# US 2016/0355253 A1 · Apparatus and methods for actuation of flight control surfaces > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2016/0355253 A1 - Document ID: US20160355253A1 - Status: Published application - Kind: A1 - Application number: 15/114,532 - Filed: 2015-01-30 - Published: 2016-12-08 - Earliest claimed: 2014-01-31 - Assignees: Bombardier Inc.; Universite de Sherbrooke - Applicants: Bombardier Inc.; Université De Sherbrooke - Inventors: Gustave NFONGUEM; Patrick CHOUINARD; Jean-Sebastien PLANTE - Web page: https://patentgrep.com/patent/US20160355253A1 ## CPC - B64C 13/36: fluid - B64C 13/341: {having duplication or stand-by provisions} - F16D 37/008: {the particles being carried by a fluid, to vary viscosity when subjected to electric change, i.e. electro-rheological or smart fluids (composition of such fluids C10M171/001)} - F16D 37/02: the particles being magnetisable - F16H 1/222: {with non-parallel axes} - F16D 2023/123: {Clutch actuation by cams, ramps or ball-screw mechanisms} - F16D 2037/004: {characterised by multiple substantially axial gaps in which the fluid or medium consisting of small particles is arranged} - F16D 2037/007: {characterised by multiple substantially radial gaps in which the fluid or medium consisting of small particles is arranged} - B64C: AEROPLANES; HELICOPTERS - F16D: COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES - F16H: GEARING ## Abstract Apparatus and methods for actuating flight control surfaces (16A-C) of fixed-wing aircraft are disclosed herein. An exemplary apparatus disclosed includes a common movable driving member (20) for actuating a plurality of flight control surfaces; a first power transfer device (24A) configured to variably adjust power transfer from the common movable driving member to a first of the plurality of flight control surfaces; and a second power transfer device (24B) configured to variably adjust power transfer from the common movable driving member to a second of the plurality of flight control surfaces. The power transferred to the second flight control surface may be adjusted independently of the power transferred to the first flight control surface. Apparatus and methods for actuating flight control surfaces using magneto-rheological fluid or electro-rheological fluid are also disclosed. ## Claims ### Claim 1 An apparatus for differentially actuating a plurality of flight control surfaces of a fixed-wing aircraft, the apparatus comprising: a common movable driving member for actuating the plurality of flight control surfaces; a first power transfer device configured to variably adjust power transfer from the common movable driving member to a first of the plurality of flight control surfaces; and a second power transfer device configured to, independently of the power transferred to the first flight control surface, variably adjust power transfer from the common movable driving member to a second of the plurality of flight control surfaces. ### Claim 2 (depends on 1) The apparatus as defined in claim 1, wherein at least one of the first power transfer device and the second power transfer device comprises one of magneto-rheological fluid and electro-rheological fluid. ### Claim 3 (depends on 1) The apparatus as defined in claim 1, wherein the first power transfer device is configured to permit deployment and retraction of the first flight control surface based on actuation of the movable driving member in a first direction. ### Claim 4 (depends on 3) The apparatus as defined in claim 3, wherein the second power transfer device is configured to permit deployment and retraction of the second flight control surface based on actuation of the movable driving member in the first direction. ### Claim 5 (depends on 1) The apparatus as defined in claim 1, wherein the first power transfer device comprises a first clutch and a second clutch cooperating to permit deployment and retraction of the first flight control surface. ### Claim 6 (depends on 5) The apparatus as defined in claim 5, wherein at least one of the first clutch and the second clutch comprises one of magneto-rheological fluid and electro-rheological fluid. ### Claim 7 (depends on 1) The apparatus as defined in claim 1, wherein at least one of the first power transfer device and the second power transfer device comprises a clutch configured for controllable slippage. ### Claim 8 (depends on 1) The apparatus as defined in claim 1, wherein the first power transfer device is configured to permit adjustment of an actuation speed of the first flight control surface based on actuation of the movable driving member at a constant speed. ### Claim 9 (depends on 1) The apparatus as defined in claim 1, wherein the second power transfer device is configured to permit adjustment of an actuation speed of the second flight control surface independently of the actuation of the first flight control surface. ### Claim 10 (depends on 1) The apparatus as defined in claim 1, comprising a first brake for holding the first flight control surface at a first desired position and a second brake for holding the second flight control surface at a second desired position. ### Claim 11 An apparatus for actuating a flight control surface of a fixed-wing aircraft, the apparatus comprising: a source of power for actuating the flight control surface; and a power transfer device configured to transfer power from the source of power to the flight control surface, the power transfer device comprising one of magneto-rheological fluid and electro-rheological fluid. ### Claim 12 (depends on 11) The apparatus as defined in claim 11, wherein the source of power comprises a rotatable driving member. ### Claim 13 (depends on 12) The apparatus as defined in claim 12, wherein the power transfer device is configured to permit deployment and retraction of the flight control surface based on rotation of the rotatable driving member in a first direction. ### Claim 14 (depends on 11) The apparatus as defined in claim 11, wherein the power transfer device comprises a first clutch and a second clutch cooperating to permit deployment and retraction of the flight control surface. ### Claim 15 (depends on 14) The apparatus as defined in claim 14, wherein the first clutch and the second clutch comprise one of magneto-rheological fluid and electro-rheological fluid. ### Claim 16 (depends on 12) The apparatus as defined in claim 12, wherein the power transfer device is configured to permit adjustment of an actuation speed of the flight control surface based on rotation of the rotatable driving member at a constant speed. ### Claim 17 (depends on 11) The apparatus as defined in claim 11, comprising a linear actuator configured to transfer power from the power transfer device to the flight control surface. ### Claim 18 (depends on 17) The apparatus as defined in claim 17, wherein the linear actuator comprises a nut engaged with a screw. ### Claim 19 A method for differentially actuating a plurality of flight control surfaces of a fixed-wing aircraft using a common movable driving member, the method comprising: variably adjusting the power transferred from the common movable driving member to a first of the plurality of flight control surfaces; and independently of the power transferred to the first flight control surface, variably adjusting the power transferred from the common movable driving member to a second of the plurality of flight control surfaces. ### Claim 20 An apparatus for differentially actuating a plurality of actuatable members, the apparatus comprising: a common movable driving member for actuating the plurality of actuatable members; a first power transfer device configured to variably adjust power transfer from the common movable driving member to a first of the plurality of actuatable members; and a second power transfer device configured to, independently of the power transferred to the first actuatable member, variably adjust power transfer from the common movable driving member to a second of the plurality of actuatable members. ### Claim 21 (depends on 20) The apparatus as defined in claim 20, wherein at least one of the first power transfer device and the second power transfer device comprises one of magneto-rheological fluid and electro-rheological fluid.