# US 2014/0197275 A1 · Aircraft landing gear and method of operating the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0197275 A1 - Document ID: US20140197275A1 - Status: Published application - Kind: A1 - Application number: 14/154,353 - Filed: 2014-01-14 - Published: 2014-07-17 - Earliest claimed: 2013-01-16 - Assignees: Otto Aviation Group - Inventors: William M. OTTO - Web page: https://patentgrep.com/patent/US20140197275A1 ## CPC - B64C 25/20: mechanical - B64C 1/00: Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like - B64C 1/065: {Spars} - B64C 1/069: {Joining arrangements therefor} - B64C 1/10: Bulkheads - B64C 3/185: {Spars} - B64C 3/26: Construction, shape, or attachment of separate skins, e.g. panels - B64C 3/58: provided with fences or spoilers (adjustable for control purposes B64C9/00) - B64C 5/02: Tailplanes - B64C 5/16: about spanwise axes - B64C 9/02: Mounting or supporting thereof - B64C 9/16: at the rear of the wing - B64C 9/20: by multiple flaps - B64C 25/02: Undercarriages - B64C 25/10: retractable, foldable, or the like - B64C 25/12: sideways - B64C 25/14: fore-and-aft - B64C 25/18: Operating mechanisms - B64D 33/10: Radiator arrangement - B64D 37/04: Arrangement thereof in or on aircraft - B64C 2025/125: {into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage} - F02B 37/001: {using exhaust drives arranged in parallel} - Y02E 30/30: Nuclear fission reactors - Y02T 50/30: Wing lift efficiency - Y02T 50/40: Weight reduction - Y02T 50/80: Energy efficient operational measures, e.g. ground operations or mission management - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F02B: INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL (gas-turbine plants F02C; hot-gas or combustion-product positive-displacement engine plants F02G) - Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A main landing gear system for an aircraft including a truss element including a front portion joined to a rear portion, a first support unit and second support unit affixed to the truss at the junction of the first portion and the second portion on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel, a first extension plate and second extension plate each rotatively coupled to the respective first trailing link and second trailing link and to a side of the truss, a first plate locking unit and second plate locking unit rotatively affixed to an end of the respective first extension plate or second extension plate and to a side of the truss, where actuation of the actuator causes the extension plates to move up or down with respect to the truss raising and lowering the wheels. ## Claims ### Claim 1 A main landing gear system for an aircraft including: a truss element including a front portion joined to a rear portion; a first support unit and second support unit affixed to the truss at the junction of the first portion and the second portion on opposing sides of the truss; a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel; a first trailing link and second trailing link each coupled to the respective first wheel and second wheel; a first extension plate and second extension plate each rotatively coupled to the respective first trailing link and second trailing link and to a side of the truss; a first plate locking unit and second plate locking unit rotatively affixed to an end of the respective first extension plate or second extension plate and to a side of the truss, wherein actuation of the actuator causes the extension plates to move up or down with respect to the truss raising and lowering the wheels. ### Claim 2 (depends on 1) The landing gear of claim 1, wherein the first locking unit and second locking units each include a first locking plate coupled to the end of the extension arm and a second locking plate rotatively coupled to the first locking plate and the truss. ### Claim 3 (depends on 1) The landing gear of claim 1, wherein the first and second trailing links are rotatively affixed to the respective first support plate and second support plate by a universal joint. ### Claim 4 (depends on 2) The landing gear of claim 2, wherein the first locking plates are tapered towards the end of the extension plate connected to the tailing link. ### Claim 5 (depends on 2) The landing gear of claim 2, wherein the linear actuator includes a base portion coupled to the support unit and an extension portion coupled to the wheel. ### Claim 6 (depends on 2) The landing gear of claim 2, wherein the actuator is a hydraulic actuator. ### Claim 7 (depends on 2) The landing gear of claim 2, wherein the actuation device is a linear actuator. ### Claim 8 A method of retracting a rear landing gear for an aircraft including: rotating a wheel towards a support arm by an oleopneumatic cylinder rotatively coupled to the support arm and the wheel; rotating an extension plate rotatively affixed to a truss affixed to the support arm and a trailing link rotatively affixed to the wheel; rotating a first locking plate coupled to the extension arm and a second locking plate coupled to the first locking plate and the truss upward; rotating the trailing link relative to the wheel as the extension plate is rotated towards the truss. ### Claim 9 (depends on 8) The method of claim 8, wherein the first locking plate and second locking plate are rotatively coupled by a pin. ### Claim 10 (depends on 8) The method of claim 8, wherein the trailing link is rotatively affixed to the extension plate by a universal joint. ### Claim 11 (depends on 8) The method of claim 8, wherein the first locking plates are tapered towards the end of the extension plate connected to the tailing link. ### Claim 12 (depends on 8) The method of claim 8, wherein the oleopneumatic cylinder includes a base portion coupled to the support unit and an extension portion coupled to the wheel. ### Claim 13 (depends on 8) The method of claim 8, wherein the oleopneumatic cylinder is a hydraulic actuator. ### Claim 14 (depends on 8) The method of claim 8, wherein the oleopneumatic cylinder is a linear actuator.