# US 11,111,006 B2 · Multiple controlloable airflow modification devices > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,111,006 B2 - Document ID: US11111006B2 - Status: Granted - Kind: B2 - Application number: 15/979,331 - Filed: 2018-05-14 - Published: 2019-02-21 - Granted: 2021-09-07 - Earliest claimed: 2009-12-01 - Assignees: Tamarack Aerospace Group, Inc. - Applicants: Tamarack Aerospace Group, Inc. - Inventors: Nicholas R. Guida - Web page: https://patentgrep.com/patent/US11111006B2 ## CPC - B64C 23/069: {using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips} - B64C 13/16: actuated automatically, e.g. responsive to gust detectors - B64C 23/076: {the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps} - Y02T 50/10: Drag reduction - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, and/or increase efficiency. ## Claims ### Claim 1 An aircraft comprising: a fuselage; a baseline wing, the baseline wing coupled to the fuselage at a first end of the baseline wing and having an aileron; and a wing extension comprising: a horizontal portion coupled to a second end of the baseline wing, such that the horizontal portion is outboard of the baseline wing; and a plurality of controllable airflow modification devices (CAMDs) coupled to the horizontal portion of the wing extension, a first CAMD of the plurality of CAMDs being outboard of a second CAMD of the plurality of CAMDs, the plurality of CAMDs being configured to alleviate a load on a wing and to be controllable independently of the aileron. ### Claim 2 (depends on 1) The aircraft of claim 1, wherein a CAMD of the plurality of CAMDs comprises: a control surface disposed at a trailing edge of the wing extension, such that the control surface is substantially parallel to the baseline wing; and a control system for controlling motion of the control surface based at least in part on in-flight load data. ### Claim 3 (depends on 2) The aircraft of claim 2, the control surface being configured for the aircraft based at least in part on historical flight data. ### Claim 4 (depends on 2) The aircraft of claim 2, the control system being communicatively coupled to a sensor located on the aircraft and configured to receive a signal from the sensor located on the aircraft. ### Claim 5 (depends on 2) The aircraft of claim 2, the control system configured to control the control surface of the CAMD of the plurality of CAMDs independent of a control surface of another CAMD of the plurality of CAMDs. ### Claim 6 (depends on 2) The aircraft of claim 2, the control system configured to control the control surface of the CAMD of the plurality of CAMDs in coordination with another CAMD of the plurality of CAMDs. ### Claim 7 A wing extension fixedly attachable to a baseline wing of an aircraft, the wing extension comprising: a horizontal portion that, when attached to the aircraft, is substantially parallel to the baseline wing of the aircraft, the horizontal portion being configured to fixedly attach to an outboard portion of the baseline wing of the aircraft; and a plurality of controllable airflow modification devices (CAMDs) coupled to the horizontal portion of the wing extension, a first CAMD of the plurality of CAMDs disposed outboard of a second CAMD of the plurality of CAMDs, the plurality of CAMDs being configured to alleviate a load on the baseline wing and to be controllable independently of a control surface of the baseline wing. ### Claim 8 (depends on 7) The wing extension of claim 7, a CAMD of the plurality of CAMDs being coupled to a control system for controlling a control surface of the CAMD. ### Claim 9 (depends on 8) The wing extension of claim 8, the control system being configured to control the plurality of CAMDs independently of an auto-pilot and/or a fly-by-wire system of the aircraft. ### Claim 10 (depends on 8) The wing extension of claim 8, the control system comprising a control device with control logic, the control device being configured to communicatively couple to a sensor located on the aircraft. ### Claim 11 (depends on 10) The wing extension of claim 10, the control device being configured, when coupled to the sensor, to receive a signal from the sensor located on the aircraft to indicate flight conditions of the aircraft. ### Claim 12 (depends on 11) The wing extension of claim 11, the control device being further configured to adjust the CAMD at least partly based on the signal from the sensor located on the aircraft. ### Claim 13 (depends on 7) The wing extension of claim 7, further comprising a wingtip device directly coupled to an outboard portion of the horizontal portion. ### Claim 14 A method comprising: receiving flight condition data from a sensor located on a wing extension of an aircraft; and adjusting a plurality of controllable airflow modification devices (CAMDs) located on the wing extension of the aircraft based at least in part on the received flight condition data, the plurality of CAMDs located on a horizontal portion of the wing extension that is substantially parallel to a baseline wing of the aircraft, a first CAMD of the plurality of CAMDs located outboard of a second CAMD of the plurality of CAMDs, the plurality of CAMDs controllable independently of a control surface of the baseline wing. ### Claim 15 (depends on 14) The method of claim 14, the adjusting of the plurality of CAMDs comprising, for each CAMD, rotating a control surface about a hinge along a horizontal axis such that an edge of the control surface moves up or down in relation to the horizontal portion of the wing extension. ### Claim 16 (depends on 14) The method of claim 14, the adjusting of the plurality of CAMDs configured to reduce a wing load of a wing of the aircraft by moving a center of pressure of the wing, the center of pressure associated with aerodynamic forces acting on the wing, inboard and/or reduce an impact of a wing extension on a fatigue life of a wing of the aircraft, the wing load comprising a bending moment and/or a torsional moment of the wing. ### Claim 17 (depends on 14) The method of claim 14, the adjusting of the plurality of CAMDs comprising adjusting the first CAMD of the plurality of CAMDs independent of the second CAMD of the plurality of CAMDs. ### Claim 18 (depends on 14) The method of claim 14, the adjusting of the plurality of CAMDs comprising adjusting the first CAMD of the plurality of CAMDs in coordination with the second CAMD of the plurality of CAMDs. ### Claim 19 (depends on 14) The method of claim 14, the adjusting of the plurality of CAMDs comprising: adjusting the first CAMD of the plurality of CAMDs to provide a first control response; and adjusting the second CAMD of the plurality of CAMDs to provide a second control response, a magnitude of the first control response being greater than a magnitude of the second control response. ### Claim 20 (depends on 19) The method of claim 19, the adjusting of the plurality of CAMDs further comprising: adjusting the first CAMD of the plurality of CAMDs while the second CAMD of the plurality of CAMDs is adjusted to provide the second control response. ### Claim 21 (depends on 19) The method of claim 19, wherein the magnitude of the second control response is zero and the magnitude of the first control response is greater than zero. ### Claim 22 (depends on 14) The method of claim 14, the adjusting of the plurality of CAMDs comprising: adjusting the first CAMD of the plurality of CAMDs to provide a first control response; and adjusting the second CAMD of the plurality of CAMDs to provide a second control response synchronously with the first CAMD of the plurality of CAMDs, a magnitude of the second control response being equal to a magnitude of the first control response.