Variable Patents (Class 244/201)
  • Patent number: 10669006
    Abstract: An aircraft (102) including a wing (101), having a fixed wing (105) with a wing tip device (103) moveably mounted at the outer end thereof. The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. The wing tip device (103) and the fixed wing (105) are separated along an oblique primary cut plane (113). The wing tip device (103) and the fixed wing (105) meet along an interfacing cut line (135). The interfacing cut line (135) comprises a first length (137) offset from the primary cut plane (113) in a first direction; a second length (141) offset from the primary cut plane (113) in a second direction, opposite to the first direction; and a transition section (139) over which the interfacing cut line (135) transitions from the first length to the second length.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: June 2, 2020
    Assignee: Airbus Operations Limited
    Inventor: Benjamin Bishop
  • Patent number: 10421529
    Abstract: An aircraft including a wing 10 having a fixed wing 12 and a swing wing tip device 14 pivotably mounted about a pivot 16 at the tip of the fixed wing, wherein the swing wing tip device 14 is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations, where the span of the aircraft wing is reduced. The swing wing tip device 14 includes a receiving portion 48 arranged such that in the ground configuration, portions of the upper wing skin and lower wing skin of the fixed wing which are exposed in the flight configuration are at least partially received within the receiving portion 48 of the swing wing 14.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: September 24, 2019
    Assignee: Airbus Operations Limited
    Inventors: Stefan Napier, Robert Hart, Matthew Harding, Nick Livings
  • Patent number: 10414484
    Abstract: An aircraft (40). The aircraft comprises a plurality of propellers (46) mounted to wings (44). Each propeller comprises at least one blade (72, 74) coupled to a respective propeller cyclic actuator (78) configured to cyclically alter the pitch of the respective blade (72, 74) as the propeller rotates. The aircraft (40) is configured such that provision of cyclic pitch to the propeller (46) twists at least a portion of the wing (44) about a span of the wing (46) relative to the fuselage (42), to thereby adjust the local angle of incidence of the wing (46).
    Type: Grant
    Filed: September 15, 2015
    Date of Patent: September 17, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Matthew Moxon
  • Patent number: 10293914
    Abstract: An aerofoil for an aircraft includes an engine, a first lift body, and a second lift body which is arranged behind the first lift body in the direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil.
    Type: Grant
    Filed: April 22, 2016
    Date of Patent: May 21, 2019
    Assignee: Lilium GmbH
    Inventor: Daniel Wiegand
  • Patent number: 10132290
    Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.
    Type: Grant
    Filed: October 20, 2015
    Date of Patent: November 20, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Dmitry Floryovych Opaits, Seyed Gholamali Saddoughi, Grover Andrew Bennett, Matthew Patrick Boespflug, Stephen Bertram Johnson, Peggy Lynn Baehmann, Fulton Jose Lopez, Daniel Jason Erno, Robert Michael Zirin, Anurag Gupta
  • Patent number: 9714084
    Abstract: Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when the vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region there between and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle.
    Type: Grant
    Filed: November 8, 2013
    Date of Patent: July 25, 2017
    Assignee: Gulfstream Aerospace Corporation
    Inventors: Preston A. Henne, Donald C. Howe
  • Patent number: 9511848
    Abstract: A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid.
    Type: Grant
    Filed: October 12, 2012
    Date of Patent: December 6, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Martin Gerber, Freerk Syassen
  • Patent number: 9114884
    Abstract: An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).
    Type: Grant
    Filed: March 26, 2010
    Date of Patent: August 25, 2015
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Frédéric Chelin, Thierry Surply
  • Publication number: 20150097087
    Abstract: A swing wing tip system for an air vehicle is provided. The swing wing tip system has a swing wing tip assembly with an unfixed wing tip portion movably connected to a fixed wing portion of a wing. The swing wing tip assembly has a dual load path structure configured to transfer load from the unfixed wing tip portion to the fixed wing portion. The dual load path structure has dual wing skin plates and a rotation joint coupled between the dual wing skin plates and configured to rotationally couple the unfixed wing tip portion to the fixed wing portion. The rotation joint has a dual rotation pin element having a center rotation axis and dual rotation elements configured to rotate about the center rotation axis. The swing wing tip system has an actuator assembly coupled to the rotation joint and a controller system coupled to the actuator assembly.
    Type: Application
    Filed: October 6, 2013
    Publication date: April 9, 2015
    Applicant: The Boeing Company
    Inventors: Seiya Sakurai, Ryan W. Kosko, Gregory M. Santini
  • Patent number: 9002484
    Abstract: A system and method is described generally for producing surface deformations on a surface of a body. The system and method relate to a first surface being a surface of the body exposed to the fluid flow and at least one actuator affecting deformation of the first surface. A control system providing control commands to the at least one actuator is provided and a sensor providing environmental characteristic information to the control system is also provided.
    Type: Grant
    Filed: December 1, 2006
    Date of Patent: April 7, 2015
    Inventors: Roderick A. Hyde, Nathan P. Myhrvold, Lowell L. Wood, Jr., Alistair K. Chan, Clarence T. Tegreene
  • Patent number: 8973874
    Abstract: The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the outer end. The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle relative to the span direction. The leading edge comprises a backward sweep part between the kink and the outer end extending from the kink presenting an angle relative to the span direction. The top surface comprises a flow control means for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge.
    Type: Grant
    Filed: April 14, 2011
    Date of Patent: March 10, 2015
    Assignee: B.V. Green X
    Inventor: Robert Jan Musters
  • Publication number: 20140252156
    Abstract: A high-altitude unmanned stratosphere aerial vehicle includes a fuselage, wings, control surfaces, and a propulsion system including an engine and a propeller. Each wing has a plurality of hoses and wing spars extending in a direction perpendicularly to the longitudinal fuselage axis and are surrounded by a skin forming a wing covering that determines the cross-sectional contour of the wing, the cross-sectional contour forming a laminar flow airfoil that generates high lift when there is low flow resistance. At the free end facing away from the fuselage, each wing has a winglet extending transversely to the longitudinal wing axis. The winglet has a movable control surface, which allows an aerodynamic side force to be generated so as to bring the aerial vehicle to a banked position.
    Type: Application
    Filed: October 20, 2012
    Publication date: September 11, 2014
    Applicant: EADS Deutschland GmbH
    Inventors: Manfred Hiebl, Hans Wolfgang Pongratz
  • Patent number: 8827211
    Abstract: Systems, equipment, and methods to deposit energy to modify and control air flow, lift, and drag, in relation to air vehicles, and methods for seeding flow instabilities at the leading edges of control surfaces, primarily through shockwave generation through deposition of laser energy at a distance.
    Type: Grant
    Filed: October 23, 2008
    Date of Patent: September 9, 2014
    Inventor: Kevin Kremeyer
  • Patent number: 8783337
    Abstract: A system and method for producing surface deformations on a surface of a body. The system and method relate to changing the convective heat transfer coefficient for a surface. The system includes a first surface being a surface of a body exposed to a fluid flow and at least one actuator affecting deformation of the first surface. The system also includes a control system providing control commands to the at least one actuator, the control commands configured to change deformations on the first surface in order to change the convective heat transfer coefficient of the first surface. Further, the system includes a sensor providing environmental characteristic information to the control system.
    Type: Grant
    Filed: December 1, 2006
    Date of Patent: July 22, 2014
    Inventors: Roderick A. Hyde, Nathan P. Myhrvold, Lowell L. Wood, Jr., Alistair K. Chan, Clarence T. Tegreene
  • Patent number: 8708286
    Abstract: A rotation joint and methods for rotationally coupling a swing tip assembly to a fluid-dynamic body are presented. A rotation plate configured to couple to the swing tip assembly comprises a slide ring comprising an open center, an upper slide surface, an inner slide surface, and a lower slide surface. An upper joint plate is slidably coupled to the upper slide surface and the inner slide surface is configured to couple the fluid-dynamic body. A lower joint plate is slidably coupled to the lower slide surface and the inner slide surface, and is coupled to the upper joint plate through the open center. The lower joint plate is configured to couple to the fluid-dynamic body.
    Type: Grant
    Filed: June 21, 2012
    Date of Patent: April 29, 2014
    Assignee: The Boeing Company
    Inventors: Seiya Sakurai, Kelly T. Jones, Stephen J. Fox, Bruce R. Fox, Nicholas I. Bennett, Mark S. Good
  • Patent number: 8703268
    Abstract: A panel structure includes a composite facesheet and a stiffening core having a plurality of core members in an intersecting web configuration provided on the composite facesheet.
    Type: Grant
    Filed: February 2, 2010
    Date of Patent: April 22, 2014
    Assignee: The Boeing Company
    Inventors: Christopher P. Henry, Sloan P. Smith, Andrew C. Keefe
  • Patent number: 8646729
    Abstract: Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.
    Type: Grant
    Filed: June 1, 2011
    Date of Patent: February 11, 2014
    Assignee: The Boeing Company
    Inventor: Glenn S. Bushnell
  • Patent number: 8616494
    Abstract: The invention relates to a vortex generator (10), in particular for a model (12) in a fluid-dynamic channel. In order to save time during the development of vehicles, in particular aircraft, in particular to save wind tunnel time, it is suggested to configure the vortex generator (10) switchable. Further, the invention relates to various uses of such a switchable vortex generator (10), in particular on models in fluid-dynamic channels and in fluid-dynamic channel tests.
    Type: Grant
    Filed: May 6, 2009
    Date of Patent: December 31, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Klaus-Peter Neitzke, Karin Bauer, Christian Bolzmacher, Winfried Kupke
  • Publication number: 20130341467
    Abstract: A rotation joint and methods for rotationally coupling a swing tip assembly to a fluid-dynamic body are presented. A rotation plate configured to couple to the swing tip assembly comprises a slide ring comprising an open center, an upper slide surface, an inner slide surface, and a lower slide surface. An upper joint plate is slidably coupled to the upper slide surface and the inner slide surface is configured to couple the fluid-dynamic body. A lower joint plate is slidably coupled to the lower slide surface and the inner slide surface, and is coupled to the upper joint plate through the open center. The lower joint plate is configured to couple to the fluid-dynamic body.
    Type: Application
    Filed: June 21, 2012
    Publication date: December 26, 2013
    Inventors: Seiya Sakurai, Kelly T. Jones, Stephen J. Fox, Bruce R. Fox, Nicholas I. Bennett, Mark S. Good
  • Patent number: 8590831
    Abstract: An aircraft includes a fuselage and takeoff and landing wings that are extended at takeoff and landing and serve as the main aerodynamic elements producing the lift. The takeoff and landing wings are in a retracted position in cruising flight to attain a minimum possible drag coefficient of the aircraft and, as a result, reduce fuel requirements in the cruising configuration significantly. When retracted, the takeoff and landing wings are integrated compactly into the fuselage surface. The retracted takeoff and landing wings are fixed in position by retracted position locks of the fuselage. A takeoff and landing wing has a turbine blade profile in cross-section. A takeoff and landing wing has longitudinal rows of slots simulating the operation of a slat and a two-slot flap. The slots are closed with shutters on the outer side of the wing.
    Type: Grant
    Filed: February 8, 2011
    Date of Patent: November 26, 2013
    Inventor: Sergey Nikolaevich Afanasyev
  • Publication number: 20130277495
    Abstract: A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics.
    Type: Application
    Filed: April 2, 2013
    Publication date: October 24, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Airbus Operations GmbH
  • Publication number: 20130233976
    Abstract: A device and a related method are disclosed for selectively providing a modified aerodynamic flow over a wing under aerodynamic flight conditions with respect to a respective datum aerodynamic flow over an external wing surface of the wing in the absence of the device under similar aerodynamic flight conditions. The device includes a body configured to be movably mounted to the wing for selective displacement between at least two different positions with respect to the external wing surface and having an external body surface. The device includes a motion inducing arrangement coupled to the body and configured for providing the selective displacement. In each position, the body is in a respective superposed relationship with a respective wing surface portion of the wing external surface and the modified aerodynamic flow includes airflow over the external body surface. A wing and an air vehicle including the device are also disclosed.
    Type: Application
    Filed: November 12, 2012
    Publication date: September 12, 2013
    Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventors: Alexander NAGEL, Shlomo BAUMINGER
  • Patent number: 8473122
    Abstract: The present invention relates to a method for actively deforming, by feedback control, an aerodynamic profile comprising an elastic material, applied to a part of the surface of the aerodynamic profile, said elastic material being in contact with a fluid flow; said elastic material being able to be deformed by one or more shape memory actuators placed in contact with the elastic material, said actuators being controlled by a computer connected to sensors. This method applies notably to a deformation of an aerofoil of a wing of an aircraft in flight, notably subsonic.
    Type: Grant
    Filed: February 2, 2009
    Date of Patent: June 25, 2013
    Assignee: Thales
    Inventor: Georges-Henri Simon
  • Patent number: 8447445
    Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
    Type: Grant
    Filed: November 18, 2009
    Date of Patent: May 21, 2013
    Assignee: The Boeing Company
    Inventors: Dan Onu, John D. Winter, Candy L. Carr, Paul M. Vijgen, Gary A. Emch, Michael E. Renzelmann
  • Patent number: 8418968
    Abstract: An apparatus comprises a structure having a first side, a second side substantially opposite to the first side, a flexible skin, and a plurality of deformable assemblies. The flexible skin is attached to the first side and the second side of the structure. The plurality of deformable assemblies is moveably connected to the structure, in which each deformable assembly in the plurality of deformable assemblies has a vertex and a base. The each deformable assembly in the plurality of deformable assemblies has a height that is capable of changing to change a shape of the structure and a shape of the flexible skin.
    Type: Grant
    Filed: November 14, 2011
    Date of Patent: April 16, 2013
    Assignee: The Boeing Company
    Inventor: Robert Erik Grip
  • Publication number: 20130087661
    Abstract: This invention relates to a propulsive unit for an aircraft, comprising: a nacelle which defines a duct for channeling an airflow when in use and which provides an outwardly facing surface of the propulsive unit, the outwardly facing surface having an aerodynamic shape; a fan unit for accelerating the airflow within the duct when in use; wherein the duct has an inlet and an outlet and the nacelle is operable to adjust the either or both of the area of the inlet and outlet whilst substantially retaining the aerodynamic shape of the outwardly facing surface.
    Type: Application
    Filed: October 4, 2012
    Publication date: April 11, 2013
    Applicant: ROLLS-ROYCE PLC
    Inventor: ROLLS-ROYCE PLC
  • Publication number: 20130068894
    Abstract: The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the outer end. The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle relative to the span direction. The leading edge comprises a backward sweep part between the kink and the outer end extending from the kink presenting an angle relative to the span direction. The top surface comprises a flow control means for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge.
    Type: Application
    Filed: April 14, 2011
    Publication date: March 21, 2013
    Applicant: B.V. GREEN X
    Inventor: Robert Jan Musters
  • Publication number: 20130062473
    Abstract: The invention pertains to a flow body with a flow surface section that extends in a flow body wingspan direction and a flow body chord direction and with a plurality of fluid lines that lead into the flow surface section and respectively form an opening therein, as well as to a method for taking in and/or blowing out fluid through at least one fluid line that leads into a flow surface section of a flow body and respectively forms an opening therein.
    Type: Application
    Filed: September 7, 2012
    Publication date: March 14, 2013
    Inventors: Burkhard Gölling, Erik Wassen, Tobias Hoell, Frank Thiele
  • Patent number: 8382040
    Abstract: A wing assembly has a wing and one or more no-bias laminar flow oval diskettes that are fixed on a support structure along the C/L (center of lift) of an airfoil, of an aircraft wing. The benefit of an oval diskette with laminar flow is that it has no speed limitations and it allows an aircraft to clime at a speed that matches its Ground Effect Lift speed which is a 25% performance increase and a 40% reduction in vortex drag with a increase stability that eliminates inertia coupling of high-speed airfoils.
    Type: Grant
    Filed: February 16, 2011
    Date of Patent: February 26, 2013
    Inventor: Terry Wayne Hamilton
  • Patent number: 8382042
    Abstract: A structure includes a polymer structural member, which may include a shape memory polymer material, that can change its size and/or shape. An electromagnetic source is used to impose an electric field or a magnetic field on the polymer structural material, in order to control the shape of the material. The force may be used to change the shape of the material and/or to maintain the shape of the material while it is under load. The polymer material may be a solid material, may be a foam, and/or may include a gel. A shape memory polymer material may have mixed in it particles that are acted upon by the electromagnetic field. The structure may be used in any of a variety of devices where shape change (morphing), especially under loading, is desired.
    Type: Grant
    Filed: May 14, 2008
    Date of Patent: February 26, 2013
    Assignee: Raytheon Company
    Inventors: Terry M. Sanderson, Yvonne C. Levenson, David R. Sar
  • Patent number: 8366057
    Abstract: A method and apparatus for an adaptive aerostructure is presented that relies on certified aerospace materials and can therefore be applied in conventional passenger aircraft. This structure consists of a honeycomb material which cells extend over a significant length perpendicular to the plane of the cells. Each of the cells contains an inelastic pouch (or bladder) that forms a circular tube when the cell forms a perfect hexagon. By changing the cell differential pressure (CDP) the stiffness of the honeycomb can be altered. Using an external force or the elastic force within the honeycomb material, the honeycomb can be deformed such that the cells deviate from their perfect-hexagonal shape. It can be shown that by increasing the CDP, the structure eventually returns to a perfect hexagon. By doing so, a fully embedded pneumatic actuator is created that can perform work and substitute conventional low-bandwidth flight control actuators.
    Type: Grant
    Filed: July 26, 2010
    Date of Patent: February 5, 2013
    Assignee: University of Kansas
    Inventors: Roelof Vos, Ronald M. Barrett
  • Patent number: 8262032
    Abstract: A wing, such as a wing for an unmanned aerial vehicle (UAV), includes a beam or box that can be selectively expanded from a collapsed condition, to increase the thickness of the wing. The beam may include a pair of plates that are close together when the beam is in a collapsed condition, and separate from one another to put the beam in an expanded condition. The plates may be substantially parallel to each other, and may have shape memory foam and/or resilient devices, such as coil springs, between them, in order to provide a force to separate the plates before, during, and/or after deployment of the wing. The expandable/collapsible beam may have a lock mechanism to lock it into place when the beam is in an expanded condition.
    Type: Grant
    Filed: November 12, 2009
    Date of Patent: September 11, 2012
    Assignee: Raytheon Company
    Inventors: Terry M. Sanderson, David R. Sar
  • Patent number: 8240616
    Abstract: Systems and methods to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of effectors connected to the outer surface of the aerodynamic structure to be in fluid contact with a flowing fluid when operationally flowing, to induce controlled, globally distributed disturbances at a viscous wall sublayer of a turbulent boundary layer of the flowing fluid when operationally flowing and to manipulate fluid behavior of the flowing fluid to thereby substantially reduce pressure loss associated with incipient separation of the fluid flow from portions of the aerodynamic structure.
    Type: Grant
    Filed: April 22, 2009
    Date of Patent: August 14, 2012
    Inventors: Daniel N. Miller, Brent N. McCallum, Stewart A. Jenkins, David M. Wells
  • Patent number: 8235329
    Abstract: A vehicle control method (and concomitant control structure) comprising deploying an electrolaminate affixed to a substrate and using the combination to control motion of the vehicle.
    Type: Grant
    Filed: June 2, 2009
    Date of Patent: August 7, 2012
    Assignee: Lockheed Martin Corporation
    Inventor: David R. Darling
  • Patent number: 8226048
    Abstract: Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes an airfoil having an external flow surface with an upper portion and a lower portion, and with the airfoil forming a base link. The system further includes a six-bar linkage coupled to the airfoil and having a Stephenson II configuration, including a binary second link pivotably connected to the airfoil, a ternary third link pivotably connected to the second link, a binary fourth link pivotably connected to the third link, a ternary fifth link pivotably connected to the airfoil and the fourth link, and a binary sixth link pivotably connected to the third link and the fifth link. The system can further include a deployable leading edge panel carried by the linkage, with the leading edge panel being movable via the linkage between a stowed position and at least one deployed position.
    Type: Grant
    Filed: December 9, 2008
    Date of Patent: July 24, 2012
    Assignee: The Boeing Company
    Inventors: Kevin W. Beyer, Seiya Sakurai
  • Patent number: 8205840
    Abstract: The invention relates to an elongated, torsion-deformable aerodynamic element, in which the upper surface (2) is continuous while the lower surface (3) comprises a longitudinal slot (6) in the direction of the span and in the vicinity of the leading edge (4). Furthermore, an actuator device (14) inside said aerodynamic element is capable of sliding the edges (6A and 6R) of the slot (6) relative to each other.
    Type: Grant
    Filed: December 3, 2008
    Date of Patent: June 26, 2012
    Assignee: Office National d'Etudes et de Recherches Aerospatiales
    Inventors: Hugues Mercier des Rochettes, Didier Joly, Léon Buchaniek
  • Publication number: 20120138751
    Abstract: An aircraft having a high lift system, including a control computer, high lift bodies on each wing, a drive coupled to these, an activation device connected to the drive via an analog connection, an input device, and sensors detecting a state of the high lift bodies connected via analog lines to the activation device. The input device connects via a digital connection to the activation device for transmitting commands for adjusting the high lift bodies. The activation device is installed in the payload area of the fuselage and in an area extending from a location spaced from the front of the wingbox by a distance of one third of the fuselage length extending from there to the aircraft's tip, as far as a location spaced from the rear of the wingbox by a distance of one third of the fuselage length extending from there to the aircraft's tail end.
    Type: Application
    Filed: May 26, 2010
    Publication date: June 7, 2012
    Applicant: AIRBUS OPERATIONS GMBH
    Inventors: Martin Richter, Peter Lücken
  • Patent number: 8193476
    Abstract: A solid-fuel pellet thrust and control actuation system (PT-CAS) provides command authority for maneuvering flight vehicles over subsonic and supersonic speeds and within the atmosphere and exo-atmosphere. The PT-CAS includes a chamber or solid-fuel pellets that are ignited to expel gas through a throat. The expelled gas is directed at supersonic vehicle speeds in atmosphere to a cavity between an aero control surface and the airframe to pressurize the cavity and deploy the surface or at subsonic speeds in atmosphere or any speed in exo-atmosphere allowed to flow out a through-hole in the surface where the throat and through-hole provide a virtual converging/diverging nozzle to produce a supersonic divert thrust. A pellet and control actuation system (P-CAS) without the through-hole provides command authority at supersonic speeds in atmosphere.
    Type: Grant
    Filed: September 3, 2008
    Date of Patent: June 5, 2012
    Assignee: Raytheon Company
    Inventors: Thomas A. Olden, Robert Cavalleri, Lloyd E. Kinsey, Jr.
  • Patent number: 8186631
    Abstract: An aerofoil member is described which provides for a ‘smart Core’and flexible skin. The core comprises sheet material elements forming adjoining cells. The length of the elements can be changed, for example, using the piezo-electric effect, to alter the cross-sectional shape of the aerofoil without changing the peripheral length. Thus, the shape of the aerofoil may be changed to suit different flight conditions, or to mimic the effect of control surfaces.
    Type: Grant
    Filed: June 8, 2009
    Date of Patent: May 29, 2012
    Assignee: Imperial Innovations Limited
    Inventor: Lorenzo Iannucci
  • Patent number: 8177170
    Abstract: An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, two opposed surfaces connected one to a suction face side and the other to a pressure face side of the wing and that extend longitudinally along the fuselage. At least one of the two surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic disturbances on the central fairing toward the wing to control the flow of air over the wing.
    Type: Grant
    Filed: November 6, 2006
    Date of Patent: May 15, 2012
    Assignee: Airbus Operations SAS
    Inventors: Thierry Fol, Philippe Jimenez, Arnaud Namer
  • Publication number: 20120112011
    Abstract: A casing for a lifting aid for an aircraft, comprising at least one strake which extends essentially in a protruding manner in the direction of flight in relation to an outer surface of the casing. An aircraft comprising a lifting aid and said type of casing.
    Type: Application
    Filed: November 10, 2011
    Publication date: May 10, 2012
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: ROLF EMUNDS
  • Publication number: 20120074264
    Abstract: An airplane wing configuration includes a first wing positioned above and forward of a second wing on an airplane fuselage. The first wing is operable to direct airflow over an upper surface of the second wing, whereby the first and second wings are capable of generating greater lift than a sum of their individual lifts. The first wing may include an adjustable wing flap that redirects airflow over the upper surface of the second wing, and the second wing may include a rotatable portion that pivots to vary the angle of attack of the second wing independent of the first wing.
    Type: Application
    Filed: September 22, 2011
    Publication date: March 29, 2012
    Inventor: Clifford D. Heaton
  • Publication number: 20120012712
    Abstract: An aircraft assembly comprising: a pair of covers; a spar web extending between the covers in a thickness direction, the spar web having a length which extends in a span-wise direction; and a container which extends from the spar web and houses at least part of a system component. The container comprises first and second side walls which are spaced apart from each other across the spar web in the thickness direction, and inboard and outboard walls which are spaced apart from each other along the spar web in the span-wise direction. The spar web and at least part of the container are integrally formed as a single piece.
    Type: Application
    Filed: April 15, 2010
    Publication date: January 19, 2012
    Inventor: James Eden
  • Patent number: 8087618
    Abstract: A propulsion system for an aircraft includes an airfoil, an engine having an engine cowling carried by the airfoil and configured to produce exhaust gases that are predominantly directed toward an aft end of the airfoil by the engine cowling as engine exhaust, a propulsion flap carried by the airfoil and disposed aft of the engine cowling and a plurality of exhaust ejection orifices provided in the propulsion flap and adapted to receive at least a portion of the exhaust gases from the engine cowling.
    Type: Grant
    Filed: July 9, 2009
    Date of Patent: January 3, 2012
    Assignee: The Boeing Company
    Inventors: Arvin Shmilovich, Yoram Yadlin, Roger W. Clark, Robert D. Gregg, III
  • Patent number: 8083185
    Abstract: An embodiment of an aircraft wing includes a main wing section and a variable incidence wing tip. The main wing section is adapted to connect to an aircraft fuselage at a first angle of incidence. The variable incidence wing tip is connected to the main wing section so that the variable incidence wing tip is rotatable to angles of incidence that are different from the first angle of incidence. An embodiment of a method for operating an aircraft includes generating a control signal based on an indication of a desired angle of incidence of a variable incidence wing tip, conveying the control signal to a wing tip rotation mechanism, and rotating the variable incidence wing tip in accordance with the control signal, so that the angle of incidence of the variable incidence wing tip is different from an angle of incidence of the main wing section.
    Type: Grant
    Filed: November 7, 2007
    Date of Patent: December 27, 2011
    Assignee: The Boeing Company
    Inventors: Christopher A. Konings, Jeffrey P. Slotnick
  • Patent number: 8083183
    Abstract: An air discharge device includes a grid that is connected to an aerodynamic surface of an aircraft. The grid includes a number of openings delimited by intermediate zones that are arranged in the extension of the aerodynamic surface of the aircraft and at least one longitudinal reinforcement separating the openings into at least two stages. The dimensions and/or the surface ratio of the perforated zones that correspond to openings and non-perforated zones that correspond to intermediate zones or to the longitudinal reinforcement are such that they create a depression close to the air discharge.
    Type: Grant
    Filed: January 4, 2008
    Date of Patent: December 27, 2011
    Assignee: Airbus Operations SAS
    Inventors: David Grossein, Arnaud Hormiere
  • Patent number: 8056865
    Abstract: An apparatus comprises a structure having a first side, a second side substantially opposite to the first side, a flexible skin, and a plurality of deformable assemblies. The flexible skin is attached to the first side and the second side of the structure. The plurality of deformable assemblies is moveably connected to the structure, in which each deformable assembly in the plurality of deformable assemblies has a vertex and a base. The each deformable assembly in the plurality of deformable assemblies has a height that is capable of changing to change a shape of the structure and a shape of the flexible skin.
    Type: Grant
    Filed: March 5, 2009
    Date of Patent: November 15, 2011
    Assignee: The Boeing Company
    Inventor: Robert Erik Grip
  • Patent number: 7963485
    Abstract: A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal stabilizer. The horizontal stabilizer has a load-bearing structure which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas which are connected to the load-bearing structure such that they can move and can be moved independently of the elevator in order to trim the horizontal stabilizer by varying the aerodynamic profile.
    Type: Grant
    Filed: July 10, 2007
    Date of Patent: June 21, 2011
    Assignee: Airbus Operations GmbH
    Inventor: Manfred Koneczny
  • Publication number: 20110101172
    Abstract: The invention pertains to an aerodynamic body that can be adjusted relative to a main wing of an aircraft by means of an adjusting device, wherein 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 the gap is variable due to the adjustability of the aerodynamic body, featuring 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 in such a way that the shell part can be telescopically moved relative to this aerodynamic body in the wingspread direction; to 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; to an airfoil for an aircraft with a main wing and an aerodynamic body that can be adjusted relative to the main wing by means of an adjusting device and is arranged adjacent to a componen
    Type: Application
    Filed: April 23, 2009
    Publication date: May 5, 2011
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Werner Dyckrup
  • Publication number: 20110101170
    Abstract: An aircraft system may include an airfoil and a deployable device coupled to the airfoil. The system may further include a shape memory alloy actuator coupled between the airfoil and the deployable device. The actuator may be movable between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. The system may additionally include an activatable link positioned between the actuator and the deployable device. The link may have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device.
    Type: Application
    Filed: December 3, 2010
    Publication date: May 5, 2011
    Applicant: The Boeing Company
    Inventors: James H. Mabe, Frederick T. Calkins, Glenn S. Bushnell, Stefan R. Bieniawski