Variable Gap Type, E.g., "fowler Flap" Patents (Class 244/216)
-
Patent number: 9846432Abstract: An aircraft includes a wing. The wing includes an aileron pivotally connected to a trailing edge of the wing, and a Lam aileron pivotally connected to the trailing edge of the wing. The aircraft includes a motor connected to the Lam aileron and configured to rotate the Lam aileron. The aircraft includes a controller configured to detect a deflection of the aileron from a neutral position, calculate a target deflection for the Lam aileron using the deflection of the aileron, and cause the motor to rotate the Lam aileron to the target deflection.Type: GrantFiled: July 25, 2014Date of Patent: December 19, 2017Assignee: Lam Aviation, Inc.Inventors: Michael Lam, Greg Cole
-
Patent number: 9840320Abstract: A bell crank mechanism is configured to at least indirectly link movement of an aircraft wing spoiler-like hinge panel to the movement of a primary flight control device on an aircraft wing trailing edge. The aircraft wing is configured to be fixed to and to extend from an aircraft fuselage, the wing including a leading edge and a trailing edge. The primary flight control device is attached to the trailing edge, and any movement of the control device is directly subject to an aircraft input controller by a linear actuator. The moveable aerodynamic hinge panel, a secondary control device, is situated proximally to the primary flight control device, and the hinge panel is separately attached to the trailing edge. The bell crank mechanism slaves any hinge panel motion to movements of the primary control device.Type: GrantFiled: December 19, 2014Date of Patent: December 12, 2017Assignee: The Boeing CompanyInventors: Matthew D M Fevergeon, Jan A. Kordel
-
Patent number: 9815504Abstract: The present invention concerns an improved flow control device for a vehicle (1), especially for a truck or small van, that comprises at least one air deflector blade (10, 12), which can be installed in an operating position as an extension of the contour on a rear vehicle edge (52), which forms an air deflector area and which is installed tiltably around a swivel axis by means of an adjustment unit between the operating position (I) and a stowing position (II). The present invention further concerns a vehicle (1) that is equipped with the flow control device.Type: GrantFiled: February 7, 2014Date of Patent: November 14, 2017Assignee: AIRNMOTION GMBHInventors: Rainer M. Buffo, Ingo Martin, Rene Tuxhorn
-
Patent number: 9751615Abstract: An aircraft wing comprising a main wing, a high lift element, and at least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprises a track element provided on the main wing, and having a first support surface and a first track side wall, an actuator device, a drive rod, and a carriage device connected to the high lift element and having an engagement portion. The object is to provide an aircraft wing which is configured in such a manner that when the connecting system for connecting the high lift element to the main wing fails the high lift element can still be held in a possibly unskewed position.Type: GrantFiled: April 29, 2015Date of Patent: September 5, 2017Assignee: Airbus Operations GmbHInventor: Martin Recksiek
-
Patent number: 9709026Abstract: An airfoil for an airborne wind turbine including a main wing adapted for attachment to an electrically conductive tether, a pivotable trailing element positioned behind the main wing, wherein a chord line of the airfoil has a length that is measured from the leading edge of the main wing to a trailing edge of the trailing element, wherein when the main wing and trailing element are positioned in a first flying position, a slot gap exists between a trailing edge of the main wing and the leading edge of the trailing element, wherein the main wing has a thickness that is 15-28% of the length of the chord line; and wherein a spar bulge exists in the main wing such that 15-25% of the overall length of the chord line has a thickness that is 95% or more of a maximum thickness of the main wing.Type: GrantFiled: December 31, 2013Date of Patent: July 18, 2017Assignee: X Development LLCInventor: Damon Vander Lind
-
Patent number: 9592904Abstract: A drive mechanism for deforming a skin of a deformable structural component of a fluid-dynamic flow body to provide a space-saving drive concept for large deformations under great loads. The drive mechanism comprises a linearly movably driven linear movement unit, and a transmission element configured to translate linear movement of the linear movement unit into rotary movement of a rotatably mounted load introduction device of the structural component to introduce a deformation force onto the skin.Type: GrantFiled: December 11, 2014Date of Patent: March 14, 2017Assignee: AIRBUS DEFENCE AND SPACE GMBHInventor: Johannes Kirn
-
Patent number: 9580168Abstract: A primary flight control device for an aircraft, such as a flaperon attached to an aircraft wing, utilizes independent yet interactive airgap control systems designed to avoid weight penalties associated with conventionally used cam and track systems. An actuator directly controls movements of the flaperon; the flaperon motion is then used to slave separate movements of secondary flight control devices, such as a flaperon hinge panel and a cove lip door, to various positions of the flaperon for indirect control of aerodynamic air gaps during flight. The use of a bell crank for indirectly slaving the flaperon hinge panel movements to the flaperon avoids conventionally used cam and track systems. Although the cove lip door utilizes a separate linkage system, the bell crank and cove lip door linkage systems work in conjunction to assure desired aerodynamic airflows over the aircraft wing and flaperon structures.Type: GrantFiled: December 19, 2014Date of Patent: February 28, 2017Assignee: The Boeing CompanyInventors: Matthew D M Fevergeon, Jan A. Kordel, Victor Liu
-
Patent number: 9567063Abstract: Flap track fairing systems are split into a forward immovably fixed portion and an aft movable portion. The fixed forward portion is immovably attached to the main wing structure of an aircraft while the movable aft portion is attached either to the movable components of the flap deployment mechanism or to the lower surface of the flap. A separation line between the forward movable portion and the aft fixed portion is provided such that the movable portion does not interfere structurally with the flap fairing structure during a flap extension/retraction cycle. An airflow deflector is positioned near a forward separation edge of the aft fairing portion so as to be positioned within a gap defined between the forward edge of the aft fairing portion and a rearward edge of the forward fairing portion when the flap is in the deployed configuration thereof to thereby deflect airflow away from the interior space of the fairing.Type: GrantFiled: May 21, 2015Date of Patent: February 14, 2017Assignee: EMBRAER S.A.Inventors: Alysson Kennerly Colaciti, Leandro Guilherme Crenite Simões, Alexandre Viana Ferreira, Micael Gianini Valle do Carmo, Mário Triches, Jr., Vinicius Losada Gouveia
-
Patent number: 9555875Abstract: The present disclosure pertains to an actuation mechanism for a flap with aileron functionality, including a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion, and wherein the linear-motion bearing is rotatably attachable at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point. The present disclosure further pertains to an aircraft flap with such an actuation mechanism and an aircraft having an aircraft flap.Type: GrantFiled: May 23, 2014Date of Patent: January 31, 2017Assignee: Airbus Operations GmbHInventor: Alexander Burchard
-
Patent number: 9452823Abstract: A lift flap bearing apparatus is improved with respect to aerodynamics, construction space and assembly, for guiding and adjusting a first lift flap and a second lift flap. The lift flap bearing apparatus comprises a first guiding device for guiding the first lift flap and a second guiding device for guiding the second lift flap. The first and the second guiding devices each have a first curved guide rail and a second curved guide rail.Type: GrantFiled: August 21, 2012Date of Patent: September 27, 2016Assignees: EADS Deutschland GmbH, Airbus Operations GmbHInventors: Tamas Havar, Juan Perez-Sanchez, Tobias Ender, Oliver Seack
-
Patent number: 9446835Abstract: A wing including a spar, a box shaped sleeve in the spar running substantially the entire length of the wing, a skin affixed to spar and to the corners of the sleeve and shaped to from a leading edge and trailing edge of the wing, a spoiler affixed to an upper surface of the trailing edge of the spar, a vent affixed to the lower surface of the trailing edge of the spar below the spoiler.Type: GrantFiled: January 14, 2014Date of Patent: September 20, 2016Assignee: OTTO AVIATION GROUPInventor: William M. Otto
-
Patent number: 9284034Abstract: A wing flap control system on a wing comprising at least two control plates having an opening sized to accommodate a drive shaft, a drive shaft that engages each of the openings in each of the plurality of plates, a sprocket rotatively affixed the drive shaft with the drive shaft penetrating the other control plate, at least two idler sprockets between the control plates, a chain wrapped around the sprocket and idler sprockets, a support arm rotatively coupled to the chain by a chain shoe and to a foreflap, a link arm rotatively coupled to the support arm and to a flap, where movement of the drive shaft causes the foreflap and flap to extend and retract to increase or decrease the surface area of the wing.Type: GrantFiled: January 14, 2014Date of Patent: March 15, 2016Assignee: OTTO AVIATION GROUPInventor: William M. Otto
-
Patent number: 9242719Abstract: A wing of an aircraft or spacecraft, the wing including at least a movable flow body, the wing including a movable support member, which is connected to the flow body, for rotating the flow body on the wing, the wing including a flow body control element, the flow body control element being fixed to the wing in a first point and the support member in a second point, the two points of the flow body control element and of the support member forming an axis, the flow body control element being formed at a predetermined angle to the axis and the flow body control element guiding the flow body in a predetermined plane about this axis.Type: GrantFiled: March 31, 2010Date of Patent: January 26, 2016Assignee: AIRBUS OPERATIONS GmbHInventor: Mark Heintjes
-
Patent number: 9233755Abstract: Improved supersonic laminar flow wing structure, on a supersonic aircraft, having strake extending forwardly of the wing inboard extent, and reversed fillet at strake junction with the wing leading edge. Plain and split flap structures may also be provided at each laminar flow wing.Type: GrantFiled: May 18, 2011Date of Patent: January 12, 2016Assignee: Aerion CorporationInventors: James D. Chase, Michael Henderson, Sturdza Peter
-
Patent number: 9227722Abstract: A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap support beam including an aerodynamic fairing; and a drive unit including a universal support structure which rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing.Type: GrantFiled: October 3, 2012Date of Patent: January 5, 2016Assignee: AIRBUS OPERATIONS LIMITEDInventor: Mochamad-Agoes Soenarjo
-
Patent number: 9187171Abstract: A linkage guides a flexible cable between two structures. The linkage includes a proximal arm with a proximal pivot joint for coupling the proximal arm to a first one of the two structures; and a distal arm which is coupled to the proximal arm by one or more intermediate pivot joints. The distal arm is shaped to follow a three-dimensional curve along a majority of its length. Shaping the distal arm to form a three-dimensional curve along a majority of its length enables the distal arm to pass through a relatively small aperture as the linkage is adjusted between its retracted and extended positions. It also enables the proximal arm to move in a locus of movement which does not interfere with other system components. The linkage can be used to guide a flexible cable between any two structures, for instance a fixed aircraft wing and a slat.Type: GrantFiled: July 5, 2011Date of Patent: November 17, 2015Assignee: ULTRA ELECTRONICS LIMITEDInventors: Mark Anthony Salthouse, Christopher Biggadike, Graeme John Dutton
-
Patent number: 9079652Abstract: A droop panel linkage for aircraft includes a lever arm, a main lever, a main tube and at least one drive strut. The lever arm is pivotally attached at a first end to a flap and is pivotally connected at a second end to a first end of the main lever. A second end of the main lever is provided with a first engagement element for engaging with a second engagement element incorporated into or associated with the main tube. The main tube is pivotally connected to a proximal end of the drive strut. A distal end of the drive strut is pivotally attached to the droop panel.Type: GrantFiled: May 21, 2010Date of Patent: July 14, 2015Assignee: AIRBUS S.A.S.Inventor: Haikou Yue
-
Patent number: 9061753Abstract: A hinged panel operation system is provided having a mechanical linkage assembly coupled between a fixed structure and a trailing edge device. The mechanical linkage assembly has a first link operatively coupled to the trailing edge device, a second link pivotably connected at a first end to the first link and pivotably connected at a second end to a third link, and an eccentric attachment connecting the second link to the third link. The hinged panel operation system further has a hinged panel positioned forward of the trailing edge device and being operatively coupled to the mechanical linkage assembly. The hinged panel is movable by the mechanical linkage assembly between a stowed position and a drooped position. The mechanical linkage assembly provides a load path to the hinged panel.Type: GrantFiled: November 29, 2012Date of Patent: June 23, 2015Assignee: The Boeing CompanyInventors: Kevin W. Beyer, Seiya Sakurai, Martin F. Stephenson
-
Patent number: 8931733Abstract: An aerodynamic body that can be adjusted relative to a main wing of an aircraft by an adjusting device is provided. A gap between the aerodynamic body and another aerodynamic body or a component of the fuselage or the main wing is formed on one lateral end and said and the gap is variable due to the adjustability of the aerodynamic body. The body features a gap bridge-over device with a shell part that extends along the gap and overlaps the outer shell of the aerodynamic body in the wingspread direction on the front side thereof so that the shell part can be telescopically moved relative to this aerodynamic body in the wingspread direction. An airfoil for an aircraft with a main wing and a plurality of aerodynamic bodies that are arranged adjacent to one another transverse to the chord direction is also provided.Type: GrantFiled: April 23, 2009Date of Patent: January 13, 2015Assignee: Airbus Operations GmbHInventor: Werner Dyckrup
-
Patent number: 8899528Abstract: A blade seal comprises a flexible member having a relatively thick edge opposite a relatively thin edge, and an actuator at least partially embedded in the flexible member for actively deflecting the thin edge with respect to the thick edge upon activation of the actuator. The blade seal may be fixed to an aerodynamic trailing edge of either a fixed aerofoil portion or a flight control surface of an aerofoil for sealing between the fixed aerofoil portion and the flight control surface. Also, a method of sealing an aerofoil using the blade seal.Type: GrantFiled: May 14, 2010Date of Patent: December 2, 2014Assignee: Airbus Operations LimitedInventor: Christopher Coconnier
-
Patent number: 8844878Abstract: A high lift system for an aircraft includes: a main wing, a flap disposed on the main wing of the aircraft that can be adjusted between a retracted position and several extended positions relative to the main wing by way of a flap actuating mechanism and a drive device, a carrier part disposed on the main wing to which the flap actuating mechanism is coupled and relative to which the flap actuating mechanism for adjusting the flap can be moved, where the carrier part is disposed on the main wing by way of a bearing device including an adjusting device with which the orientation of the carrier part relative to the orientation of the main wing can be adjusted.Type: GrantFiled: August 6, 2008Date of Patent: September 30, 2014Assignee: Airbus Operations GmbHInventors: Timo Voss, Joachim Loerke
-
Patent number: 8763958Abstract: A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise.Type: GrantFiled: April 18, 2012Date of Patent: July 1, 2014Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Travis L. Turner, Mehdi R. Khorrami, David P. Lockard, Martin J. McKenney, Raymond D. Atherley, Reggie T. Kidd
-
Patent number: 8684316Abstract: A trailing edge flap mechanism incorporates a support beam, a flap carrier beam supporting an aerodynamic flap, a first link interconnecting a first and second rotation points and a second link interconnecting third and fourth rotation points. The support beam has a ground connection on a first fixed axis of rotation. A connecting link has a ground connection on a second fixed axis of rotation and is connected to the first link intermediate the first and second rotation points. An actuator is connected with a drive link pivotally engaged to the first link for initial forward and aft movement of a nose profile of the Fowler flap substantially parallel to the wing lower surface with extending aft movement providing a rapidly changing angle of the flap with respect to the wing upper surface.Type: GrantFiled: September 23, 2011Date of Patent: April 1, 2014Assignee: The Boeing CompanyInventors: Seiya Sakurai, James M. Wheaton, Stephen J. Fox, Sharon Xiangdong Che
-
Patent number: 8613409Abstract: A trailing edge aerodynamic airfoil of a load-bearing aerodynamic surface of an aircraft of the crocodile type has two airfoil flaps, with each flap being integral in a forward section with a rotational shaft that determines the axis of rotation of the airfoil flap. In a position called the zero setting, the airfoil flaps are essentially joined and form a rear section of the load-bearing surface, and each airfoil flap is movable in translation independently of the other airfoil flap, relative to the load-bearing surface, with each flap being entrained in rotation relative to the load-bearing surface around its axis of rotation by the motion in translation. The ends of the rotational shaft have extensions guided by runners fastened to these ends and acting conjointly with racks fastened to the load-bearing surface.Type: GrantFiled: November 8, 2010Date of Patent: December 24, 2013Assignee: Airbus Operations (S.A.S.)Inventors: Olivier Cazals, Thierry Druot
-
Patent number: 8584991Abstract: A wing, having an adjustable flap that can be moved between a retracted and an extended setting is provided, as well as a gap-covering device, with an adjustment lever and a gap-covering flap arranged on the latter with a flow surface. The adjustment lever with the gap-covering flap is pre-loaded by means of a pre-loading device into a first setting, in which the gap-covering flap is located in the interior of the wing. The adjustable flap and the adjustment lever with the gap-covering flap are mechanically coupled such that as the adjustable flap moves into its retracted setting, a movement of the adjustment lever takes place against the pre-load effected by the pre-loading device, into a second setting. The flow surface of the gap-covering flap in the second setting of the adjustment lever runs between the upper side of the retracted adjustable flap and the wing flow surface.Type: GrantFiled: November 10, 2009Date of Patent: November 19, 2013Assignee: Airbus Operations GmbHInventors: Bernhard Schlipf, Chris Payne, Markus Gibbert, Tom Dostmann
-
Patent number: 8567727Abstract: A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. Also, a method of operating the trailing edge flap arrangement.Type: GrantFiled: November 4, 2010Date of Patent: October 29, 2013Assignee: Airbus Operations LimitedInventor: Stuart Morris
-
Patent number: 8534611Abstract: A method and apparatus for managing a flight control surface system. A leading edge section on a wing of an aircraft is extended into a deployed position. A deformable section connects the leading edge section to a trailing section. The deformable section changes from a deformed shape to an original shape when the leading edge section is moved into the deployed position. The leading edge section on the wing is moved from the deployed position to an undeployed position. The deformable section changes to the deformed shape inside of the wing.Type: GrantFiled: July 17, 2009Date of Patent: September 17, 2013Assignee: The Boeing CompanyInventors: Dale M. Pitt, Nicholas Stephen Eckstein
-
Patent number: 8524022Abstract: A method of manufacturing a structure, the method comprising: forming a panel assembly by bonding a stack of thickness control plies of composite material to a laminar composite panel, the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite the first edge, and a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge; measuring the thickness of the laminate composite panel or the panel assembly; controlling the number of thickness control plies in accordance with the measured thickness; attaching a first component to the panel assembly, the first component having a surface which engages the laminar composite panel and a ramp which engages the ramp in the stack of thickness control plies; and attaching the laminar composite panel at or near its edge to a further component.Type: GrantFiled: June 23, 2010Date of Patent: September 3, 2013Assignee: Airbus Operations LimitedInventors: Alex Iliopoulos, John Flood
-
Publication number: 20130075537Abstract: A trailing edge flap mechanism incorporates a support beam, a flap carrier beam supporting an aerodynamic flap, a first link interconnecting a first and second rotation points and a second link interconnecting third and fourth rotation points. The support beam has a ground connection on a first fixed axis of rotation. A connecting link has a ground connection on a second fixed axis of rotation and is connected to the first link intermediate the first and second rotation points. An actuator is connected with a drive link pivotally engaged to the first link for initial forward and aft movement of a nose profile of the Fowler flap substantially parallel to the wing lower surface with extending aft movement providing a rapidly changing angle of the flap with respect to the wing upper surface.Type: ApplicationFiled: September 23, 2011Publication date: March 28, 2013Applicant: THE BOEING COMPANYInventors: Seiya Sakurai, James M. Wheaton, Stephen J. Fox, Sharon Xiangdong Che
-
Patent number: 8393568Abstract: A roller clutch assembly for use in an actuator is provided that includes a roller cage and at least one roller. A lubricating medium at least partially surrounds the roller cage and the roller. The roller cage includes at least one wiper configured to move the lubricating medium toward its functional location adjacent the rollers. An aircraft actuator for controlling movement of an aircraft flight control surface is also provided that includes a ball nut and a ball screw operatively connected to the flight control surface. A one-way roller clutch is operatively connected to the ball nut and substantially prevents rotation of the ball nut in a first direction in response to a compressive force on the ball screw. A roller clutch assembly according to the present invention is positioned between the ball nut and the one-way roller clutch.Type: GrantFiled: April 8, 2009Date of Patent: March 12, 2013Assignee: Eaton CorporationInventors: William A. Maresko, Donald R. Cavalier, Aaron M. Klap
-
Patent number: 8336829Abstract: An aircraft wing trailing edge control surface including a trailing edge flap adjustable to different positions, a sealing flap on the upper side between the wing and the flap, and a ventilation flap on the underside between the wing and the flap. The flap is adjustable downward through positive positions and upward through negative positions. The wing profile is closed on the upper side by the sealing flap and the underside by the ventilation flap when the flap is used as a control flap and adjusted between negative and low positive positions. The ventilation flap releases air flow from the wing underside to the upper side of the flap and the sealing flap is retracted to release an outflow of air from the upper side of the flap when the flap is used for increasing lift and the flap is adjusted between low and high positive positions.Type: GrantFiled: September 18, 2006Date of Patent: December 25, 2012Assignee: Airbus Operations GmbHInventors: Daniel Reckzeh, Bernhard Schlipf, Luc Andreani, Mark Sutcliffe
-
Patent number: 8292235Abstract: A method of operating an aircraft wing assembly, the assembly comprising a main wing element with a leading edge; a slat on the leading edge of the main wing element; and a seal member. The assembly is placed in a first configuration during take off in which the slat is in a deployed position with a slot between the slat and the main wing element, and the seal member is in a deployed position in which it seals the slot. During cruise both the slat and the seal member are retracted. During landing the slat is deployed fully with a slot between the slat and the main wing element, but the seal member is kept in its retracted position so that the slot remains open.Type: GrantFiled: October 29, 2009Date of Patent: October 23, 2012Assignee: Airbus Operations LimitedInventors: Timothy David Wollaston, James Michael Ribeiro
-
Patent number: 8292236Abstract: A seal for sealing a gap between a first (252) and a second (207) component of an aircraft flight surface which has a first seal body (222) having a first sealing portion (246) arranged to seal against the first component, wherein the first seal body is movably mounted to the second component so as to seal at least part of the gap during relative movement of the first and second components. A seal is also provided with components movable relative to each other.Type: GrantFiled: March 17, 2009Date of Patent: October 23, 2012Assignee: Airbus Operations LimitedInventor: Eric Wildman
-
Patent number: 8282038Abstract: A bi-directional flight control surface mechanism comprises a fixed part V of a vertical stabilizer having leading and trailing edges and a rudder having leading and trailing edges. The rudder is mounted relative to the fixed part of the vertical stabilizer so that the trailing edge of the fixed structure is adjacent the leading edge of the rudder. The rudder is movable from a neutral position in which the rudder lies in line with the fixed part of the vertical stabilizer to define a notional centerline to first and second angled positions in which the rudder is angled relative to the fixed part of the vertical stabilizer at a non-zero angle on one or other side of the notional centerline. An actuator is provided to drive the rudder relative to the fixed part of the vertical stabilizer so as to vary the distance between said part of the trailing edge of the fixed part of the vertical stabilizer and the leading edge of the rudder.Type: GrantFiled: July 31, 2009Date of Patent: October 9, 2012Assignee: Airbus Operations LimitedInventors: Keith MacGregor, David Croston
-
Patent number: 8245982Abstract: A wing, comprising a structure, an outer skin, and a leading edge device comprising a moveable body with a leading and a trailing edge and a support and actuation mechanism for attaching said moveable body to a structure of a wing and guiding a substantially circular motion of said moveable body, around a hinge line, between a retracted position and at least one deployed position. Said leading edge device further comprises at least one guiding device comprising a track and a follower with a roller. The track follows a substantially circular arc substantially centered on the hinge line. The roller is arranged to be guided by the track and hold down said moveable aerodynamic surface so as to substantially restrict lift-off of its trailing edge from the outer skin of the wing.Type: GrantFiled: March 7, 2008Date of Patent: August 21, 2012Assignee: Asco IndustriesInventors: Alexandre Vormezeele, Christophe Cnop, Dietmar Bloemen, Eoin O'Beirne
-
Publication number: 20120153086Abstract: A system is provided for reducing aeroacoustic noise generated by an aircraft having wings equipped with trailing-edge flaps. The system includes a plurality of elastically deformable structures. Each structure is coupled to and along one of the side edges of one of the trailing-edge flaps, and is coupled to a portion of one of the wings that is adjacent to the one of the side edges. The structures elastically deform when the trailing-edge flaps are deployed away from the wings.Type: ApplicationFiled: December 15, 2011Publication date: June 21, 2012Applicant: United States of America as represented by the Administrator of the National Aeronautics and SpacInventors: Mehdi R. Khorrami, David P. Lockard, James B. Moore, Ji Su, Travis L. Turner, John C. Lin, Karen M. Taminger, Seun K. Kahng, Scott A. Verden
-
Patent number: 8157208Abstract: A landing flap drive system, in one example, includes a first drive motor for operating a landing flap. In this arrangement, the landing flap drive system is integrated in a track of the landing flap such that final assembly and integration of the system are facilitated to a significant extent.Type: GrantFiled: April 12, 2006Date of Patent: April 17, 2012Assignees: Airbus Deutchland GmbH, Deutsches Zentrum Fuer Luft—und Raumfahrt E.V. (DLR)Inventors: Martin Recksiek, Christoph Giebeler, Ina Brueckner
-
Publication number: 20120061524Abstract: A wing is provided, including a high-lift flap arranged on the wing such that it is movable by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the wing and adjustable by means of a drive device. Each adjustment mechanism includes a first adjustment lever, articulated on a main wing surface via a first pivotal articulation, with the formation of a first rotation axis; a second adjustment lever, articulated on the high-lift flap via a second pivotal articulation, with the formation of a second rotation axis; and a central articulation, linking together the first and the second adjustment levers, with the formation of a third rotation axis. An intermediate articulated part is arranged on at least one of the adjustment mechanisms for coupling the first adjustment lever and the main wing surface, or for coupling the second adjustment lever and the high-lift flap.Type: ApplicationFiled: March 29, 2010Publication date: March 15, 2012Applicant: AIRBUS OPERATIONS GMBHInventors: Bernhard Schlipf, Xavier Hue
-
Patent number: 8109473Abstract: A slotted aerofoil configuration is provided in which the leading element thereof is contoured to provide mild stall characteristics. A wing based partially or fully on such an aerofoil, an air vehicle including such wings, and a method for designing an aerofoil are also disclosed.Type: GrantFiled: May 29, 2007Date of Patent: February 7, 2012Assignee: Israel Aerospace Industries Ltd.Inventors: Michael Shepshelovich, Alex Nagel
-
Publication number: 20120018588Abstract: Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.Type: ApplicationFiled: October 3, 2011Publication date: January 26, 2012Applicant: THE BOEING COMPANYInventors: Douglas S. Lacy, Jan A. Kordel, John V. Dovey, Michael A. Balzer, Seiya Sakurai, Neal V. Huynh
-
Patent number: 8066228Abstract: A device for adjusting the lift characteristics of an aircraft with a high lift device that is movably attachable to a wing element and that includes at least one slot covering device, where the at least one slot covering device, is movably attachable to the wing element. The slot covering device is designed to regulate the size of a slot between the wing element and the high lift device.Type: GrantFiled: April 7, 2006Date of Patent: November 29, 2011Assignee: Airbus Deutschland GmbHInventors: Klaus Bender, Ole Boettger
-
Publication number: 20110168850Abstract: A two element aerofoil, and wing element based thereon, is provided, including a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil. A gap is provided between the primary aerofoil element and the secondary aerofoil element. The primary aerofoil element has at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of the secondary aerofoil element that is configured for minimizing or avoiding accretion of contaminant on the secondary aerofoil element when subjected to an airflow that includes the contaminant, at least at one design set of conditions. A method for designing a two element aerofoil is also provided.Type: ApplicationFiled: September 16, 2009Publication date: July 14, 2011Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.Inventors: Michael Shepshelovich, Danny Abramov
-
Publication number: 20110127385Abstract: A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements moveable collectively between a retracted and an extended position, wherein at least the leading flap element is rotatable about its axis independently of the collective array movement. Also, a method of operating the trailing edge flap arrangement, comprising collectively moving the array of flap elements between a retracted and an extended position, and rotating at least the leading flap element about its axis independently of the collective array movement. The flap arrangement can be deployed as a single slotted flap which can be vented to further improve lift performance. The flap arrangement can also be operated to provide variable camber across the performance envelope.Type: ApplicationFiled: November 4, 2010Publication date: June 2, 2011Applicant: AIRBUS OPERATIONS LIMITEDInventor: Stuart MORRIS
-
Publication number: 20110127386Abstract: A single slotted trailing edge flap arrangement for an aircraft wing, comprising a main flap element and an auxiliary flap element sealed to and supported by the main flap element for movement between a retracted and an extended position relative to the main flap element so as to vary the planform area of the flap. The auxiliary flap element remains sealed to the main flap element when in its extended position, and movement of the auxiliary flap element relative to the main flap element is solely translational. The auxiliary flap element may be translationally deployed from the main flap element by sliding the auxiliary flap element out from the underside of the main flap element. Also, a method of operating the flap arrangement.Type: ApplicationFiled: November 4, 2010Publication date: June 2, 2011Applicant: AIRBUS OPERATIONS LIMITEDInventor: Stuart MORRIS
-
Publication number: 20110127387Abstract: A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. Also, a method of operating the trailing edge flap arrangement.Type: ApplicationFiled: November 4, 2010Publication date: June 2, 2011Applicant: AIRBUS OPERATIONS LIMITEDInventor: Stuart MORRIS
-
Patent number: 7766281Abstract: A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state.Type: GrantFiled: November 9, 2005Date of Patent: August 3, 2010Assignee: Airbus Deutschland GmbHInventors: Thomas Lorkowski, Boris Grohmann
-
Patent number: 7744040Abstract: Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.Type: GrantFiled: November 4, 2008Date of Patent: June 29, 2010Assignee: The Boeing CompanyInventors: Douglas S. Lacy, Kevin W. Beyer, Stephen T. Brown, Paul W. Dees, Neal V. Huynh, Jan A. Kordel, Clayton A. Prow, Seiya Sakurai
-
Patent number: 7661630Abstract: A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length. The outboard flap portion is adapted to translate between a first and a second position to create a functional slot between a bottom surface of the flap member leading part and a bottom surface of the airfoil trailing part to draw a portion of higher pressure air from the bottom surface of the airfoil through the functional slot to distribute the higher pressure air over a top surface of the outboard flap portion.Type: GrantFiled: March 13, 2008Date of Patent: February 16, 2010Inventor: John Libby
-
Publication number: 20100006707Abstract: An aircraft wing trailing edge control surface including a trailing edge flap adjustable to different positions, a sealing flap on the upper side between the wing and the flap, and a ventilation flap on the underside between the wing and the flap. The flap is adjustable downward through positive positions and upward through negative positions. The wing profile is closed on the upper side by the sealing flap and the underside by the ventilation flap when the flap is used as a control flap and adjusted between negative and low positive positions. The ventilation flap releases air flow from the wing underside to the upper side of the flap and the sealing flap is retracted to release an outflow of air from the upper side of the flap when the flap is used for increasing lift and the flap is adjusted between low and high positive positions.Type: ApplicationFiled: September 18, 2006Publication date: January 14, 2010Applicant: Airbus Deutschland GmbHInventors: Daniel Reckzeh, Bernhard Schlipf, Luc Andreani, Mark Sutcliffe
-
Patent number: RE44313Abstract: Slotted cruise airfoil technology allows production of a substantially unswept wing that achieves the same cruise speed as today's conventional jet airplanes with higher sweep. This technology allows the wing boundary layer to negotiate a strong recovery gradient closer to the wing trailing edge. The result is about a cruise speed of Mach=0.78, but with a straight wing. It also means that for the same lift, the super velocities over the top of the wing can be lower. With very low sweep and this type of cruise pressure distribution, natural laminar flow will be obtained. In addition, heat is transferred from the leading edge of the wing and of the main flap to increase the extent of the natural laminar flow. The slotted cruise wing airfoil allows modularization of the wing and the body for a family of airplanes. The unsweeping of the wing significantly changes the manufacturing processes, reduces manufacturing costs and flow time from detail part fabrication to airplane delivery.Type: GrantFiled: October 22, 1997Date of Patent: June 25, 2013Assignee: The Boeing CompanyInventors: Robert H. Kelley-Wickemeyer, Peter Z. Anast, James Douglas McLean, Hilda Seidel