CA2593915A1 - Systems and methods for controlling aircraft flaps and spoilers - Google Patents
Systems and methods for controlling aircraft flaps and spoilers Download PDFInfo
- Publication number
- CA2593915A1 CA2593915A1 CA002593915A CA2593915A CA2593915A1 CA 2593915 A1 CA2593915 A1 CA 2593915A1 CA 002593915 A CA002593915 A CA 002593915A CA 2593915 A CA2593915 A CA 2593915A CA 2593915 A1 CA2593915 A1 CA 2593915A1
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- CA
- Canada
- Prior art keywords
- spoiler
- flap
- wing
- actuator
- motion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/32—Air braking surfaces
- B64C9/323—Air braking surfaces associated with wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
- B64D2045/001—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear for indicating symmetry of flaps deflection
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/30—Wing lift efficiency
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned at least partially aft of the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.
Claims
I/We claim:
[c1] 1. An aircraft wing system, comprising:
a wing having a trailing edge;
a flap positioned proximate to the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position;
a first actuator operatively coupled to the flap to move the flap between the first flap position and the second flap position;
a spoiler positioned at least proximate to the flap, the spoiler being movable among at least three positions including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position in which the spoiler is deflected downwardly from the first spoiler position, and a third spoiler position in which the spoiler is deflected upwardly from the first spoiler position; and a second actuator operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions mechanically independently of motion of the flap.
[c2] 2. The system of claim 1 wherein the second actuator is connected to the wing and includes a coupling connected to the spoiler, and wherein the wing does not include a fairing that houses the coupling.
[c3] 3. The system of claim 1, further comprising a controller operatively coupled to the first and second actuators, and wherein the controller is configured to direct the spoiler to the first spoiler position during cruise, the second spoiler position during take-off and landing, and the third spoiler position during speed-braking and roll maneuvers.
[c4] 4. The system of claim 1 wherein the flap is mechanically coupled to the wing, and the spoiler is mechanically coupled to the wing, but the spoiler is not mechanically connected directly to the flap.
[c5] 5. The system of claim 1, further comprising a controller operatively coupled to the first and second actuators to coordinate movement of the first and second actuators.
[c6] 6. The system of claim 1, further comprising a controller operatively coupled to the first and second actuators with non-mechanical links to coordinate movement of the first and second actuators.
[c7] 7. The system of claim 1 wherein the second actuator is configured to move the spoiler independently of the flap during a first mode of operation, and wherein the second actuator is configured to release a force applied to the spoiler allowing the spoiler to be driven by direct mechanical contact with the flap from the second spoiler position to the first spoiler position as the flap moves from the second flap position to the first flap position.
[c8] 8. The system of claim 1 wherein the wing has a trailing edge and a chord line and wherein the flap is a single flap positioned proximate to the wing trailing edge at the chord line.
[c9] 9. A system for controlling an aircraft wing, comprising:
a controller operatively coupled to a flap actuator and a spoiler actuator, the controller being programmed with instructions to:
place the wing in a high lift configuration by directing the flap actuator to deflect the flap downwardly to form a gap with a trailing edge of the wing, and directing the spoiler actuator to deflect the spoiler downwardly to form a gap with the flap, without mechanically tying the motion of the flap to the motion of the spoiler; and place the wing in a speed brake configuration by directing the flap actuator to deflect the flap downwardly, and directing the spoiler actuator to deflect the spoiler upwardly, without mechanically tying the motion of the flap to the motion of the spoiler.
[c10] 10. The system of claim 9 wherein the controller is configured to receive a signal corresponding to a position of the flap, and is configured to direct the spoiler actuator in accordance with a schedule of spoiler and flap positions.
[c11] 11. The system of claim 9 wherein the controller is configured to receive a signal corresponding to a position of the flap, and is configured to at least restrict motion of the spoiler if the flap fails to move to a commanded position.
[c12] 12. The system of claim 9 wherein the controller is programmed with instructions to move the spoiler independently of the flue position.
[c13] 13. A method for operating an aircraft wing system, comprising:
placing the wing in a high lift configuration by deflecting a flap downwardly to form a gap with a trailing edge of the wing, and deflecting a spoiler downwardly to form a gap with the flap without mechanically tying the motion of the flap to the motion of the spoiler; and placing the wing in a speed brake configuration by deflecting the flap downwardly and deflecting the spoiler upwardly without mechanically tying the motion of the flap to the motion of the spoiler.
[c14] 14. The method of claim 13 wherein placing the wing in a high lift configuration includes directing non-mechanical signals via a non-mechanical link from a controller to a first actuator coupled to the flap and to a second actuator coupled to the spoiler.
[c15] 15. The method of claim 13, further comprising placing the wing in a cruise configuration by positioning the flap in a neutral position and positioning the spoiler to form a generally continuous contour with an upper surface of the wing without mechanically tying the motion of the flap to the motion of the spoiler.
[c16] 16. The method of claim 13, further comprising controlling a rolling motion of the aircraft by deflecting a spoiler on one side of a longitudinal centerline of the aircraft upwardly by a first amount, and directing a spoiler on an opposite side of the aircraft centerline not to deflect or to deflect by a second amount.
[c17] 17. The method of claim 13, further comprising receiving an indication of a position of the flap from a flap position sensor, and deflecting the spoiler downwardly in accordance with a schedule of the flap positions and spoiler positions.
[c18] 18. The method of claim 13, further comprising:
placing the wing in a cruise configuration by positioning the flap in a neutral position and positioning the spoiler to form a generally continuous contour with an upper surface of the wing without mechanically tying the motion of the flap to the motion of the spoiler; and controlling a rolling motion of the aircraft by deflecting a spoiler on one side of a longitudinal centerline of the aircraft upwardly by a first amount, and directing a spoiler on an opposite side of the aircraft centerline not to deflect or to deflect by a second amount less than the first amount.
[c19] 19. An aircraft wing system, comprising:
a wing having a trailing edge;
a flap positioned proximate to the wing trailing edge and being deployable relative to the wing;
a first actuator operatively coupled to the flap to move the flap relative to the wing;
a spoiler positioned at least proximate to the flap, the spoiler being deployable relative to the wing; and a second actuator operatively coupled to the spoiler to drive the spoiler during a first mode of operation, the second actuator being configured to release at least a portion of a driving force applied to the spoiler during a second mode of operation to allow the flap to mechanically contact and drive the spoiler.
[c20] 20. The system of claim 19 wherein the flap is deployable between a first flap position and a second flap position, and wherein the spoiler is deployable among at least three positions including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position in which the spoiler is deflected downwardly from the first spoiler position, and a third spoiler position in which the spoiler is deflected upwardly from the first spoiler position.
[c21] 21. The system of claim 19 wherein the flap and the spoiler are moved mechanically independently of each other during the first mode of operation.
[c22] 22. The system of claim 19, further comprising a controller operatively coupled to the first actuator with a first non-mechanical link, and wherein the controller is operatively coupled to the second actuator with a second non-mechanical link.
[c23] 23. The system of claim 19 wherein the second actuator includes a hydraulic actuator and wherein the hydraulic actuator includes a relief valve that at least limits a force applied to the spoiler during operation in the second mode.
[c24] 24. The system of claim 19 wherein the second actuator includes a mechanical actuator and wherein the mechanical actuator includes a clutch that at least reduces a force applied to the spoiler during operation in the second mode.
[c25] 25. The system of claim 19, further comprising a controller operatively coupled to the first and second actuators to transmit operational signals to the first and second actuators, and wherein the system is configured to enter the second mode when the operational signals are not transmitted to the second actuator.
[c26] 26. The system of claim 19, further comprising means for limiting a force applied to the spoiler during operation in the second mode.
[c27] 27. A method for operating a wing system of an aircraft, comprising:
placing the wing in a high lift configuration by deflecting a flap downwardly to form a gap with a trailing edge of the wing, and deflecting a spoiler downwardly to form a gap with the flap in a first mode of operation;
releasing at least a portion of a driving force applied to the spoiler during a second mode of operation to allow the flap to mechanically contact and drive the spoiler.
[c28] 28. The method of claim 27 wherein placing the wing in a high lift configuration includes deflecting the flap and the spoiler without mechanically tying the motion of the flap to the motion of the spoiler during the first mode of operation.
[c29] 29. The method of claim 27 wherein placing the wing in a high lift configuration includes directing a first signal via a first non-mechanical link to a first actuator coupled to the flap, and directing a second signal via a second non-mechanical link to a second actuator coupled to the spoiler.
[c30] 30. The method of claim 27 wherein the spoiler is moved by a hydraulic actuator and wherein the method includes causing a relief valve of the hydraulic actuator to release, so as to at least reduce a force applied to the spoiler during operation in the second mode.
[c31] 31. The method of clam 27 wherein the spoiler is moved by a mechanical actuator and wherein the method includes causing a clutch of the mechanical actuator to slip so as to at least reduce a force applied to the spoiler during operation in the second mode.
[c1] 1. An aircraft wing system, comprising:
a wing having a trailing edge;
a flap positioned proximate to the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position;
a first actuator operatively coupled to the flap to move the flap between the first flap position and the second flap position;
a spoiler positioned at least proximate to the flap, the spoiler being movable among at least three positions including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position in which the spoiler is deflected downwardly from the first spoiler position, and a third spoiler position in which the spoiler is deflected upwardly from the first spoiler position; and a second actuator operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions mechanically independently of motion of the flap.
[c2] 2. The system of claim 1 wherein the second actuator is connected to the wing and includes a coupling connected to the spoiler, and wherein the wing does not include a fairing that houses the coupling.
[c3] 3. The system of claim 1, further comprising a controller operatively coupled to the first and second actuators, and wherein the controller is configured to direct the spoiler to the first spoiler position during cruise, the second spoiler position during take-off and landing, and the third spoiler position during speed-braking and roll maneuvers.
[c4] 4. The system of claim 1 wherein the flap is mechanically coupled to the wing, and the spoiler is mechanically coupled to the wing, but the spoiler is not mechanically connected directly to the flap.
[c5] 5. The system of claim 1, further comprising a controller operatively coupled to the first and second actuators to coordinate movement of the first and second actuators.
[c6] 6. The system of claim 1, further comprising a controller operatively coupled to the first and second actuators with non-mechanical links to coordinate movement of the first and second actuators.
[c7] 7. The system of claim 1 wherein the second actuator is configured to move the spoiler independently of the flap during a first mode of operation, and wherein the second actuator is configured to release a force applied to the spoiler allowing the spoiler to be driven by direct mechanical contact with the flap from the second spoiler position to the first spoiler position as the flap moves from the second flap position to the first flap position.
[c8] 8. The system of claim 1 wherein the wing has a trailing edge and a chord line and wherein the flap is a single flap positioned proximate to the wing trailing edge at the chord line.
[c9] 9. A system for controlling an aircraft wing, comprising:
a controller operatively coupled to a flap actuator and a spoiler actuator, the controller being programmed with instructions to:
place the wing in a high lift configuration by directing the flap actuator to deflect the flap downwardly to form a gap with a trailing edge of the wing, and directing the spoiler actuator to deflect the spoiler downwardly to form a gap with the flap, without mechanically tying the motion of the flap to the motion of the spoiler; and place the wing in a speed brake configuration by directing the flap actuator to deflect the flap downwardly, and directing the spoiler actuator to deflect the spoiler upwardly, without mechanically tying the motion of the flap to the motion of the spoiler.
[c10] 10. The system of claim 9 wherein the controller is configured to receive a signal corresponding to a position of the flap, and is configured to direct the spoiler actuator in accordance with a schedule of spoiler and flap positions.
[c11] 11. The system of claim 9 wherein the controller is configured to receive a signal corresponding to a position of the flap, and is configured to at least restrict motion of the spoiler if the flap fails to move to a commanded position.
[c12] 12. The system of claim 9 wherein the controller is programmed with instructions to move the spoiler independently of the flue position.
[c13] 13. A method for operating an aircraft wing system, comprising:
placing the wing in a high lift configuration by deflecting a flap downwardly to form a gap with a trailing edge of the wing, and deflecting a spoiler downwardly to form a gap with the flap without mechanically tying the motion of the flap to the motion of the spoiler; and placing the wing in a speed brake configuration by deflecting the flap downwardly and deflecting the spoiler upwardly without mechanically tying the motion of the flap to the motion of the spoiler.
[c14] 14. The method of claim 13 wherein placing the wing in a high lift configuration includes directing non-mechanical signals via a non-mechanical link from a controller to a first actuator coupled to the flap and to a second actuator coupled to the spoiler.
[c15] 15. The method of claim 13, further comprising placing the wing in a cruise configuration by positioning the flap in a neutral position and positioning the spoiler to form a generally continuous contour with an upper surface of the wing without mechanically tying the motion of the flap to the motion of the spoiler.
[c16] 16. The method of claim 13, further comprising controlling a rolling motion of the aircraft by deflecting a spoiler on one side of a longitudinal centerline of the aircraft upwardly by a first amount, and directing a spoiler on an opposite side of the aircraft centerline not to deflect or to deflect by a second amount.
[c17] 17. The method of claim 13, further comprising receiving an indication of a position of the flap from a flap position sensor, and deflecting the spoiler downwardly in accordance with a schedule of the flap positions and spoiler positions.
[c18] 18. The method of claim 13, further comprising:
placing the wing in a cruise configuration by positioning the flap in a neutral position and positioning the spoiler to form a generally continuous contour with an upper surface of the wing without mechanically tying the motion of the flap to the motion of the spoiler; and controlling a rolling motion of the aircraft by deflecting a spoiler on one side of a longitudinal centerline of the aircraft upwardly by a first amount, and directing a spoiler on an opposite side of the aircraft centerline not to deflect or to deflect by a second amount less than the first amount.
[c19] 19. An aircraft wing system, comprising:
a wing having a trailing edge;
a flap positioned proximate to the wing trailing edge and being deployable relative to the wing;
a first actuator operatively coupled to the flap to move the flap relative to the wing;
a spoiler positioned at least proximate to the flap, the spoiler being deployable relative to the wing; and a second actuator operatively coupled to the spoiler to drive the spoiler during a first mode of operation, the second actuator being configured to release at least a portion of a driving force applied to the spoiler during a second mode of operation to allow the flap to mechanically contact and drive the spoiler.
[c20] 20. The system of claim 19 wherein the flap is deployable between a first flap position and a second flap position, and wherein the spoiler is deployable among at least three positions including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position in which the spoiler is deflected downwardly from the first spoiler position, and a third spoiler position in which the spoiler is deflected upwardly from the first spoiler position.
[c21] 21. The system of claim 19 wherein the flap and the spoiler are moved mechanically independently of each other during the first mode of operation.
[c22] 22. The system of claim 19, further comprising a controller operatively coupled to the first actuator with a first non-mechanical link, and wherein the controller is operatively coupled to the second actuator with a second non-mechanical link.
[c23] 23. The system of claim 19 wherein the second actuator includes a hydraulic actuator and wherein the hydraulic actuator includes a relief valve that at least limits a force applied to the spoiler during operation in the second mode.
[c24] 24. The system of claim 19 wherein the second actuator includes a mechanical actuator and wherein the mechanical actuator includes a clutch that at least reduces a force applied to the spoiler during operation in the second mode.
[c25] 25. The system of claim 19, further comprising a controller operatively coupled to the first and second actuators to transmit operational signals to the first and second actuators, and wherein the system is configured to enter the second mode when the operational signals are not transmitted to the second actuator.
[c26] 26. The system of claim 19, further comprising means for limiting a force applied to the spoiler during operation in the second mode.
[c27] 27. A method for operating a wing system of an aircraft, comprising:
placing the wing in a high lift configuration by deflecting a flap downwardly to form a gap with a trailing edge of the wing, and deflecting a spoiler downwardly to form a gap with the flap in a first mode of operation;
releasing at least a portion of a driving force applied to the spoiler during a second mode of operation to allow the flap to mechanically contact and drive the spoiler.
[c28] 28. The method of claim 27 wherein placing the wing in a high lift configuration includes deflecting the flap and the spoiler without mechanically tying the motion of the flap to the motion of the spoiler during the first mode of operation.
[c29] 29. The method of claim 27 wherein placing the wing in a high lift configuration includes directing a first signal via a first non-mechanical link to a first actuator coupled to the flap, and directing a second signal via a second non-mechanical link to a second actuator coupled to the spoiler.
[c30] 30. The method of claim 27 wherein the spoiler is moved by a hydraulic actuator and wherein the method includes causing a relief valve of the hydraulic actuator to release, so as to at least reduce a force applied to the spoiler during operation in the second mode.
[c31] 31. The method of clam 27 wherein the spoiler is moved by a mechanical actuator and wherein the method includes causing a clutch of the mechanical actuator to slip so as to at least reduce a force applied to the spoiler during operation in the second mode.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2706676A CA2706676C (en) | 2005-02-04 | 2006-02-03 | Systems and methods for controlling aircraft flaps and spoilers |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/051,738 | 2005-02-04 | ||
US11/051,738 US7338018B2 (en) | 2005-02-04 | 2005-02-04 | Systems and methods for controlling aircraft flaps and spoilers |
PCT/US2006/003889 WO2006084157A2 (en) | 2005-02-04 | 2006-02-03 | Systems and methods for controlling aircraft flaps and spoilers |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CA2706676A Division CA2706676C (en) | 2005-02-04 | 2006-02-03 | Systems and methods for controlling aircraft flaps and spoilers |
Publications (2)
Publication Number | Publication Date |
---|---|
CA2593915A1 true CA2593915A1 (en) | 2006-08-10 |
CA2593915C CA2593915C (en) | 2010-09-07 |
Family
ID=36637020
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CA2706676A Active CA2706676C (en) | 2005-02-04 | 2006-02-03 | Systems and methods for controlling aircraft flaps and spoilers |
CA2593915A Active CA2593915C (en) | 2005-02-04 | 2006-02-03 | Systems and methods for controlling aircraft flaps and spoilers |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CA2706676A Active CA2706676C (en) | 2005-02-04 | 2006-02-03 | Systems and methods for controlling aircraft flaps and spoilers |
Country Status (8)
Country | Link |
---|---|
US (2) | US7338018B2 (en) |
EP (1) | EP1843943B2 (en) |
JP (1) | JP5201997B2 (en) |
CN (1) | CN100500510C (en) |
AT (1) | ATE467555T1 (en) |
CA (2) | CA2706676C (en) |
DE (1) | DE602006014253D1 (en) |
WO (1) | WO2006084157A2 (en) |
Families Citing this family (92)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6799739B1 (en) | 2003-11-24 | 2004-10-05 | The Boeing Company | Aircraft control surface drive system and associated methods |
US7494094B2 (en) * | 2004-09-08 | 2009-02-24 | The Boeing Company | Aircraft wing systems for providing differential motion to deployable lift devices |
US7264206B2 (en) | 2004-09-30 | 2007-09-04 | The Boeing Company | Leading edge flap apparatuses and associated methods |
US7338018B2 (en) | 2005-02-04 | 2008-03-04 | The Boeing Company | Systems and methods for controlling aircraft flaps and spoilers |
US7721999B2 (en) | 2005-05-20 | 2010-05-25 | The Boeing Company | Aerospace vehicle fairing systems and associated methods |
DE102005045759A1 (en) * | 2005-09-23 | 2007-04-12 | Airbus Deutschland Gmbh | Progressive aerofoil trailing edge for aircraft has flap, which can be adjusted both downward and upward by positive and by negative flap deflections respectively whereby aerofoil profile is closed on top side by sealing flap |
US7548800B2 (en) * | 2005-11-09 | 2009-06-16 | The Boeing Company | Method and computer program product for controlling an aerodynamic vehicle having at least one structural mode |
US7708231B2 (en) | 2005-11-21 | 2010-05-04 | The Boeing Company | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
US7475854B2 (en) * | 2005-11-21 | 2009-01-13 | The Boeing Company | Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods |
FR2900126B1 (en) * | 2006-04-21 | 2008-12-26 | Airbus France Sas | METHOD AND APPARATUS FOR REDUCING WAKE SWIRLS OF AN AIRCRAFT APPROACH / LANDING PHASE |
DE102006053259A1 (en) * | 2006-11-11 | 2008-05-21 | Airbus Deutschland Gmbh | High-lift system on the wing of an aircraft and method for its operation |
DE102007009060A1 (en) * | 2007-02-23 | 2008-08-28 | Airbus Deutschland Gmbh | Spoiler for an aerodynamically effective surface of an aircraft |
DE102007046707A1 (en) * | 2007-09-28 | 2009-04-09 | Liebherr-Aerospace Lindenberg Gmbh | Sensor system for monitoring the synchronous operation of control surfaces of an aircraft |
US7954769B2 (en) | 2007-12-10 | 2011-06-07 | The Boeing Company | Deployable aerodynamic devices with reduced actuator loads, and related systems and methods |
US7766282B2 (en) | 2007-12-11 | 2010-08-03 | The Boeing Company | Trailing edge device catchers and associated systems and methods |
GB0808349D0 (en) * | 2008-05-09 | 2008-06-18 | Airbus Uk Ltd | Spoiler deployment mechanism |
DE102008034444B4 (en) * | 2008-05-14 | 2013-09-05 | Diehl Aerospace Gmbh | Input system for a flaps control of an aircraft |
DE102008050544A1 (en) | 2008-10-06 | 2010-04-29 | Airbus Deutschland Gmbh | On the wing of an aircraft arranged slat |
US7945425B2 (en) * | 2008-10-17 | 2011-05-17 | The Boeing Company | In-flight detection of wing flap free wheeling skew |
US8256719B2 (en) * | 2008-12-01 | 2012-09-04 | The Boeing Company | Shape changing airfoil system |
US8226048B2 (en) * | 2008-12-09 | 2012-07-24 | The Boeing Company | Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods |
GB0823392D0 (en) * | 2008-12-23 | 2009-01-28 | Goodrich Actuation Systems Ltd | Drive arrangement |
US8500060B2 (en) * | 2009-02-10 | 2013-08-06 | The Boeing Company | Aircraft with a pressurized vessel |
GB0902685D0 (en) * | 2009-02-18 | 2009-04-01 | Airbus Uk Ltd | Aircraft wing assembly |
US8056865B2 (en) * | 2009-03-05 | 2011-11-15 | The Boeing Company | Mechanism for changing the shape of a control surface |
WO2010135552A2 (en) * | 2009-05-20 | 2010-11-25 | Deka Products Limited Partnership | Centrifugally driven aerodynamic rotor blade brake assembly |
US8382045B2 (en) | 2009-07-21 | 2013-02-26 | The Boeing Company | Shape-changing control surface |
GB0920969D0 (en) * | 2009-11-27 | 2010-01-13 | Airbus Operations Ltd | Trailing edge flap |
GB0920968D0 (en) * | 2009-11-27 | 2010-01-13 | Airbus Operations Ltd | Trailing edge flap |
GB0921007D0 (en) * | 2009-11-30 | 2010-01-13 | Airbus Operations Ltd | Trailing edge flap |
GB0921486D0 (en) | 2009-12-08 | 2010-01-20 | Airbus Operations Ltd | Control surface assembly |
WO2012068136A2 (en) * | 2010-11-15 | 2012-05-24 | Lam Aviation, Inc. | Mechanical control mixer and method therefor |
US8511608B1 (en) * | 2010-11-15 | 2013-08-20 | The Boeing Company | Trailing edge flap system |
US9327824B2 (en) * | 2010-12-15 | 2016-05-03 | The Boeing Company | Adjustment of wings for variable camber for optimum take-off and landing |
US8650811B2 (en) | 2011-02-04 | 2014-02-18 | The Boeing Company | Solar collector frame |
DE102011014687A1 (en) * | 2011-03-22 | 2012-09-27 | Airbus Operations Gmbh | A load introduction element for a movable surface of an aircraft, aircraft with at least one movable surface and at least one load introduction element and method for releasing a movable surface connected to a load introduction element |
GB201108450D0 (en) | 2011-05-20 | 2011-07-06 | Airbus Operations Ltd | Aircraft wing assembly |
US8438743B2 (en) * | 2011-06-01 | 2013-05-14 | Hamilton Sundstrand Corporation | Resolver type skew sensor with gimbal attachment |
US8684316B2 (en) | 2011-09-23 | 2014-04-01 | The Boeing Company | Aircraft flap mechanism having compact large fowler motion providing multiple cruise positions |
GB201117340D0 (en) * | 2011-10-07 | 2011-11-23 | Airbus Uk Ltd | Flat support |
US8783604B2 (en) * | 2011-10-21 | 2014-07-22 | Raytheon Company | Aircraft wing with knuckled rib structure |
US20140076419A1 (en) * | 2012-02-27 | 2014-03-20 | Sinhatech | Self adjusting deturbulator enhanced flap and wind deflector |
US8740139B1 (en) | 2012-04-23 | 2014-06-03 | The Boeing Company | Leading edge snag for exposed propeller engine installation |
CN102642615A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane high lift device with single slotted flaps |
US9108715B2 (en) * | 2012-05-29 | 2015-08-18 | The Boeing Company | Rotary actuated high lift gapped aileron |
EP2682341B1 (en) * | 2012-07-06 | 2014-11-12 | Airbus Operations GmbH | System and method for rigging a control surface of an aircraft |
US9016638B2 (en) * | 2012-09-20 | 2015-04-28 | The Boeing Company | Aircraft flap system and associated method |
US9061753B2 (en) * | 2012-11-29 | 2015-06-23 | The Boeing Company | Hinged panel operation systems and methods |
JP6144487B2 (en) | 2012-12-26 | 2017-06-07 | 三菱航空機株式会社 | Flap deployment device and aircraft |
JP6181942B2 (en) * | 2013-02-28 | 2017-08-16 | 三菱航空機株式会社 | Aircraft warning system and aircraft |
US9689374B2 (en) | 2013-10-09 | 2017-06-27 | Siemens Aktiengesellschaft | Method and apparatus for reduction of fatigue and gust loads on wind turbine blades |
EP2942272A1 (en) | 2014-05-09 | 2015-11-11 | Airbus Operations GmbH | An aircraft wing and an aircraft comprising such aircraft wing |
ES2728917T3 (en) * | 2014-06-12 | 2019-10-29 | Airbus Operations Gmbh | Output device for progressive variation of an aerodynamic profile |
US9623957B2 (en) * | 2014-08-26 | 2017-04-18 | The Boeing Company | Torque tube door |
JP6424079B2 (en) * | 2014-11-28 | 2018-11-14 | ナブテスコ株式会社 | Hydraulic actuator |
JP6362986B2 (en) * | 2014-10-01 | 2018-07-25 | ナブテスコ株式会社 | Hydraulic actuator |
US9994304B2 (en) | 2014-10-01 | 2018-06-12 | Nabtesco Corporation | Hydraulic actuator |
US9950782B2 (en) | 2014-10-31 | 2018-04-24 | The Boeing Company | Methods and apparatus for integrating rotary actuators in flight control systems |
CN104527969B (en) * | 2014-11-19 | 2018-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft front wing servoactuation system and its method of servo-controlling |
US9731812B2 (en) | 2015-01-26 | 2017-08-15 | The Boeing Company | Flap mechanism and associated method |
GB201522486D0 (en) | 2015-12-21 | 2016-02-03 | Airbus Operations Ltd | Seal assembly |
US10472046B1 (en) | 2016-02-03 | 2019-11-12 | Lockheed Martin Corporation | Internal wing control surface linkage system |
US10196131B2 (en) * | 2016-02-16 | 2019-02-05 | The Boeing Company | Hydraulic system and method for an aircraft flight control system |
US10144502B2 (en) * | 2016-03-09 | 2018-12-04 | The Boeing Company | Aerodynamic structures having lower surface spoilers |
US10099771B2 (en) | 2016-03-14 | 2018-10-16 | The Boeing Company | Aircraft wing structure and associated method for addressing lift and drag |
WO2017200441A1 (en) * | 2016-05-19 | 2017-11-23 | Saab Ab | An aircraft secondary control system for aircraft and a method for operating the system |
US11046425B2 (en) * | 2016-05-20 | 2021-06-29 | Bombardier Inc. | Apparatus and methods for actuating a double-slotted flap using a slave screw |
EP3301017B1 (en) * | 2016-09-30 | 2019-08-07 | Airbus Operations GmbH | System for driving and guiding of a trailing edge control surface |
US20180099736A1 (en) * | 2016-10-12 | 2018-04-12 | The Boeing Company | Aircraft wings, aircraft, and related methods |
CN106741865B (en) * | 2016-11-30 | 2019-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of airplane servo actuating system hydraulic control method |
US10538306B2 (en) * | 2016-12-21 | 2020-01-21 | The Boeing Company | Wing flap deflection control removal |
US10137999B2 (en) | 2017-03-30 | 2018-11-27 | The Boeing Company | Methods and apparatus for detecting airflow control surface skew conditions |
US10766602B2 (en) * | 2017-11-01 | 2020-09-08 | The Boeing Company | Mechanical droop for spoiler operation |
CN108045556B (en) * | 2017-11-30 | 2021-05-25 | 中国航空工业集团公司西安飞机设计研究所 | Airplane flaperon motion mechanism |
US10633078B2 (en) * | 2017-12-07 | 2020-04-28 | The Boeing Company | Pre-deformed aircraft spoilers and droop panels designed to seal with flap in deflected state |
US10882604B2 (en) * | 2018-01-18 | 2021-01-05 | The Boeing Company | Distributed trailing edge wing flap systems |
US10882603B2 (en) * | 2018-03-20 | 2021-01-05 | The Boeing Company | Distributed trailing edge wing flap systems |
GB2574442B (en) * | 2018-06-06 | 2021-10-27 | Ge Aviat Systems Ltd | Method and apparatus for reducing aircraft wing bending moment |
CN109080815B (en) * | 2018-07-20 | 2021-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle |
US11001371B2 (en) * | 2018-08-07 | 2021-05-11 | The Boeing Company | Hydraulic droop control for aircraft wing |
US11084569B2 (en) | 2018-09-19 | 2021-08-10 | The Boeing Company | Friction stir welded monolithic aircraft structure and method |
US10926865B2 (en) * | 2018-12-11 | 2021-02-23 | The Boeing Company | Spoiler with releasable portion |
EP3674207B1 (en) | 2018-12-20 | 2024-04-24 | Bombardier Inc. | System and method for controlling aircraft flight control surfaces |
GB2583182B (en) | 2019-03-11 | 2021-03-10 | Borealis Tech Ltd | System and method for determining aircraft safe taxi, takeoff, and flight readiness |
LT6788B (en) | 2019-05-22 | 2020-12-28 | Vilniaus Gedimino technikos universitetas | Aircraft wing with a double hinge |
CN110143272B (en) * | 2019-05-30 | 2021-10-01 | 中国人民解放军海军工程大学 | Device for controlling clearance flow of combined control surface of aircraft |
CN110259748B (en) * | 2019-06-21 | 2021-08-06 | 江西洪都航空工业集团有限责任公司 | Aircraft trailing edge flap folding and unfolding control combination valve |
US11155333B2 (en) | 2019-08-22 | 2021-10-26 | The Boeing Company | Friction stir welded aircraft structure and method |
US11052992B2 (en) * | 2019-11-22 | 2021-07-06 | The Boeing Company | Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings |
US11897596B2 (en) * | 2020-07-21 | 2024-02-13 | The Boeing Company | Methods and apparatus for automatically extending aircraft wing flaps in response to detecting an excess energy steep descent condition |
CN114408158B (en) * | 2022-03-03 | 2024-02-02 | 中国商用飞机有限责任公司 | Turbulent flow device and operation method thereof |
CN115384757B (en) * | 2022-10-31 | 2023-01-24 | 北京启时智航科技有限公司 | Flaperon actuating mechanism and wing structure |
Family Cites Families (377)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2563453A (en) | 1951-08-07 | Device fob controlling the trailing | ||
US2899152A (en) | 1959-08-11 | Aircraft control surface operating mechanism | ||
DE387833C (en) | 1921-05-27 | 1924-01-04 | Handley Page Ltd | Wing for aircraft |
US1770575A (en) | 1927-12-03 | 1930-07-15 | Ksoll Joseph | Aeroplane with supporting surface subdivided by gaps |
US1724456A (en) | 1928-04-24 | 1929-08-13 | Louis H Crook | Aerodynamic control of airplane wings |
FR705155A (en) | 1930-11-05 | 1931-06-02 | Improvements to air navigation devices | |
US2086085A (en) | 1935-05-14 | 1937-07-06 | Handley Page Ltd | Aircraft control gear |
US2138952A (en) | 1935-08-31 | 1938-12-06 | Arado Flugzeugwerke Gmbh | Auxiliary wing for aircraft |
US2169416A (en) | 1936-06-12 | 1939-08-15 | United Aircraft Corp | Slotted deflector flap |
US2117607A (en) * | 1936-08-04 | 1938-05-17 | United Aircraft Corp | Slotted deflector flap |
US2282516A (en) * | 1938-07-11 | 1942-05-12 | Messerschmitt Boelkow Blohm | Airplane wing structure |
US2347230A (en) | 1938-12-16 | 1944-04-25 | Daniel R Zuck | Airplane with nonstalling and glide angle control characteristics |
US2378528A (en) | 1939-05-17 | 1945-06-19 | Arsandaux Louis | Supporting element for aircraft |
US2358985A (en) | 1940-02-23 | 1944-09-26 | James P Mcandrew | Aircraft |
US2289704A (en) | 1940-02-26 | 1942-07-14 | Charles H Grant | Aircraft wing |
US2389274A (en) | 1941-02-04 | 1945-11-20 | Lockheed Aircraft Corp | Aircraft control system |
US2422296A (en) | 1941-08-22 | 1947-06-17 | Curtiss Wright Corp | Slat and flap control system |
US2319383A (en) * | 1942-01-19 | 1943-05-18 | Edward F Zap | Linkage mounting for aerodynamic members |
US2383102A (en) | 1942-02-13 | 1945-08-21 | Edward F Zap | Aerodynamic member |
US2385351A (en) | 1942-06-23 | 1945-09-25 | Jess S W Davidsen | Control system for hydraulically actuated devices |
US2421694A (en) | 1942-07-02 | 1947-06-03 | Lockheed Aircraft Corp | Airplane control surface |
US2458900A (en) * | 1942-08-10 | 1949-01-11 | Curtiss Wright Corp | Flap operating means |
FR978969A (en) | 1942-12-29 | 1951-04-20 | Development of high-lift slit wing planes | |
US2387492A (en) | 1943-03-22 | 1945-10-23 | Curtiss Wright Corp | Hydraulically operated split flap |
US2518854A (en) | 1943-06-14 | 1950-08-15 | Douglas Aircraft Co Inc | Wing high lift flap device |
US2444293A (en) | 1943-06-18 | 1948-06-29 | Curtiss Wright Corp | Gap seal for flaps |
FR984443A (en) | 1943-09-24 | 1951-07-05 | High lift wing | |
US2406475A (en) | 1944-02-19 | 1946-08-27 | Samuel H Pearis | Slotted airplane wing |
US2504684A (en) * | 1946-01-30 | 1950-04-18 | Goodrich Co B F | Extensible structure for varying the configuration of an aircraft surface |
US2502315A (en) * | 1946-02-26 | 1950-03-28 | Beech Aircraft Corp | Operating mechanism for high lift devices for airplanes |
FR61015E (en) | 1946-12-03 | 1955-03-23 | ||
US2555862A (en) | 1947-05-23 | 1951-06-05 | Onera (Off Nat Aerospatiale) | High-lift appliance for largely sweptback wings |
US2665084A (en) * | 1949-11-14 | 1954-01-05 | Northrop Aircraft Inc | Flap actuator and control system |
US2583453A (en) * | 1950-04-19 | 1952-01-22 | Frank G Weisbecker | Knitting machine attachment |
US2665085A (en) * | 1950-06-13 | 1954-01-05 | Blackburn & Gen Aircraft Ltd | Selective dual aileron control for aircraft |
US2652812A (en) | 1952-05-13 | 1953-09-22 | Gen Electric | Combined manual and automatic hydraulic servomotor apparatus |
US2886008A (en) * | 1953-08-03 | 1959-05-12 | Gen Motors Corp | Locking actuator and valve mechanism therefor |
US2877968A (en) * | 1954-10-28 | 1959-03-17 | Gen Electric | Combined manual and automatic servomotor apparatus |
US2851229A (en) | 1956-05-03 | 1958-09-09 | Chance Vought Aircraft Inc | Variable-contour airfoil |
US2864239A (en) | 1956-10-04 | 1958-12-16 | Sperry Rand Corp | Electro-hydraulic servo system for steering dirigible craft |
US2990145A (en) | 1956-11-05 | 1961-06-27 | Gen Electric | Integrated hydraulic power actuator |
US2990144A (en) | 1956-11-05 | 1961-06-27 | Gen Electric | Integrated hydraulic power actuator |
US2920844A (en) * | 1957-04-12 | 1960-01-12 | North American Aviation Inc | Aircraft boundary-layer control system |
US2891740A (en) | 1957-06-27 | 1959-06-23 | John P Campbell | External-flow jet flap |
US2938680A (en) | 1957-07-02 | 1960-05-31 | North American Aviation Inc | Multiple position airfoil slat |
GB853034A (en) | 1957-09-17 | 1960-11-02 | Smith & Sons Ltd S | Improvements in or relating to visual indicators |
US2892312A (en) | 1958-01-27 | 1959-06-30 | Deere & Co | Demand compensated hydraulic system |
US2912190A (en) | 1958-05-05 | 1959-11-10 | Chance Vought Aircraft Inc | Variable-contour airfoil |
US3013748A (en) | 1959-03-11 | 1961-12-19 | Douglas Aircraft Co Inc | Aircraft flap supporting and operating mechanism |
GB886136A (en) | 1960-01-20 | 1962-01-03 | Smith & Sons Ltd S | Improvements in or relating to visual indicating devices for use in aircraft |
US3112089A (en) | 1960-10-12 | 1963-11-26 | Dornier Werke Gmbh | Airplane wing flaps |
DE1129379B (en) | 1960-11-11 | 1962-05-10 | Dornier Werke Gmbh | Airplane wing with fixed leading wing |
US3102607A (en) | 1960-12-19 | 1963-09-03 | Charles E Roberts | Carrier system for transport and delivery along a trackway |
US3089666A (en) | 1961-04-13 | 1963-05-14 | Boeing Co | Airplane having changeable thrust direction |
US3203647A (en) | 1961-12-06 | 1965-08-31 | Alvarez-Calderon Alberto | High lift fdaps for aircraft wings |
US3375998A (en) * | 1962-04-16 | 1968-04-02 | Alberto Alvarez Calderon | Leading edge flap and apparatus thereof |
US3166271A (en) * | 1962-08-20 | 1965-01-19 | Daniel R Zuck | Airplane having non-stalling wings and wing-mounted propellers |
US3203275A (en) | 1962-11-26 | 1965-08-31 | Vaino A Hoover | Mechanical actuator |
US3136504A (en) | 1963-07-02 | 1964-06-09 | William F Carr | Electrical primary flight control system |
US3263946A (en) | 1964-08-19 | 1966-08-02 | Boeing Co | Drive mechanism |
US3282535A (en) | 1964-11-12 | 1966-11-01 | Boeing Co | Leading edge spoiler and flap wing stall control means |
GB1083267A (en) | 1964-12-11 | 1967-09-13 | Power Jets Res & Dev Ltd | Flap systems for aircraft |
US3423858A (en) * | 1967-01-10 | 1969-01-28 | Speno International | Automatic control system for railway work apparatus |
GB1181991A (en) | 1967-04-14 | 1970-02-18 | Edward M Lanier | Aircraft Lift-Increasing Device |
GB1227316A (en) | 1967-05-16 | 1971-04-07 | ||
US3504870A (en) * | 1967-12-08 | 1970-04-07 | Boeing Co | Aircraft wing variable camber leading edge flap |
US3463418A (en) | 1968-03-20 | 1969-08-26 | Edmond S Miksch | Vortex generator for airplane wing |
US3659810A (en) | 1968-05-20 | 1972-05-02 | James L Robertson | Inherently stable tapered wing flaperon airplane |
US3539133A (en) | 1968-05-20 | 1970-11-10 | Robertson Aircraft Corp | Inherently stable tapered wing flaperon airplane |
US3556439A (en) * | 1968-11-22 | 1971-01-19 | Boeing Co | Methods and high lift systems for making an aircraft wing more efficient for takeoffs and landings |
FR1601027A (en) * | 1968-12-30 | 1970-08-03 | ||
US3589648A (en) * | 1969-01-02 | 1971-06-29 | Lockheed Aircraft Corp | Means for controlling the vertical path of an aircraft |
US3587311A (en) | 1969-06-19 | 1971-06-28 | Teledyne Inc | Aircraft instrument system |
US3583660A (en) * | 1969-08-18 | 1971-06-08 | Lockheed Aircraft Corp | Lift and control augmenter for airfoils |
DE1943680C2 (en) | 1969-08-28 | 1982-06-24 | Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen | Control flap arrangement |
US3730459A (en) | 1969-09-18 | 1973-05-01 | D Zuck | Airplane with floating wing and reverse propeller thrust |
FR2064681A5 (en) * | 1969-10-13 | 1971-07-23 | Onera (Off Nat Aerospatiale) | |
DE1962956C3 (en) | 1969-12-16 | 1975-09-04 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Device for deflecting and redirecting the jet of thrust and lifting fans |
US3614028A (en) * | 1970-01-12 | 1971-10-19 | Mc Donnell Douglas Corp | Turbofan-powered stol aircraft |
US3653611A (en) * | 1970-03-24 | 1972-04-04 | Mason Trupp | Slotted delta wing aircraft |
US3704843A (en) | 1970-06-11 | 1972-12-05 | Mc Donnell Douglas Corp | Aircraft control system |
US3655149A (en) * | 1970-09-25 | 1972-04-11 | Lockheed Aircraft Corp | Flap actuating mechanism |
US3711039A (en) * | 1970-10-26 | 1973-01-16 | Boeing Co | Pneumatic leading edge flap for an aircraft wing |
US3776491A (en) | 1971-06-25 | 1973-12-04 | R Oulton | Aircraft with compound wing |
US3743219A (en) | 1971-06-30 | 1973-07-03 | Boeing Co | High lift leading edge device |
GB1404762A (en) * | 1971-10-07 | 1975-09-03 | Lucas Industries Ltd | Electro-hydraulic actuating systems for aircraft control surfaces |
US3813062A (en) | 1971-10-12 | 1974-05-28 | A Prather | Fan-like tail section for man-powered glider aircraft |
US3767140A (en) * | 1971-11-03 | 1973-10-23 | Mc Donnell Douglas Corp | Airplane flaps |
US3807447A (en) * | 1972-02-24 | 1974-04-30 | Daikin Ind Ltd | Fluid controlling apparatus |
US3804267A (en) * | 1972-04-03 | 1974-04-16 | Sperry Rand Corp | Bale wagon |
US3993584A (en) | 1972-12-20 | 1976-11-23 | The Harshaw Chemical Company | Agglomerate containing fibrous polytetrafluoroethylene |
US3790106A (en) * | 1973-01-24 | 1974-02-05 | J Morris | Flap system |
US3831886A (en) | 1973-01-26 | 1974-08-27 | Lockheed Aircraft Corp | Airfoil with extendible and retractable leading edge |
US3837601A (en) | 1973-03-09 | 1974-09-24 | Boeing Co | Aerodynamic slot closing mechanism |
US3827658A (en) | 1973-04-05 | 1974-08-06 | Lockheed Aircraft Corp | Actuating means for a vane |
US3913450A (en) | 1973-05-11 | 1975-10-21 | Dreis & Krump Manufacturing Co | Hydraulic Control system for press brakes or the like |
US3897029A (en) | 1973-07-09 | 1975-07-29 | Alberto Alvarez Calderon | Variable camber multi-slotted flaps |
US3917192A (en) | 1973-07-09 | 1975-11-04 | Alvarez Calderon Alberto | Flap mechanisms and apparatus |
US3836099A (en) | 1973-09-28 | 1974-09-17 | Us Navy | Airfoil camber change system |
US3862730A (en) * | 1973-10-23 | 1975-01-28 | United Aircraft Corp | Fas actuation system |
FR2249804B1 (en) * | 1973-11-06 | 1976-10-01 | Aerospatiale | |
US3910530A (en) | 1973-11-07 | 1975-10-07 | Boeing Co | Leading edge flap |
US3904152A (en) | 1974-03-13 | 1975-09-09 | Lockheed Aircraft Corp | Variable area, variable camber wing for aircraft |
US3994451A (en) | 1974-03-28 | 1976-11-30 | The Boeing Company | Variable camber airfoil |
US3874617A (en) * | 1974-07-17 | 1975-04-01 | Mc Donnell Douglas Corp | Stol flaps |
US3941341A (en) * | 1974-12-13 | 1976-03-02 | Brogdon Jr Glenn F | Quick-release roller attachment for supporting a rope or hose and the like on an aerial ladder |
US3992979A (en) | 1974-12-20 | 1976-11-23 | Joseph Lucas (Industries) Limited | Hydraulic actuating arrangements |
US3987983A (en) | 1974-12-20 | 1976-10-26 | The Boeing Company | Trailing edge flaps having spanwise aerodynamic slot opening and closing mechanism |
US3985319A (en) | 1975-02-03 | 1976-10-12 | The Boeing Company | Variable pivot trailing edge flap |
US4049219A (en) | 1975-02-03 | 1977-09-20 | The Boeing Company | Variable pivot trailing edge flap |
US3991574A (en) | 1975-02-03 | 1976-11-16 | Frazier Larry Vane W | Fluid pressure power plant with double-acting piston |
US3941334A (en) * | 1975-03-28 | 1976-03-02 | The Boeing Company | Variable camber airfoil |
US3968946A (en) | 1975-03-31 | 1976-07-13 | The Boeing Company | Extendable aerodynamic fairing |
US4074878A (en) | 1975-06-23 | 1978-02-21 | Sherman Irving R | Programmed flap system for an aircraft having wings |
US4015787A (en) * | 1975-11-17 | 1977-04-05 | Fairchild Industries Inc. | Aircraft wing |
US4011888A (en) * | 1976-03-12 | 1977-03-15 | Elevator Equipment Co. | Unitary elevator up level control valve |
US4120470A (en) | 1976-09-28 | 1978-10-17 | The Boeing Company | Efficient trailing edge system for an aircraft wing |
US4106730A (en) * | 1976-10-01 | 1978-08-15 | The Boeing Company | Engine out control system for STOL aircraft |
US4180222A (en) | 1976-12-27 | 1979-12-25 | Lockheed Aircraft Corporation | Aileron segment control for a flaperon system |
GB1596642A (en) * | 1977-04-06 | 1981-08-26 | British Aerospace | Aircraft wings |
DE2725632C2 (en) * | 1977-06-07 | 1982-11-11 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Ailerons and flap drives for an aircraft |
US4131253A (en) | 1977-07-21 | 1978-12-26 | The Boeing Company | Variable camber trailing edge for airfoil |
US4171787A (en) | 1977-07-21 | 1979-10-23 | Zapel Edwin J | Variable camber leading edge for airfoil |
US4146200A (en) * | 1977-09-14 | 1979-03-27 | Northrop Corporation | Auxiliary flaperon control for aircraft |
DE2751361C2 (en) | 1977-11-17 | 1984-09-27 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | A method for controlling aircraft by controlling detached wing leading edge eddy currents |
US4189120A (en) * | 1977-12-14 | 1980-02-19 | Boeing Commercial Airplane Company | Variable camber leading edge flap |
US4189121A (en) * | 1978-01-23 | 1980-02-19 | Boeing Commercial Airplane Company | Variable twist leading edge flap |
FR2427499A1 (en) | 1978-06-01 | 1979-12-28 | Sarrazin Applic Hydr | INTEGRATED CONTROL DEVICE FOR FLUID CIRCUIT, AND ITS APPLICATIONS |
US4479620A (en) | 1978-07-13 | 1984-10-30 | The Boeing Company | Wing load alleviation system using tabbed allerons |
US4189122A (en) * | 1978-07-21 | 1980-02-19 | The United States Of America As Represented By The Secretary Of The Navy | Wide angle gimbal system |
US4325123A (en) * | 1978-07-28 | 1982-04-13 | The Boeing Company | Economy performance data avionic system |
US4247843A (en) * | 1978-08-23 | 1981-01-27 | Sperry Corporation | Aircraft flight instrument display system |
US4202519A (en) | 1978-09-08 | 1980-05-13 | The Boeing Company | Airfoil leading edge slat apparatus |
US4275942A (en) | 1978-12-26 | 1981-06-30 | The Boeing Company | Stowage bin mechanism |
US4283029A (en) | 1979-01-02 | 1981-08-11 | Rudolph Peter K C | Actuating apparatus for a flap system having an upper surface blowing powered lift system |
US4293110A (en) | 1979-03-08 | 1981-10-06 | The Boeing Company | Leading edge vortex flap for wings |
US4262868A (en) * | 1979-05-29 | 1981-04-21 | The Boeing Company | Three-position variable camber flap |
US4285482A (en) | 1979-08-10 | 1981-08-25 | The Boeing Company | Wing leading edge high lift device |
US4312486A (en) * | 1979-09-20 | 1982-01-26 | The Boeing Company | Variable camber trailing edge for airfoil |
US4360176A (en) | 1979-11-05 | 1982-11-23 | The Boeing Company | Wing leading edge slat |
US4461449A (en) | 1980-05-01 | 1984-07-24 | The Boeing Company | Integral hydraulic blocking and relief valve |
US4351502A (en) | 1980-05-21 | 1982-09-28 | The Boeing Company | Continuous skin, variable camber airfoil edge actuating mechanism |
US4358077A (en) | 1980-06-16 | 1982-11-09 | Coronel Paul K | Transverse wing actuation system |
US4363098A (en) | 1980-06-24 | 1982-12-07 | The Boeing Company | Electric command spoiler system |
US4365774A (en) | 1980-08-08 | 1982-12-28 | Coronel Paul K | Convertible delta wing aircraft |
US4353517A (en) | 1980-10-07 | 1982-10-12 | The Boeing Company | Flap assembly for aircraft wing |
FR2492337A1 (en) | 1980-10-16 | 1982-04-23 | Aerospatiale | AIRCRAFT WING WITH A HYPERSUSTENTATOR SYSTEM IN ITS ATTACK EDGE AND AIRCRAFT COMPRISING SUCH AILET |
US4368937A (en) * | 1981-02-17 | 1983-01-18 | The Boeing Company | Overhead stowage bin mechanism |
US4459084A (en) | 1981-05-26 | 1984-07-10 | Clark Garry E | Internal combustion driven pumping system and variable torque transmission |
US4498646A (en) * | 1981-07-01 | 1985-02-12 | Dornier Gmbh | Wing for short take-off and landing aircraft |
US4485992A (en) | 1981-09-10 | 1984-12-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Leading edge flap system for aircraft control augmentation |
US4472780A (en) * | 1981-09-28 | 1984-09-18 | The Boeing Company | Fly-by-wire lateral control system |
US4427168A (en) * | 1981-09-29 | 1984-01-24 | The Boeing Company | Variable camber leading edge mechanism with Krueger flap |
US4471927A (en) | 1981-09-29 | 1984-09-18 | The Boeing Company | Trailing edge flap assembly |
DE3140350A1 (en) | 1981-10-10 | 1983-04-28 | Dornier Gmbh, 7990 Friedrichshafen | PROFILES, IN PARTICULAR WING PROFILES FOR AIRCRAFT |
US4433615A (en) † | 1981-10-22 | 1984-02-28 | The Bendix Corporation | Blocking and thermal relief valve |
US4444368A (en) * | 1981-10-30 | 1984-04-24 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Slotted variable camber flap |
DE3149629C1 (en) | 1981-12-15 | 1983-04-21 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Device for sealing an air gap on an aircraft flap |
US4700911A (en) | 1982-02-09 | 1987-10-20 | Dornier Gmbh | Transverse driving bodies, particularly airplane wings |
US4441675A (en) * | 1982-06-25 | 1984-04-10 | Mcdonnell Douglas Corporation | High lift surface actuation system |
EP0100775B1 (en) | 1982-08-09 | 1987-01-21 | The Boeing Company | Wing leading edge slat |
US4747375A (en) | 1982-08-31 | 1988-05-31 | Williams John K | Device for controlling the phased displacement of rotating shafts |
EP0103038A1 (en) | 1982-09-13 | 1984-03-21 | The Boeing Company | Continuous skin, variable camber airfoil edge actuating mechanism |
US4575030A (en) * | 1982-09-13 | 1986-03-11 | The Boeing Company | Laminar flow control airfoil |
US4496121A (en) * | 1982-09-21 | 1985-01-29 | The Boeing Company | Control surface lock for flutter constraint |
US4448375A (en) | 1982-09-29 | 1984-05-15 | The Boeing Company | Folding truss mechanism for trailing edge flaps |
SE434762B (en) | 1982-11-29 | 1984-08-13 | Ingemanssons Ingenjorsbyra Ab | SEALING DEVICE AT TROSKELLOS DORR |
US4618109A (en) | 1982-12-06 | 1986-10-21 | The Boeing Company | Wing trailing edge air dams |
US4712752A (en) | 1982-12-06 | 1987-12-15 | The Boeing Company | Wing trailing edge air dam |
US4706913A (en) | 1982-12-28 | 1987-11-17 | The Boeing Company | Variable camber leading edge assembly for an airfoil |
US4475702A (en) | 1982-12-28 | 1984-10-09 | The Boeing Company | Variable camber leading edge assembly for an airfoil |
DE3277502D1 (en) | 1982-12-30 | 1987-11-26 | Boeing Co | Variable-camber airfoil |
US4533096A (en) | 1982-12-30 | 1985-08-06 | The Boeing Company | High lift system control assembly |
US4729528A (en) * | 1983-02-28 | 1988-03-08 | Northrop Corporation | Aeroelastic control flap |
US4530271A (en) † | 1983-06-21 | 1985-07-23 | Lockheed Corporation | Electric actuator system with hydraulic coupling as protection against mechanical jamming |
US4542869A (en) * | 1983-06-23 | 1985-09-24 | Mcdonnell Douglas Corporation | Flap mechanism |
GB8321281D0 (en) | 1983-08-06 | 1983-09-28 | British Aerospace | Underwing engine installation |
US4544117A (en) | 1983-11-14 | 1985-10-01 | Lockheed Corporation | Leading edge flap and boundary layer control system |
FR2555960B1 (en) * | 1983-12-06 | 1986-09-19 | Aerospatiale | BOOM AIRCRAFT WING PROVIDED WITH A HYPERSUSTENTATOR SYSTEM AND AN ENGINE SUSPENSION MAT, AS WELL AS AN ENGINE SUSPENSION MAT FOR SUCH A WING |
US4575099A (en) * | 1984-01-27 | 1986-03-11 | General Electric Company | High excursion seal with flexible membrane to prevent gas leakage through hinge |
US4605187A (en) | 1984-03-09 | 1986-08-12 | The Boeing Company | Wing flap mechanism |
US4899284A (en) * | 1984-09-27 | 1990-02-06 | The Boeing Company | Wing lift/drag optimizing system |
US4576347A (en) * | 1984-10-30 | 1986-03-18 | The Boeing Company | Flap torque tube slot seal |
US4702442A (en) | 1984-12-06 | 1987-10-27 | The Boeing Company | Aircraft trailing edge flap apparatus |
US4702441A (en) | 1984-12-31 | 1987-10-27 | The Boeing Company | Aircraft wing stall control device and method |
US5082207A (en) * | 1985-02-04 | 1992-01-21 | Rockwell International Corporation | Active flexible wing aircraft control system |
US4669687A (en) | 1985-03-06 | 1987-06-02 | The Boeing Company | Airfoil flap member with flap track member |
DE3530865A1 (en) * | 1985-08-29 | 1987-03-12 | Messerschmitt Boelkow Blohm | DRIVE AND GUIDE DEVICE FOR A FLAP SYSTEM ARRANGED ON AN AIRCRAFT WING |
EP0218021B1 (en) * | 1985-08-29 | 1988-06-08 | Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung | Flaps arrangement for an aircraft wing |
DE3530862A1 (en) * | 1985-08-29 | 1987-03-12 | Messerschmitt Boelkow Blohm | FLAP ARRANGEMENT FOR AN AIRCRAFT WING |
US4796192A (en) * | 1985-11-04 | 1989-01-03 | The Boeing Company | Maneuver load alleviation system |
US4650140A (en) * | 1985-12-30 | 1987-03-17 | The Boeing Company | Wind edge movable airfoil having variable camber |
US4717097A (en) * | 1986-03-03 | 1988-01-05 | The Boeing Company | Aircraft wings with aileron-supported ground speed spoilers and trailing edge flaps |
US4779822A (en) | 1986-05-23 | 1988-10-25 | Sundstrand Corporation | Actuator system |
US4691879A (en) | 1986-06-16 | 1987-09-08 | Greene Vibert F | Jet airplane |
DE3620886A1 (en) | 1986-06-21 | 1988-01-14 | Messerschmitt Boelkow Blohm | DRIVE DEVICE WITH VARIABLE TORQUE LIMITING SYSTEM |
FR2606363B1 (en) | 1986-11-07 | 1989-03-03 | Aerospatiale | SYSTEM FOR CONTROLLING THE AIRCRAFT SHUTTERS OF AN AIRCRAFT |
US4784355A (en) * | 1986-11-10 | 1988-11-15 | The United States Of America As Represented By The Secretary Of The Air Force | Flap system for short takeoff and landing aircraft |
DE3641247A1 (en) | 1986-12-03 | 1988-06-16 | Messerschmitt Boelkow Blohm | LANDING VALVE GUIDE RAIL FAIRING FOR AIRCRAFT |
US4823826A (en) * | 1986-12-22 | 1989-04-25 | Pony Industries, Inc. | Process and apparatus for introducing aqueous chloride dioxide into high pressure water injection wells |
DE3702294C1 (en) | 1987-01-27 | 1988-04-14 | Messerschmitt Boelkow Blohm | Actuator for wing flaps of aircraft |
GB8711252D0 (en) | 1987-05-13 | 1987-07-15 | British Aerospace | High lift device |
US5100082A (en) * | 1987-09-17 | 1992-03-31 | The Boeing Company | Hydraulic power supplies |
US4834319A (en) | 1987-10-05 | 1989-05-30 | Allied-Signal Inc. | Differentially coupled dual channel actuator |
US5074495A (en) | 1987-12-29 | 1991-12-24 | The Boeing Company | Load-adaptive hybrid actuator system and method for actuating control surfaces |
US4823836A (en) * | 1988-05-31 | 1989-04-25 | Lothar Bachmann | Dampers with leaf spring seals |
US4867394A (en) | 1988-06-23 | 1989-09-19 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Compression pylon |
US5046688A (en) | 1988-10-28 | 1991-09-10 | The Boeing Company | Wing major assembly jig |
US5039032A (en) | 1988-11-07 | 1991-08-13 | The Boeing Company | High taper wing tip extension |
US5050081A (en) | 1988-11-14 | 1991-09-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and system for monitoring and displaying engine performance parameters |
GB8827345D0 (en) | 1988-11-23 | 1988-12-29 | Smiths Industries Plc | Aircraft instrument systems |
US5129597A (en) | 1989-02-06 | 1992-07-14 | Deutsche Airbus Gmbh | Ceiling luggage compartment combination for the passenger cabin of an aircraft |
US4962902A (en) | 1989-03-20 | 1990-10-16 | The Boeing Company | Aircraft control surface linkage |
GB8915487D0 (en) * | 1989-07-06 | 1989-08-23 | Short Brothers Plc | A flap assembly |
DE3930862A1 (en) | 1989-09-15 | 1991-03-28 | Vdo Schindling | METHOD AND DEVICE FOR PRESENTING AIRPORT INFORMATION |
US5082208A (en) * | 1989-09-29 | 1992-01-21 | The Boeing Company | System and method for controlling an aircraft flight control member |
US5056741A (en) | 1989-09-29 | 1991-10-15 | The Boeing Company | Apparatus and method for aircraft wing stall control |
US5094412A (en) * | 1989-10-13 | 1992-03-10 | Bell Helicopter Textron Inc. | Flaperon system for tilt rotor wings |
US5088665A (en) * | 1989-10-31 | 1992-02-18 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Serrated trailing edges for improving lift and drag characteristics of lifting surfaces |
US5114100A (en) | 1989-12-29 | 1992-05-19 | The Boeing Company | Anti-icing system for aircraft |
US5167383A (en) | 1990-08-18 | 1992-12-01 | Yoshio Nozaki | STOL aircraft |
DE4033277A1 (en) | 1990-10-19 | 1992-04-23 | Airbus Gmbh | DRIVING DEVICE FOR FLAPS ARRANGED ON AIRCRAFT WINGS |
US5094411A (en) * | 1990-10-19 | 1992-03-10 | Vigyan, Inc. | Control configured vortex flaps |
US5203619A (en) * | 1990-11-07 | 1993-04-20 | Intermetro Industries Corporation | Storage system including a vertically retractable storage unit |
GB9026451D0 (en) | 1990-12-05 | 1991-01-23 | Smiths Industries Plc | Aircraft display systems |
DE4105459A1 (en) | 1991-02-21 | 1992-08-27 | Heilmeier & Weinlein | HYDRAULIC CONTROL DEVICE |
JPH07112836B2 (en) | 1991-06-14 | 1995-12-06 | 富士重工業株式会社 | Aircraft hydraulic steering system |
DE4130644A1 (en) | 1991-09-14 | 1993-03-18 | Airbus Gmbh | UPPER LUGGAGE RACK WITH A LOWERABLE TRAY, IN PARTICULAR FOR A PASSENGER PLANE |
US5158252A (en) | 1991-10-24 | 1992-10-27 | The Boeing Company | Three-position variable camber Krueger leading edge flap |
US5280863A (en) * | 1991-11-20 | 1994-01-25 | Hugh Schmittle | Lockable free wing aircraft |
GB9201762D0 (en) | 1992-01-28 | 1992-03-11 | Wes Technology Inc | Seals for gas isolators |
DE4209037C2 (en) | 1992-03-20 | 1994-06-23 | Deutsche Aerospace Airbus | Device for carrying luggage in airplanes |
US5681014A (en) | 1992-05-15 | 1997-10-28 | Palmer; Harry W. | Torsional twist airfoil control means |
US5493497A (en) * | 1992-06-03 | 1996-02-20 | The Boeing Company | Multiaxis redundant fly-by-wire primary flight control system |
FR2695905B1 (en) | 1992-09-24 | 1994-12-16 | Aerospatiale | Rigid kruger spout, for leading edge of aircraft wings. |
US5310387A (en) | 1992-09-30 | 1994-05-10 | Hughes Aircraft Company | Differential motor drive |
US5282591A (en) * | 1992-12-21 | 1994-02-01 | The United States Of America As Represented By The Secretary Of The Navy | Active vortex control for a high performance wing |
FR2709110B1 (en) * | 1993-08-20 | 1995-11-10 | Lucas Air Equipement | Servo-control device of an aircraft flight control member. |
US5544847A (en) | 1993-11-10 | 1996-08-13 | The Boeing Company | Leading edge slat/wing combination |
US5388788A (en) * | 1993-12-16 | 1995-02-14 | The Boeing Company | Hinge fairings for control surfaces |
GB9405001D0 (en) | 1994-03-15 | 1994-04-27 | British Aerospace | Rigging of aircraft wing flaps |
DE4422152C2 (en) * | 1994-06-27 | 2000-02-03 | Daimler Chrysler Aerospace | Method and arrangement for optimizing the aerodynamic effect of a wing |
US5535852A (en) | 1994-08-17 | 1996-07-16 | Bishop; David J. | Lift apparatus |
FR2728535A1 (en) * | 1994-12-26 | 1996-06-28 | Aerospatiale | VARIABLE SLOTTED AEROBRAKE FOR AIRCRAFT WING |
US5686907A (en) | 1995-05-15 | 1997-11-11 | The Boeing Company | Skew and loss detection system for individual high lift devices |
US5680124A (en) | 1995-05-15 | 1997-10-21 | The Boeing Company | Skew and loss detection system for adjacent high lift devices |
US5609020A (en) * | 1995-05-15 | 1997-03-11 | The Boeing Company | Thrust reverser synchronization shaft lock |
US5711496A (en) * | 1995-06-30 | 1998-01-27 | Nusbaum; Steve R. | STOL aircraft and wing slat actuating mechanism for same |
US5715163A (en) * | 1995-08-22 | 1998-02-03 | The Boeing Company | Cursor controlled navigation system for aircraft |
US5681013A (en) | 1995-12-26 | 1997-10-28 | The Boeing Company | Vortex leading edge flap assembly for supersonic airplanes |
US5915653A (en) | 1996-01-02 | 1999-06-29 | The Boeing Company | Spherical mating fairings for hingeline applications |
US5875998A (en) * | 1996-02-05 | 1999-03-02 | Daimler-Benz Aerospace Airbus Gmbh | Method and apparatus for optimizing the aerodynamic effect of an airfoil |
US5743490A (en) * | 1996-02-16 | 1998-04-28 | Sundstrand Corporation | Flap/slat actuation system for an aircraft |
WO1997038900A1 (en) * | 1996-04-13 | 1997-10-23 | Michael Craig Broadbent | Variable camber wing mechanism |
US5927656A (en) | 1996-06-26 | 1999-07-27 | The Boeing Company | Wing leading edge flap and method therefor |
SE507968C2 (en) | 1996-07-25 | 1998-08-03 | Electrolux Ab | Carrier, e.g. for wall mounted household stove |
GB9619488D0 (en) | 1996-09-18 | 1996-10-30 | Dowty Boulton Paul Ltd | Flight control surface actuation system |
DE19643222C2 (en) | 1996-10-19 | 1998-12-10 | Daimler Benz Ag | Float with variable curvature |
US5788190A (en) | 1996-10-22 | 1998-08-04 | The Boeing Company | Slotted cruise trailing edge flap |
US6293497B1 (en) | 1996-10-22 | 2001-09-25 | The Boeing Company | Airplane with unswept slotted cruise wing airfoil |
US5836550A (en) | 1996-11-27 | 1998-11-17 | Boeing Company | Mechanism for streamwise fowler deployment of the wing trailing or leading edge |
CN1184056A (en) * | 1996-11-29 | 1998-06-10 | 三星航空产业株式会社 | Airfoil of aircraft |
JP3638745B2 (en) * | 1997-02-07 | 2005-04-13 | 富士重工業株式会社 | Rotor blade with rotary spoiler |
DE19712034A1 (en) | 1997-03-21 | 1998-09-24 | Deutsch Zentr Luft & Raumfahrt | Flexible leading edge profile for aerofoil |
US5918836A (en) * | 1997-03-25 | 1999-07-06 | Sundstrand Corporation | Aircraft spoiler blow-down mechanism |
GB2323576B (en) | 1997-03-26 | 2001-08-22 | British Aerospace | Fairing arrangements for aircraft |
US6082679A (en) | 1997-06-26 | 2000-07-04 | The Boeing Company | Active system for early destruction of trailing vortices |
US6389333B1 (en) | 1997-07-09 | 2002-05-14 | Massachusetts Institute Of Technology | Integrated flight information and control system |
US5934615A (en) | 1997-08-25 | 1999-08-10 | Hexcel Corporation | Luggage bins with articulating mechanism |
US7455264B2 (en) | 1997-08-26 | 2008-11-25 | Mcdonnell Douglas Corporation | Reconfiguration control system for an aircraft wing |
US5957798A (en) † | 1997-09-10 | 1999-09-28 | Gec-Marconi Aerospace Inc. | Fail-free actuator assembly |
US6209824B1 (en) * | 1997-09-17 | 2001-04-03 | The Boeing Company | Control surface for an aircraft |
DE19741490C2 (en) | 1997-09-19 | 2000-06-08 | Deutsch Zentr Luft & Raumfahrt | Inflow profile with variable profile adaptation |
US5921506A (en) | 1997-09-25 | 1999-07-13 | Northrop Grumman Corporation | Extendible leading edge flap |
US6112141A (en) | 1997-10-15 | 2000-08-29 | Dassault Aviation | Apparatus and method for graphically oriented aircraft display and control |
US5978715A (en) | 1997-10-15 | 1999-11-02 | Dassault Aviation | Apparatus and method for aircraft display and control |
US6057786A (en) | 1997-10-15 | 2000-05-02 | Dassault Aviation | Apparatus and method for aircraft display and control including head up display |
US5839698A (en) | 1997-10-23 | 1998-11-24 | Northrop Grumman Corporation | Control surface continuous seal |
US6085129A (en) | 1997-11-14 | 2000-07-04 | Rockwell Collins, Inc. | Integrated vertical profile display |
US5984230A (en) | 1997-12-15 | 1999-11-16 | Orazi; Paul | Wing assemblies for aircraft |
US6079672A (en) | 1997-12-18 | 2000-06-27 | Lam; Lawrence Y. | Aileron for fixed wing aircraft |
US6145791A (en) | 1998-01-09 | 2000-11-14 | Northrop Grumman Corporation | Elastomeric transition for aircraft control surface |
ES2156660B1 (en) | 1998-01-14 | 2002-02-16 | Saiz Manuel Munoz | FLIGHT CONTROLS WITH AUTOMATIC COMPENSATION. |
US7051982B1 (en) | 1998-03-27 | 2006-05-30 | Bae Systems Plc | Fairing arrangements for aircraft |
US6068219A (en) | 1998-04-13 | 2000-05-30 | Northrop Grumman Corporation | Single surface multi axis aircraft control |
DE19819341C2 (en) | 1998-04-30 | 2000-06-15 | Daimler Chrysler Aerospace | Method for reducing gust loads on an aircraft below the cruising altitude |
EP0958999B2 (en) * | 1998-05-21 | 2007-08-29 | McDonnell Douglas Corporation | Aerofoil |
US6188937B1 (en) * | 1998-09-30 | 2001-02-13 | Honeywell International Inc. | Methods and apparatus for annunciation of vehicle operational modes |
US6045204A (en) * | 1998-10-13 | 2000-04-04 | Hexcel Corporation | Overhead stowage bins in aircraft |
GB9823599D0 (en) * | 1998-10-28 | 1998-12-23 | Lucas Ind Plc | Brake assembly |
US6189837B1 (en) * | 1998-10-29 | 2001-02-20 | The Boeing Company | Auxiliary spoiler retract system |
DE19858872C2 (en) | 1998-12-19 | 2001-02-08 | Daimler Chrysler Ag | Adaptive aircraft wing |
FR2787759B1 (en) | 1998-12-28 | 2001-03-16 | Aerospatiale | METHOD AND SYSTEM FOR CONTROLLING A GOVERNOR OF AN AIRCRAFT OPERATED BY MULTIPLE HYDRAULIC CYLINDERS AND MODULAR POWER |
US6382566B1 (en) | 1998-12-29 | 2002-05-07 | The Boeing Company | Method and apparatus for detecting skew and asymmetry of an airplane flap |
US6164598A (en) | 1999-03-10 | 2000-12-26 | Northrop Grumman Corporation | Adaptive control surface apparatus |
DE19910551C2 (en) * | 1999-03-10 | 2001-04-05 | Eads Airbus Gmbh | Aircraft wing with at least one short-coupled engine |
US6328265B1 (en) | 1999-05-25 | 2001-12-11 | Faruk Dizdarevic | Slot forming segments and slot changing spoilers |
US6173924B1 (en) * | 1999-06-15 | 2001-01-16 | Northrop Grumman Corporation | Low density flexible edge transition |
US6244542B1 (en) | 1999-07-20 | 2001-06-12 | Northrop Grumman Corporation | Rotor driven edge |
GB9920318D0 (en) | 1999-08-27 | 1999-11-03 | British Aerospace | A fairing arrangement for an aircraft |
US6466141B1 (en) * | 1999-09-28 | 2002-10-15 | Lucas Industries Limited | Skew detection system |
DE10001038B4 (en) | 2000-01-13 | 2004-01-29 | Airbus Deutschland Gmbh | Luggage rack with a lowerable luggage compartment, especially for an aircraft passenger cabin |
US6598834B2 (en) | 2000-02-14 | 2003-07-29 | Aerotech Services Inc. | Method for reducing fuel consumption in aircraft |
FR2806488B1 (en) | 2000-03-16 | 2002-05-17 | Snecma Moteurs | DEVICE AND METHOD FOR REGULATING PRESSURE AND FLOW OF FUEL SUPPLYING A UNIT OF VALVES |
DE10019187C1 (en) * | 2000-04-17 | 2002-01-03 | Airbus Gmbh | Pressure control for a sinker |
JP2001343032A (en) | 2000-06-01 | 2001-12-14 | Komatsu Ltd | Fluid pressure control valve of clutch or brake and fluid pressure control method |
FR2811037B1 (en) | 2000-06-28 | 2002-10-18 | Aerospatiale Matra Airbus | ELECTRICALLY CONTROLLED HYDRAULIC ACTUATION SYSTEM |
US6431498B1 (en) | 2000-06-30 | 2002-08-13 | Philip Watts | Scalloped wing leading edge |
US6561463B1 (en) * | 2000-07-14 | 2003-05-13 | Honeywell International Inc. | Flight control module with integrated spoiler actuator control electronics |
US6464175B2 (en) | 2000-07-14 | 2002-10-15 | Honda Giken Kogyo Kabushiki Kaisha | Rotor blade operating device in airplane and flaperon operating device in airplane |
US6439512B1 (en) | 2000-08-24 | 2002-08-27 | Hr Textron, Inc. | All-hydraulic powered horizontal stabilizer trim control surface position control system |
US6443394B1 (en) | 2000-09-21 | 2002-09-03 | The B.F. Goodrich Company | Inflatable airfoil device |
DE10055961B4 (en) | 2000-11-11 | 2004-09-09 | Eads Deutschland Gmbh | Variable wing area with adjustable profile shape that extends in the span direction |
US6375126B1 (en) * | 2000-11-16 | 2002-04-23 | The Boeing Company | Variable camber leading edge for an airfoil |
US20020046087A1 (en) * | 2000-12-18 | 2002-04-18 | John Hey | Method of drawing attention to advertisements |
US6481667B1 (en) | 2001-03-05 | 2002-11-19 | Northrop Grumman Corporation | System and method for deflecting an aerodynamic control surface |
NL1017811C2 (en) | 2001-04-10 | 2002-10-11 | Stork Prod Eng | Cabin baggage assembly with underpressure. |
US6547183B2 (en) * | 2001-08-02 | 2003-04-15 | The Boeing Company | Moveable closet |
US6478541B1 (en) | 2001-08-16 | 2002-11-12 | The Boeing Company | Tapered/segmented flaps for rotor blade-vortex interaction (BVI) noise and vibration reduction |
US6870490B2 (en) * | 2001-08-23 | 2005-03-22 | Honeywell International Inc. | Display of altitude and path capture trajectories |
US20030132860A1 (en) | 2001-09-21 | 2003-07-17 | Honeywell International, Inc. | Interface for visual cueing and control for tactical flightpath management |
US6591169B2 (en) | 2001-09-27 | 2003-07-08 | The Boeing Company | Method and computer program product for controlling the actuators of an aerodynamic vehicle |
US6622972B2 (en) | 2001-10-31 | 2003-09-23 | The Boeing Company | Method and system for in-flight fault monitoring of flight control actuators |
GB0127254D0 (en) * | 2001-11-13 | 2002-01-02 | Lucas Industries Ltd | Aircraft flight surface control system |
EP1338506A1 (en) | 2002-02-15 | 2003-08-27 | Fairchild Dornier GmbH | Airplane wing with slat and Krueger flap |
US6601801B1 (en) | 2002-04-24 | 2003-08-05 | The Boeing Company | Gapped trailing-edge control surface for an airfoil |
US6745113B2 (en) | 2002-06-07 | 2004-06-01 | The Boeing Company | Method and system for autoflight information display |
FR2840877B1 (en) | 2002-06-13 | 2004-08-06 | Airbus France | DEVICE FOR JOINING A COMPONENT ON AERODYNAMIC AIRCRAFT SURFACE |
US7258308B2 (en) * | 2002-07-02 | 2007-08-21 | The Boeing Company | Method and apparatus for controlling airflow with a gapped trailing edge device having a flexible flow surface |
US6698523B2 (en) * | 2002-07-02 | 2004-03-02 | Husco International, Inc. | Electrohydraulic control system for implement lift cylinders |
US6802475B2 (en) | 2002-07-04 | 2004-10-12 | Smiths Wolverhampton Limited | Flight surface actuator |
US6622974B1 (en) | 2002-08-14 | 2003-09-23 | The Boeing Company | Geometric morphing wing with expandable spars |
US6796534B2 (en) | 2002-09-10 | 2004-09-28 | The Boeing Company | Method and apparatus for controlling airflow with a leading edge device having a flexible flow surface |
US20040059474A1 (en) * | 2002-09-20 | 2004-03-25 | Boorman Daniel J. | Apparatuses and methods for displaying autoflight information |
US7048235B2 (en) * | 2002-10-09 | 2006-05-23 | The Boeing Company | Slotted aircraft wing |
US7048228B2 (en) | 2002-10-09 | 2006-05-23 | The Boeing Company | Slotted aircraft wing |
US6755375B2 (en) | 2002-10-22 | 2004-06-29 | The Boeing Company | Method and apparatus for controlling aircraft devices with multiple actuators |
US6796526B2 (en) | 2002-11-25 | 2004-09-28 | The Boeing Company | Augmenting flight control surface actuation system and method |
DE10313728B4 (en) * | 2003-03-27 | 2011-07-21 | Airbus Operations GmbH, 21129 | Flap system on the wing of a fixed-wing aircraft |
US6827311B2 (en) * | 2003-04-07 | 2004-12-07 | Honeywell International, Inc. | Flight control actuation system |
CA2427416C (en) | 2003-05-01 | 2010-11-16 | 101039130 Saskatchewan Ltd. | Steering device for towed implements |
US7070381B2 (en) | 2003-05-20 | 2006-07-04 | Khan Farooq A | Hydraulic control system for refuse collection vehicle |
US7059563B2 (en) * | 2003-06-03 | 2006-06-13 | The Boeing Company | Systems, apparatuses, and methods for moving aircraft control surfaces |
US7243881B2 (en) * | 2003-06-03 | 2007-07-17 | The Boeing Company | Multi-function trailing edge devices and associated methods |
DE10326799B3 (en) | 2003-06-13 | 2004-12-16 | Airbus Deutschland Gmbh | Device for actuating flap elements on the wings of an aircraft |
US6843452B1 (en) * | 2003-06-17 | 2005-01-18 | The Boeing Company | Variable trailing edge geometry and spanload control |
US6824099B1 (en) | 2003-07-10 | 2004-11-30 | The Boeing Company | Brake systems for aircraft wing flaps and other control surfaces |
US7028948B2 (en) * | 2003-08-28 | 2006-04-18 | The Boeing Company | Apparatus for increase of aircraft lift and maneuverability |
FR2859976B1 (en) * | 2003-09-22 | 2006-12-08 | Airbus France | AIRCRAFT WING COMPRISING AT LEAST ONE DEPORTER SHUTTER AND DEPORTER SHUTTER FOR SAID WING |
FI115764B (en) | 2003-11-03 | 2005-07-15 | Patria Finavicomp Oy | Arrangement for forming vortexes |
US6799739B1 (en) | 2003-11-24 | 2004-10-05 | The Boeing Company | Aircraft control surface drive system and associated methods |
DE10361891A1 (en) | 2003-12-23 | 2005-08-04 | Airbus Deutschland Gmbh | Device for controlling and adjusting flaps on aircraft wings |
US7460029B2 (en) | 2003-12-24 | 2008-12-02 | The Boeing Company | Systems and methods for presenting and obtaining flight control information |
US7424350B2 (en) | 2004-02-02 | 2008-09-09 | The Boeing Company | Vehicle control systems and corresponding sizing methods |
FR2866627B1 (en) * | 2004-02-24 | 2006-05-05 | Airbus France | METHOD AND DEVICE FOR OPTIMIZING THE BRAQUING OF DETOURING SHUTTERS OF AN AIRCRAFT IN FLIGHT |
US7577501B2 (en) | 2004-02-26 | 2009-08-18 | The Boeing Company | Methods and systems for automatically tracking information during flight |
US7357358B2 (en) | 2004-02-27 | 2008-04-15 | The Boeing Company | Aircraft leading edge device systems and corresponding sizing methods |
US7751947B2 (en) | 2004-03-31 | 2010-07-06 | The Boeing Company | Methods and systems for displaying assistance messages to aircraft operators |
US7418319B2 (en) | 2004-03-31 | 2008-08-26 | The Boeing Company | Systems and methods for handling the display and receipt of aircraft control information |
US7321318B2 (en) | 2004-03-31 | 2008-01-22 | The Boeing Company | Methods and systems for controlling the display of information at an aircraft flight deck |
US20050242234A1 (en) * | 2004-04-29 | 2005-11-03 | The Boeing Company | Lifters, methods of flight control and maneuver load alleviation |
US6978971B1 (en) | 2004-06-15 | 2005-12-27 | The Boeing Company | Methods and apparatuses for controlling airflow proximate to engine/airfoil systems |
US7007889B2 (en) * | 2004-06-15 | 2006-03-07 | Richard Charron | Flexible airfoils and method |
US7270305B2 (en) * | 2004-06-15 | 2007-09-18 | The Boeing Company | Aircraft leading edge apparatuses and corresponding methods |
DE102004040313B4 (en) * | 2004-08-19 | 2008-02-21 | Airbus Deutschland Gmbh | System for adjusting the spanwise load distribution of a wing |
US7494094B2 (en) * | 2004-09-08 | 2009-02-24 | The Boeing Company | Aircraft wing systems for providing differential motion to deployable lift devices |
US7264206B2 (en) | 2004-09-30 | 2007-09-04 | The Boeing Company | Leading edge flap apparatuses and associated methods |
DE102004063018B4 (en) | 2004-12-22 | 2007-08-02 | Airbus Deutschland Gmbh | Device for monitoring pivotable flaps on aircraft wings |
US7322547B2 (en) | 2005-01-31 | 2008-01-29 | The Boeing Company | Aerospace vehicle leading edge slat devices and corresponding methods |
US7338018B2 (en) | 2005-02-04 | 2008-03-04 | The Boeing Company | Systems and methods for controlling aircraft flaps and spoilers |
DE102005016639B4 (en) | 2005-04-11 | 2010-12-02 | Eads Deutschland Gmbh | Wing with extendable aerodynamic wing flaps, in particular lift flaps |
US7309043B2 (en) | 2005-04-27 | 2007-12-18 | The Boeing Company | Actuation device positioning systems and associated methods, including aircraft spoiler droop systems |
US7300021B2 (en) | 2005-05-20 | 2007-11-27 | The Boeing Company | Aerospace vehicle fairing systems and associated methods |
US7500641B2 (en) * | 2005-08-10 | 2009-03-10 | The Boeing Company | Aerospace vehicle flow body systems and associated methods |
US7611099B2 (en) | 2005-09-07 | 2009-11-03 | The Boeing Company | Seal assemblies for use with drooped spoilers and other control surfaces on aircraft |
US7708231B2 (en) | 2005-11-21 | 2010-05-04 | The Boeing Company | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
US7475854B2 (en) | 2005-11-21 | 2009-01-13 | The Boeing Company | Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods |
-
2005
- 2005-02-04 US US11/051,738 patent/US7338018B2/en active Active
-
2006
- 2006-02-03 DE DE602006014253T patent/DE602006014253D1/en active Active
- 2006-02-03 CN CNB2006800041310A patent/CN100500510C/en not_active Expired - Fee Related
- 2006-02-03 CA CA2706676A patent/CA2706676C/en active Active
- 2006-02-03 JP JP2007554252A patent/JP5201997B2/en not_active Expired - Fee Related
- 2006-02-03 EP EP06734316.0A patent/EP1843943B2/en not_active Not-in-force
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- 2006-02-03 CA CA2593915A patent/CA2593915C/en active Active
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EP1843943B1 (en) | 2010-05-12 |
DE602006014253D1 (en) | 2010-06-24 |
US20100286849A1 (en) | 2010-11-11 |
US20060175468A1 (en) | 2006-08-10 |
CA2593915C (en) | 2010-09-07 |
WO2006084157A2 (en) | 2006-08-10 |
CN101115655A (en) | 2008-01-30 |
CA2706676C (en) | 2014-04-15 |
WO2006084157A3 (en) | 2007-04-12 |
US7891611B2 (en) | 2011-02-22 |
CA2706676A1 (en) | 2006-08-10 |
ATE467555T1 (en) | 2010-05-15 |
EP1843943B2 (en) | 2017-02-22 |
CN100500510C (en) | 2009-06-17 |
US7338018B2 (en) | 2008-03-04 |
EP1843943A2 (en) | 2007-10-17 |
JP2008529871A (en) | 2008-08-07 |
JP5201997B2 (en) | 2013-06-05 |
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