With Lift Modification Patents (Class 244/198)
  • Publication number: 20100252674
    Abstract: Runway length requirement for take-off and landing of an aircraft is reduced by taking advantage of dynamic lift overshoot, and in some cases, dynamic stall. In take-off and landing, the angle of attack is rapidly increased so that the lift coefficient exceeds the maximum predicted by the steady flow lift curve. By increasing the angle of attack at an appropriate rate, the increased lift coefficient can be maintained, without loss of control, until the aircraft touches down in the case of a landing, or until the aircraft can begin a normal climb, in the case of take-off. A low aspect ratio lifting body is preferred because of its more gradual stall behavior, and the potential to use dynamic stall for further deceleration before touchdown. Vortex fences can be oscillated to delay the onset of stall, and, in cruise, to energize the boundary-layer and reduce drag and/or control roll and/or yaw.
    Type: Application
    Filed: January 16, 2007
    Publication date: October 7, 2010
    Applicant: Aereon Corporation
    Inventor: James D. Lang
  • Patent number: 7798443
    Abstract: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.
    Type: Grant
    Filed: December 18, 2006
    Date of Patent: September 21, 2010
    Assignee: The Boeing Company
    Inventors: Brian K. Hamilton, Ahmed Hassan, Terrence S. Birchette, Robert R. Murrill
  • Patent number: 7793884
    Abstract: “T-tailed Deltoid Main Wing” idea allows for design of high-subsonic passenger aircraft with a capacity between 200 and 650 passengers with outer dimensions fitting within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with fuselage that have the same passenger capacity. T-tailed deltoid main wing aircraft is satisfying all safety requirements for a passenger aircraft while having over 50% longer range than the aircraft of equivalent capacity with fuselage. Simple aerodynamic and structural solutions of T-tailed deltoid main wing aircraft are resulting with low development risks and production cost. Simple and reliable flight control systems of aircraft that are based on T-tailed deltoid main wing aerodynamic configuration allow for design of all-purpose, high-lift-capacity, and long range unmanned aircraft.
    Type: Grant
    Filed: December 31, 2008
    Date of Patent: September 14, 2010
    Inventors: Faruk Dizdarevic, Mithad Dizdarevic
  • Patent number: 7780120
    Abstract: A method of controlling an aircraft in a turn without the use of a rudder by producing induced yaw. Induced yaw being produced by creating a net induced drag differential between an inboard wing to the turn and an outboard wing to the turn, whereby the net induced drag differential overcomes adverse yaw produced by the outboard wing.
    Type: Grant
    Filed: February 3, 2009
    Date of Patent: August 24, 2010
    Inventor: Mark D. Fairchild
  • Patent number: 7766281
    Abstract: 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: Grant
    Filed: November 9, 2005
    Date of Patent: August 3, 2010
    Assignee: Airbus Deutschland GmbH
    Inventors: Thomas Lorkowski, Boris Grohmann
  • Patent number: 7740205
    Abstract: An auxiliary wing and flap assembly for an aircraft which is to be extendable from a retracted position to a deployed position. Relative to the chord of the wing, the split flap is located directly adjacent the trailing edge of the wing with the auxiliary wing assembly being located at approximately the mid length of the chord of the wing. A split flap assembly extends approximately one-half the length of the aircraft wing with the auxiliary wing assembly extending the total length of the aircraft wing. The split flap is extendable to assume approximately a sixty degree angle relative to the bottom surface of the aircraft wing while the auxiliary wing assembly is extendible to assume a maximum of ninety degree angle relative to the bottom surface of the aircraft wing. The chord length of the split flap is equal to approximately 0.15 of the chord length of the aircraft wing while the auxiliary wing assembly has an airfoil-shaped member that has a chord length of approximately 0.
    Type: Grant
    Filed: June 6, 2006
    Date of Patent: June 22, 2010
    Inventor: Roger A. Nahas
  • Publication number: 20100148010
    Abstract: A transferable modified leading edge for a wing is detachably mountable to a parent wing. The parent wing may use a NACA 23000-series airfoil. A modified wing tip may be used in conjunction with the modified leading edge. The modified leading edge can be mounted to a parent wing in a way that does not damage the parent wing. The modified leading edge and wing tip can provide increased lift.
    Type: Application
    Filed: April 25, 2007
    Publication date: June 17, 2010
    Applicant: A PARTNERSHIP OF JIM LANGLEY AND COURTNEY HUNTER
    Inventor: Courtney Heath Hunter
  • Patent number: 7728265
    Abstract: A MEMS type flow actuated out-of-plane flap apparatus includes a substrate defining a plane; a duct attached to the substrate, the duct and the substrate defining a fluid flow channel; and a rotatable flap having a flow receiving portion and an extension portion. The flow receiving portion being disposed in the fluid flow channel where, in an actuated position of the flap, a fluid flow against the flow receiving portion causes rotation of the flap and movement of the extension portion out of the plane of the substrate.
    Type: Grant
    Filed: March 26, 2007
    Date of Patent: June 1, 2010
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Michael A. Deeds, David Herman
  • Patent number: 7686256
    Abstract: The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distributed arrays of flow control devices (submerged in the boundary layer) to create disturbances in the flow field that inhibit the growth of larger vortical structures and/or to energize the aft body shear layer to keep the shear layer attached the aft body surface. These undesirable aerodynamic phenomena produce increased vehicle drag which harms vehicle range, persistence, and loiter capabilities. Additionally, the unsteady nature of the turbulent vortical structures shed in the aft body wake region may produce increased dynamic buffeting and aft body heating by entraining nozzle jet exhaust (a.k.a. jet wash) —requiring additional structural support, shielding, and vehicle weight.
    Type: Grant
    Filed: September 14, 2005
    Date of Patent: March 30, 2010
    Assignee: Lockheed Martin Corporation
    Inventors: Daniel N. Miller, David D. Young
  • Patent number: 7686257
    Abstract: The present invention provides a system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a synthetic jet actuator(s) operable to produce an oscillatory flow, and fluidic jet(s) operable to provide a continuous fluid flow. The oscillatory flow of the synthetic jet(s) and the continuous fluid flow of the fluidic jet(s) combine or mix to produce the pulsed jet operable to manipulate the primary fluid flow. These synthetic pulsators may then be actively manipulated to control the flow behavior of the ducted fluid flow, influence the inception point and trajectory of flow field vortices within the fluid flow, and reduce flow separation within the primary fluid flow.
    Type: Grant
    Filed: May 23, 2005
    Date of Patent: March 30, 2010
    Assignee: Lockheed Martin Corporation
    Inventors: Seyed Saddoughi, Matthew Boespflug, Scott Donnelly
  • Publication number: 20100044519
    Abstract: The present invention provides a method of reducing the compressibility drag of wing, and it also provides a container implementing the method. The container (10, 10?, 10?) is provided successively with a front portion (11) in the vicinity of its leading edge (14), then with an intermediate portion (12), and then with a rear portion (13) in the vicinity of its trailing edge (15), said rear portion (13) tapering progressively in a direction going from the leading edge (14) of the container towards its trailing edge (15). Furthermore, said rear portion (13) is extended by connection means (17) enabling the container (10, 10?, 10?) to be connected under the wing (1) in such a manner that said tapering rear portion (13) is partially upstream from the leading edge (2) of the wing (1).
    Type: Application
    Filed: October 21, 2008
    Publication date: February 25, 2010
    Applicant: AIRBUS FRANCE
    Inventors: Thierry FOL, Cyrll BONNAUD
  • Patent number: 7661630
    Abstract: 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: Grant
    Filed: March 13, 2008
    Date of Patent: February 16, 2010
    Inventor: John Libby
  • Publication number: 20090302167
    Abstract: An aircraft can include a wing with a leading edge and a trailing edge. The wing has a main body and movable control surfaces coupled to the main body. The wing generates lifting forces when the aircraft is in flight. The movable control surfaces can be used to control the generated lifting forces. A spanwise flow inhibitor extends from the outer wingtip of the wing. At least one gurney flap extends generally downwardly from at least a portion of the trailing edge of the wing. The flap at least partially counteracts a change in center of lift attributable to the spanwise flow inhibitor.
    Type: Application
    Filed: August 23, 2006
    Publication date: December 10, 2009
    Inventor: Robert J. Desroche
  • Publication number: 20090230251
    Abstract: A wing arrangement of an aircraft has a wing and at least one pylon for suspending an engine below the wing. The wing has a leading edge with a high-lift device, which is able to move between a deployed position in which the high-lift device projects forward of the leading edge, and which is interrupted in a forward intermediate region of the wing located at the leading edge, the pylon having a forward edge extending forward of the leading edge of the wing between a forward upper portion connected to the wing in the forward intermediate region and a forward lower portion connected to a nacelle of the engine. An element of narrow elongate shape protrudes longitudinally from the forward edge and, during flight at a high angle of attack of the aircraft, generates a vortex of aerodynamic flow that is propagated toward the forward intermediate region above the wing.
    Type: Application
    Filed: March 13, 2009
    Publication date: September 17, 2009
    Applicant: AIRBUS FRANCE
    Inventors: Cyril Bonnaud, Stephanie Dantin, Marjorie Defos, Thierry Fol
  • Publication number: 20090206206
    Abstract: Improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following: strake extending forwardly of the wing inboard extent, raked wing tip, reversed fillet at strake or fuselage junction, inboard leading edge flap extending over less than about 15% of the inboard wing panel span, hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.
    Type: Application
    Filed: October 16, 2007
    Publication date: August 20, 2009
    Inventors: James D. Chase, Michael Henderson, Peter Sturdza
  • Publication number: 20090194640
    Abstract: An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like.
    Type: Application
    Filed: December 22, 2005
    Publication date: August 6, 2009
    Inventor: David Birkenstock
  • Publication number: 20090173834
    Abstract: This invention relates to an element (11) for generating a fluid dynamic force, the element (11) comprising first (13) and second (15) surfaces extending in opposite directions from a leading edge (17) of the element (11) and meeting at a trailing edge (18) thereof to define a three dimensional body that is shaped to generate a fluid dynamic force when immersed at an angle of attack ? to a fluid flow over the element (11) in a flow direction U, the first surface (13) comprising an array of fluid inlets (19) and the second surface (15) comprising a corresponding array of fluid outlets (21), each said inlet (19) being fluidly coupled to a said outlet (21) by means of a fluid duct (23) at least part of which is pitched at an angle ? to a tangent plane (Y-Y) to said second surface (15) in the vicinity of said outlet (21) and skewed at an angle ? to said fluid flow direction U, the arrangement being such that the element (11) is operable in use to generate a relatively high fluid pressure region downstream of said
    Type: Application
    Filed: July 13, 2006
    Publication date: July 9, 2009
    Applicant: CITY UNIVERSITY
    Inventors: Simon Andrew Prince, Vahik Khodagolian
  • Publication number: 20090173838
    Abstract: An extra narrow wing system for airplanes combining the advantages of sufficient lift like a conventional airplane wing with reduced space requirements. A V-shaped nudge at the back side of the main wing helps to overcome the limitations of extreme delta-wings and allows very narrow wings with angles of as low as 0 degrees but sufficient lift for a propeller or jet operated plane. Front and tail wings are one aerodynamic system. The system results in very narrow airplane designs useful when operating under space constraints.
    Type: Application
    Filed: August 15, 2006
    Publication date: July 9, 2009
    Inventors: WALTER GRILL, SEBASTIAN SCHNEEWEISS
  • Patent number: 7558653
    Abstract: The present invention relates to an autopilot system for a rotary wing aircraft operating relative to at least two pilot axes, which system comprises, for each of the two axes, at least one servo-control relationship providing a respective initial control instruction, with the two relationships having a common target; the system includes combination means (36) for providing a series of control instructions by combining the two initial control instructions (UCV, UTV).
    Type: Grant
    Filed: October 11, 2005
    Date of Patent: July 7, 2009
    Assignee: Eurocopter
    Inventor: Marc Salesse-Lavergne
  • Publication number: 20090118874
    Abstract: Systems and methods for controlling aircraft electrical power are disclosed. A system in accordance with one embodiment includes an electric motor, an aircraft load coupled to the electric motor and powered by the electric motor, and a motor controller coupled to the electric motor to vary an output of the electric motor. The motor controller is changeable among a fixed number of preset controller modes, with individual controller modes corresponding to an operation mode of the aircraft and a non-zero output level of the electric motor. In further embodiments, motor controllers can be substituted for each other, e.g., in the event one motor controller becomes unoperational.
    Type: Application
    Filed: September 7, 2006
    Publication date: May 7, 2009
    Applicant: The Boeing Company
    Inventors: Jeffrey J. White, David K. Toy, J. Everett Groat
  • Patent number: 7503527
    Abstract: A method of controlling an aircraft in a turn without the use of a rudder by producing induced yaw. Induced yaw being produced by creating a net induced drag differential between an inboard wing to the turn and an outboard wing to the turn, whereby the net induced drag differential overcomes adverse yaw produced by the outboard wing.
    Type: Grant
    Filed: September 28, 2004
    Date of Patent: March 17, 2009
    Inventor: Mark D. Fairchild
  • Patent number: 7484589
    Abstract: An apparatus and method is provided for attenuating aerospace engine noise and unsteady pressure fluctuations associated with high velocity exhaust flows. The apparatus and method reduce acoustic fatigue damage to aerospace vehicles that may be caused by the reflection of exhaust energy from landing and/or launch platforms. The apparatus includes a passive treatment area associated with the platform operable for reducing the magnitude of the reflected sound waves and unsteady pressure fluctuations from the high velocity exhaust mass flow exiting from the engine. The passive treatment area may include a layer of sound absorptive material, at least one set of roughness elements for disrupting high velocity flow structures. A protective cover may be positioned over the passive treatment area for permitting exhaust flow to pass therethrough while still providing adequate structure to support the weight of the aerospace vehicle.
    Type: Grant
    Filed: March 4, 2004
    Date of Patent: February 3, 2009
    Assignee: The Boeing Company
    Inventor: Yueping Guo
  • Patent number: 7475853
    Abstract: The present invention features a fluid flow regulator that functions to significantly influence fluid flow across the surface of an object, as well as to significantly effect the performance of the object subjected to the fluid. The fluid flow regulator comprises a pressure recovery drop that induces a sudden drop in pressure at an optimal pressure recovery point on said surface, such that a sub-atmospheric barrier is created that serves as a cushion between the molecules in the fluid and the molecules at the object's surface. More specifically, the present invention fluid flow regulator functions to significantly regulate the pressure gradients that exist along the surface of an object subject to fluid flow. Regulation of pressure gradients is accomplished by selectively reducing the pressure drag at various locations along the surface, as well as the pressure drag induced forward and aft of the object, via the pressure recovery drop.
    Type: Grant
    Filed: June 19, 2003
    Date of Patent: January 13, 2009
    Inventors: Darko Segota, John W. Finnegan, II
  • Publication number: 20080265102
    Abstract: A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.
    Type: Application
    Filed: April 27, 2007
    Publication date: October 30, 2008
    Inventors: Jon V. Larssen, Frederick T. Calkins
  • Patent number: 7410133
    Abstract: Improved miniature trailing edge effectors for aerodynamic control are provided. Three types of devices having aerodynamic housings integrated to the trailing edge of an aerodynamic shape are presented, which vary in details of how the control surface can move. A bucket type device has a control surface which is the back part of a C-shaped member having two arms connected by the back section. The C-shaped section is attached to a housing at the ends of the arms, and is rotatable about an axis parallel to the wing trailing edge to provide up, down and neutral states. A flip-up type device has a control surface which rotates about an axis parallel to the wing trailing edge to provide up, down, neutral and brake states. A rotating type device has a control surface which rotates about an axis parallel to the chord line to provide up, down and neutral states.
    Type: Grant
    Filed: December 27, 2006
    Date of Patent: August 12, 2008
    Assignee: The Board of Trustees of the Leland Stanford Junior University
    Inventors: Hak-Tae Lee, Stefan R. Bieniawski, Ilan M. Kroo
  • Publication number: 20080128561
    Abstract: A system and method is described generally for deforming a first surface of a body and deforming a second surface of a body to alter a fluid flow in order to change the characteristics of the fluid flow about the body and thereby control the fluid dynamic forces on the body.
    Type: Application
    Filed: December 1, 2006
    Publication date: June 5, 2008
    Inventors: Roderick A. Hyde, Nathan P. Myhrvold, Lowell L. Wood, Alistair K. Chan, Clarence T. Tegreene
  • Patent number: 7380756
    Abstract: A single dielectric barrier aerodynamic plasma actuator apparatus based on the dielectric barrier discharge phenomenon is disclosed and suggested for application to aerodynamic uses for drag reduction, stall elimination and airfoil efficiency improvement. In the plasma actuator apparatus non-uniform in time and space, partially ionized gasses are generated by one or more electrode pairs each having one electrically encapsulated electrode and one air stream exposed electrode and energization by a high-voltage alternating current waveform. The influence of electrical waveform variation, electrode polarity, electrode size and electrode shape on the achieved plasma are considered along with theoretical verification of achieved results. Light output, generated thrust, ionizing current waveform and magnitude and other variables are considered. Misconceptions prevailing in the present day plasma generation art are addressed and are believed-to-be corrected.
    Type: Grant
    Filed: November 16, 2004
    Date of Patent: June 3, 2008
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventors: Carl L. Enloe, Thomas E. McLaughlin, Eric J. Jumper, Thomas C. Corke
  • Publication number: 20080116321
    Abstract: A lift spoiler for use on the wings of parked aircraft to reduce lift forces produces by the aircraft wings and that are produced during storms and high wind speed conditions. The lift spoiler includes a generally rectangular spoiler panel that is supported relative to the wing upper surface by a pair of holders. The holders include suction-cup-type attachments for securely attaching the lift spoiler relative to the wing upper surface to deflect airflow over the wing surface and thereby reduce the lift effect of the airflow that acts on the wing to otherwise lift the aircraft during high wind speed conditions and cause possible damage to the aircraft while it is parked.
    Type: Application
    Filed: November 22, 2006
    Publication date: May 22, 2008
    Inventor: Timmy Tuinder
  • Patent number: 7367532
    Abstract: 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.
    Type: Grant
    Filed: January 31, 2005
    Date of Patent: May 6, 2008
    Inventor: John Libby
  • Patent number: 7357358
    Abstract: Aircraft leading edge device systems and methods for sizing such systems are disclosed. In one embodiment, a spanwise lift coefficient distribution for an airfoil corresponding to at least one design condition and at least one aircraft angle of attack is identified, and a leading edge device chord length is sized to at least approximately achieve the selected spanwise lift coefficient distribution. In another embodiment, a spanwise distribution of aircraft angles of attack corresponding to local maximum lift coefficients for an airfoil operated at a design condition is identified, and a leading edge device chord length at each of a plurality of spanwise locations is sized to achieve the distribution of aircraft angles of attack corresponding to local maximum lift coefficients. In yet another embodiment, a leading edge device chord length is tapered in two, at least approximately opposite, spanwise directions.
    Type: Grant
    Filed: February 27, 2004
    Date of Patent: April 15, 2008
    Assignee: The Boeing Company
    Inventors: Douglas S. Lacy, Greg H. Wyatt
  • Patent number: 7290738
    Abstract: Separate upper and lower plenums within an aircraft airfoil or a sea hydrofoil conduct fluid under different pressures to nozzle slots from which jets emerge to augment lift in accordance with different travel conditions. Lift is induced by nozzle slot emergence of a primary jet from one of the plenums along a reverse flow path relative to secondary jet outflow from the other plenum. This capability involves angularly adjusted deflection of the primary jet outflow along forward, reverse or vertical directional flow paths from the trailing end of the airfoil or hydrofoil under zero and other different speed conditions by emergence of the secondary wall jet.
    Type: Grant
    Filed: October 28, 2004
    Date of Patent: November 6, 2007
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Ernest O. Rogers, Robin D. Imber, Jane S. Abramson, Martin J. Donnelly
  • Patent number: 7226015
    Abstract: The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.
    Type: Grant
    Filed: January 28, 2004
    Date of Patent: June 5, 2007
    Assignee: Orbital Research Inc
    Inventors: Troy Prince, Frederick J. Lisy, Mehul P. Patel, Jack M. DiCocco, Reed Carver, Robert N. Schmidt
  • Patent number: 7108230
    Abstract: An aircraft with swept back wings and spoilers inlaid into the top surface near the tips of the wings. The aircraft also includes an elevator formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings.
    Type: Grant
    Filed: June 6, 2003
    Date of Patent: September 19, 2006
    Assignee: Northrop Grumman Corporation
    Inventor: Walter D. Clark
  • Patent number: 6834835
    Abstract: The present invention is a wing having telescoping segments deployed via an actuator composed of a heat activated material. The actuator is a coiled tube of shape memory alloy (SMA) with large force-displacement characteristics activated thermally by either a fluid or an electrical charge. Actuator motion extends an inner wing segment from an outer wing segment when the coiled tube is compressed. Compression is achieved by heating the coiled tube so as to cause a phase transformation from Martensite to Austenite. The inner wing segment may be retracted by a mechanical device or second SMA coil when the coiled tube is cooled and returned to its Martensite phase.
    Type: Grant
    Filed: March 12, 2004
    Date of Patent: December 28, 2004
    Assignee: QorTek, Inc.
    Inventors: Gareth Knowles, Ross W. Bird
  • Patent number: 6834830
    Abstract: A main wing structure comprises at least a leading edge structure and a wing central structure coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface, a lower wing surface, a leading edge and a trailing edge. The upper wing surface includes: a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located at 38% of a wing chord length; a central profile portion which has a positive curvature radius, and which is provided to extend from the largest-thickness point to the vicinity of a position corresponding to approximately 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of a wing chord from the largest-thickness point is equal to or smaller than 0.
    Type: Grant
    Filed: February 27, 2003
    Date of Patent: December 28, 2004
    Assignee: Honda Giken Kogyo Kabushiki Kaisha
    Inventor: Michimasa Fujino
  • Publication number: 20040155157
    Abstract: A winglet (12) for an aircraft wing is provided. The winglet (12) has an airflow control arrangement, for example in the form of a trailing edge flap (20) by means of which lift generated by the winglet can be varied. The control arrangement desirably forms part of a manoeuvre load alleviation system (22) for the aircraft.
    Type: Application
    Filed: October 30, 2003
    Publication date: August 12, 2004
    Inventor: Robert M Bray
  • Publication number: 20040079840
    Abstract: An aircraft lift control system mounted on an aircraft is provided. The aircraft has at least one wing. The aircraft lift control system comprises an oscillating aero surface mounted to the aircraft wing. A resonant frame is connected to the oscillating aero surface. An actuator is mounted to the resonant frame wherein the sinusoidal force produced by the actuator on the resonant frame results in a resonant deformation in the resonant frame and resonant-sinusoidal displacement of the aero-surface.
    Type: Application
    Filed: September 30, 2003
    Publication date: April 29, 2004
    Inventors: William D. Armstrong, William R. Lindberg, Jonathan W. Naughton, John E. McInroy
  • Patent number: 6669142
    Abstract: Lifting arrangement for lateral aircraft surfaces that consists of numerous lateral flutings, grooves, splines, flutes or riblets parallel to each other, arranged on the lateral surfaces of fuselages, fin units, pylons and gondolas of aircraft with a downward slope from the nose to the tail, with the flow of air passing through such flutings, grooves, etc., towards the rear and downwards, generating lifting by reaction, using small planes or fins to support the engines and flight control fins.
    Type: Grant
    Filed: July 18, 2001
    Date of Patent: December 30, 2003
    Inventor: Manuel Munoz Saiz
  • Patent number: 6651935
    Abstract: Apparatus for controlling shock/boundary-layer interactions created by a supersonic shock on a surface of a structure, includes a cavity formed in the structure and having an opening on the surface. A plate is attached to the surface and covers the opening. A plurality of flaps are formed on the plate and is operable to cooperatively close the opening in response to subsonic airflow condition over the flaps, and open the opening to permit airflow through the cavity in response to supersonic airflow conditions over the flaps.
    Type: Grant
    Filed: June 12, 2002
    Date of Patent: November 25, 2003
    Assignee: The Board of Trustees of the University of Illinois
    Inventors: Eric Loth, Philippe H. Geubelle, Scott R. White, Andrew G. Alleyne, Stephen T. Mcllwain, J. Craig Dutton, Daniel Tortorelli, David Davis
  • Patent number: 6641089
    Abstract: An auxiliary flap is movably arranged on a planar trailing edge of an aerodynamic element such as a wing, rudder, stabilizer, or flap. The auxiliary flap is rotatable and/or slidable relative to the aerodynamic element, to move selectively into three positions. In a first position, a free edge of the auxiliary flap protrudes into an airflow boundary layer on one side of the aerodynamic element, to decrease lift. In a second position, a free edge of the aerodynamic element protrudes into an airflow boundary layer on the other side of the aerodynamic element, to increase lift. In a third neutral position, the auxiliary element does not protrude into either boundary layer, so as not to influence lift. The auxiliary flap is simple and rapidly acting. The flap protrudes substantially perpendicularly into the boundary layer flow. The auxiliary flap has a planar plate shape.
    Type: Grant
    Filed: September 25, 2002
    Date of Patent: November 4, 2003
    Assignee: Airbus Deutschland GmbH
    Inventors: Detlev Schwetzler, Peter May
  • Patent number: 6592072
    Abstract: A method for forming a transonic wing that segregates a baseline transonic wing into a plurality of airfoil segments that are collectively modified an optimized so as to tailor a spanwise variation of the baseline transonic wing in a manner that includes the optimized airfoil segments. An improved wing is also provided.
    Type: Grant
    Filed: June 20, 2002
    Date of Patent: July 15, 2003
    Assignee: The Boeing Company
    Inventors: Robert D. Gregg, III, John Charles Vassberg, David M. Pitera
  • Patent number: 6578798
    Abstract: This airlifting surface division idea provides for division of airlifting surfaces resulting in low induced and interference drag. It can be applied to aircraft wings and helicopter and windmill rotor blades to significantly reduce induced drag when compared to prior art. Also, it can be used for new concepts of large subsonic and hypersonic aircraft to significantly reduce their overall drag and external dimensions when compared to prior art, simultaneously providing for very good pitch maneuver and longitudinal stability of such aircraft.
    Type: Grant
    Filed: April 8, 2002
    Date of Patent: June 17, 2003
    Inventors: Faruk Dizdarevic, Mithad Dizdarevic
  • Patent number: 6478251
    Abstract: A flier structure including a fuselage extending from front side to rear side and a weight body connected with front end of the fuselage. A port wing and a starboard wing respectively leftward and rightward extend from the fuselage. A left tailfin and a right tailfin respectively extend from rear sides of the port wing and starboard wing. The bottoms of front edges of the port wing and starboard wing are respectively connected with a left and a right flow deflecting wings. The rear sides of the left and right flow deflecting wings are respectively spaced from the port wing and starboard wing by a predetermined distance. The left and right flow deflecting wings are respectively connected with the left and right sides of the fuselage. The disconnected portions between the left flow deflecting wing and port wing and the right flow deflecting wing and starboard wing respectively form two flow deflecting spaces.
    Type: Grant
    Filed: November 2, 2001
    Date of Patent: November 12, 2002
    Inventor: Ming-Ta Wei
  • Patent number: 6467732
    Abstract: A base wing 11, as attached at its root end portion to the rotor head of a rotational drive unit, is provided with a front wing 12 and a rear wing 13 having substantially equal spans. The vortex, as generated at the wing tip, is divided into relatively weak tip vortexes of a front wing vortex 12c generated at the tip of the front wing and a rear wing vortex 13c generated at the tip of the rear wing 13. Since the front wing 12 and the rear wing 13 have equal spans, on the other hand, the front wing vortex 12c and the rear wing vortex 13c are close to each other so that they interact positively with each other and are weakened and diffused. As a result, while the helicopter is hovering, the interactions between the retreating rotor blade of the rotor and the tip vortex generated by the tip of the advancing rotor blade are drastically reduced to suppress the occurrence of the BVI noises.
    Type: Grant
    Filed: February 23, 2001
    Date of Patent: October 22, 2002
    Assignee: Fuji Jukogyo Kabushiki Kaisha
    Inventors: Takanori Tsukahara, Masahiro Obukata
  • Patent number: 6457671
    Abstract: A funnel strip is added to a rotary airfoil, which utilizes the Bernoulli principle to increase the velocity of air over the suction side of the rotating airfoil to increase the lift. The device is applicable to thrust-producing devices, such as propellers, as well as to wind-powered devices.
    Type: Grant
    Filed: September 5, 2001
    Date of Patent: October 1, 2002
    Inventor: Norman Sherman
  • Patent number: 6431499
    Abstract: In a wing with a main wing part (1) and a drag-reducing wing grid arranged at a distal end of the main wing part, a grid includes at least two winglets (2) staggered in parallel and with an overlap (c/t) smaller than one. A zero air flow direction of the winglets (2) is, on average, matched to the zero air flow direction of the main wing part (1) and the ratio of the length of the chord (cM) of the main wing part (1) to the chord length (cW) of the wing grid is essentially the same as the correction factor Kappa according to Betz applicable for the overlap of the winglets. For this wing, the lift of the main wing part (1) and the wing grid is not only equal in the design point, but also the lift gradients of the main wing part (1) and of the wing grid are coincident. This means that the drag-reducing effect of the wing grid is maintained independent of the momentary angle of attack of the wing, without the wing grid having to be adjusted accordingly.
    Type: Grant
    Filed: October 12, 2001
    Date of Patent: August 13, 2002
    Inventors: Ulrich La Roche, Lucas La Roche
  • Patent number: 6431498
    Abstract: An apparatus to modify a wing to provide increased lift over drag ratios compared to similar wings with straight leading edges. For wings extending in a lateral direction, and defining a longitudinal upstream direction, the apparatus forms a laterally extending leading edge facing in the upstream direction. The apparatus forms a plurality of protrusions spaced laterally along the leading edge, the protrusions creating a smoothly varying, alternately forward-and-aft sweep along the leading edge relative to the upstream flow direction along the leading edge.
    Type: Grant
    Filed: June 30, 2000
    Date of Patent: August 13, 2002
    Inventors: Philip Watts, Frank E. Fish
  • Publication number: 20020066830
    Abstract: Disclosed herein is a vibrational air mover that is open on both ends with eye shaped openings. There is a cable pulled tight from corner to corner of the eye shaped openings on both ends. The two eye shaped pieces are connected to each other with iron rods, the rods connect to the corners of the eye shaped pieces. This forms a rectangular shape with openings on each end. There is a cable running from corner to corner of the eye shaped openings, connecting to the center of these two cables is an additional cable that runs the length of the air mover. The eye shaped pieces are made of a flexable material, such as stainlesss steal. The frame work is then covered with material rip stop nylon is sewn to the eye shaped pieces and the iron rods it needs to be pulled tight as it is sewn on. Then the material is doped with air craft dope or butyrate dope to pull the material drum tight. Then the weight bearing cable is attached, it is attached to the front eye shaped piece in the center of the cable.
    Type: Application
    Filed: December 4, 2000
    Publication date: June 6, 2002
    Inventors: Lester Earl Mullings, Lester Earl Mullings
  • Patent number: 6394397
    Abstract: A tip member is movable mount at the outboard end of a main lifting member such as a wing or rotor blade. The main lifting member at least at the outboard end has an internal cavity defined therein between pressure-side and suction-side surfaces of the main lifting member. The tip member is movable relative to the main lifting member between a neutral position in which the tip member presents substantially no obstacle to a spanwise component of flow over either suction-side or pressure-side surfaces at the outboard end of the main lifting member, and a position in which a portion of the tip member extends beyond on of the pressure-side and suction-side surfaces of the main lifting member so as to present an obstacle to the spanwise component of flow over that surface at the outboard end of the main lifting member and thereby locally affect the flow at the outboard end.
    Type: Grant
    Filed: December 6, 2000
    Date of Patent: May 28, 2002
    Assignee: The Boeing Company
    Inventors: Hieu T. Ngo, Lisa E. Barlow
  • Patent number: 6394396
    Abstract: A hollow expandable and contractible displacement element is secured onto the concave rear surface of a slat facing the leading edge of an aircraft wing. A bleed air line supplies engine bleed air into the hollow displacement element to selectively expand or contract the displacement element, which is preferably elastically expandable. When the slat is extended, the displacement element is expanded to fill-out the concave cavity on the rear surface of the slat so as to prevent formation of a vortex in the slat air gap and thereby to reduce aero-acoustic noise. When the slat is retracted, the displacement element is contracted to be conformingly accommodated in the sickle-shaped space between the slat and the leading edge of the wing.
    Type: Grant
    Filed: April 17, 2001
    Date of Patent: May 28, 2002
    Assignee: Airbus Deutschland GmbH
    Inventors: Wolfgang Gleine, Knut Mau, Udo Carl