claim 1, wherein the step of applying the lifting force to the landing gear is effected by an actuator that is used in the step of effecting downward movement of the landing gear to the deployed position. ### Claim 7 (depends on 6) A method according to claim 6, wherein the force applied to the landing gear by the actuator during the step of applying the lifting force is reduced to facilitate the downward movement of the landing gear to the deployed position. ### Claim 8 (depends on 6) A method according to claim 6, wherein the actuator is arranged to effect movement of the landing gear substantially the entire way from the deployed position to the stowed position. ### Claim 9 (depends on 1) A method according to claim 1, wherein the lifting force applied to the landing gear results from pressure exerted by hydraulic fluid in a hydraulic circuit. ### Claim 10 (depends on 9) A method according to claim 9, wherein the downward movement of the landing gear to the deployed position is effected by movement of the hydraulic fluid in the hydraulic circuit. ### Claim 11 (depends on 9) A method according to claim 9, wherein the step of releasing the catch is effected by movement of the hydraulic fluid in the hydraulic circuit. ### Claim 12 (depends on 11) A method according to claim 11, wherein the step of releasing the catch is effected a period of time after the step of applying the lifting force to the landing gear, the period of time between the steps being determined by a hydraulic delay valve. ### Claim 13 (depends on 1) A method according to claim 1, further comprising controlling movement of the landing gear using an electronic control system. ### Claim 14 (depends on 13) A method according to claim 13, wherein the step of releasing the catch is effected a period of time after the step of applying the lifting force to the landing gear, the period of time between the steps being determined by the electronic control system. ### Claim 15 (depends on 1) A method according to claim 1, further comprising, after the step of effecting downward movement of the landing gear to the deployed position has been completed, a step of securing the landing gear in the deployed position with a further releasable catch. ### Claim 16 (depends on 15) A method according to claim 15, wherein the further releasable catch is a downlock.