Aerodynamic Resistance Reducing Patents (Class 244/130)
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Patent number: 8276851Abstract: Systems and methods for providing dynamic control to a vehicle in a dynamic fluid. The systems and methods of the invention relate to one or more morphable surfaces that can be controlled by a controller and an actuator in an active manner to provide asperities that interact with a fluid moving across the morphable surfaces. By controlling the size, shape and location of the asperities, one can exert control authority over the motion of the vehicle relative to the fluid, including a speed, a direction and an attitude of the vehicle. Examples of materials that provide suitable morphable surfaces include ionic polymer metal composites and shape memory polymers, both of which types of material are commercially available. Useful morphable surface systems have been examined and are described.Type: GrantFiled: May 9, 2008Date of Patent: October 2, 2012Assignee: California Institute of TechnologyInventor: Beverley J. McKeon
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Publication number: 20120234975Abstract: A fairing transition is provided for covering a gap between a movable body and a fixed body on a vehicle that includes, but is not limited to a base plate that is attachable to a vehicle, a cover plate that is attachable to the base plate. The base plate and the cover plate include, but are not limited to a correspondingly formed connecting profile having positive fit on surfaces that face each other, with the connecting profile configured to slide the cover plate onto the base plate. Furthermore, the cover plate is lockable to the base plate in an end position.Type: ApplicationFiled: March 14, 2012Publication date: September 20, 2012Applicant: AIRBUS OPERATIONS GMBHInventors: Sascha TIMM, Gerd STAHL, Uwe HENNING
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Patent number: 8251312Abstract: The upstream flowfield of a vehicle traveling in supersonic or hypersonic atmospheric flight is actively controlled using attribute(s) experienced by the vehicle. Sensed attribute(s) include pressure along the vehicle's outer mold line, temperature along the vehicle's outer mold line, heat flux along the vehicle's outer mold line, and/or local acceleration response of the vehicle. A non-heated, non-plasma-producing gas is injected into an upstream flowfield of the vehicle from at least one surface location along the vehicle's outer mold line. The pressure of the gas so-injected is adjusted based on the attribute(s) so-sensed.Type: GrantFiled: September 9, 2009Date of Patent: August 28, 2012Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Endwell O. Daso, Victor E. Pritchett, II, Ten-See Wang, Rebecca Ann Farr
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Patent number: 8245981Abstract: A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.Type: GrantFiled: April 30, 2008Date of Patent: August 21, 2012Assignee: General Electric CompanyInventors: Edward Atwood Rainous, Barry Lynn Allmon, Jeffre Gerry Loewe, William Clarke Brooks, Lee Alan Blanton, Courtney James Tudor, Vicky Showalter Budinger
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Patent number: 8240609Abstract: A metamaterial has a magnetic permeability response at frequencies sufficient to generate a repulsive force between a fluid and a surface to which the metamaterial may be applied. The metamaterial may be nanofabricated such that an absolute value of the magnetic permeability of the metamaterial is substantially greater than an absolute value of an electric permittivity of the metamaterial. The metamaterial may generate a repulsive force between the surface and the fluid moving relative to the surface and thereby reduce viscous drag of the fluid on the surface. A method of reducing the viscous drag of the fluid moving past the surface includes producing relative motion between the surface and the fluid and generating the repulsive force between the surface and the fluid.Type: GrantFiled: December 8, 2008Date of Patent: August 14, 2012Assignee: The Boeing CompanyInventors: Claudio G. Parazzoli, Minas H. Tanielian, Robert B. Greegor
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Patent number: 8240616Abstract: 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: GrantFiled: April 22, 2009Date of Patent: August 14, 2012Inventors: Daniel N. Miller, Brent N. McCallum, Stewart A. Jenkins, David M. Wells
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Patent number: 8226038Abstract: The invention relates a method and apparatus for reducing the drag on aircraft, particularly aircraft with an upswept afterbody. The method includes the steps of positioning a plurality of drag reducing elements on the fuselage of the aircraft, wherein the drag reducing elements are positioned on the fuselage from a position at the breakline of the fuselage and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements is positioned such that a first end of the drag reducing element is at an angle of between approximately 15 and 35° nose up relative to the flow of air about the fuselage at the location where the drag reducing element is positioned.Type: GrantFiled: March 18, 2009Date of Patent: July 24, 2012Assignee: Lockheed Martin CorporationInventors: Brian R. Smith, Brant H. Maines, Edward C. Ma, Edward A. DiGirolamo, Patrick J. Yagle
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Publication number: 20120175910Abstract: A system and method for drag reduction allows thrust output, fuel efficiency or both to be maximized. Specifically, a rear portion of a body or motor vehicle may be modified to increase thrust output, fuel efficiency or both by creating a stagnation area, a suction inlet and a convex cusp area formed on the rear portion of the motor vehicle. Increasing the concavity or camber or sharpness of the radius of the stagnation area results in greater local pressure coefficient, which results in greater thrust output. The size and shape of the suction inlet and the convex cusp area will also have an effect on thrust output and fuel efficiency. A width and volume of an airplane fuselage may be increased.Type: ApplicationFiled: January 6, 2012Publication date: July 12, 2012Inventor: David T. BIRKENSTOCK
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Publication number: 20120175463Abstract: An apparatus and method for improving the fuel range of an aircraft are provided. The aircraft includes a fuselage with a front windshield, and an external skin providing a top cover for a cockpit of the aircraft. The apparatus includes an aerodynamic fairing secured adjacent the windshield and enclosing the external skin covering the cockpit for a reduction in an abrupt change in area encountered by air flowing along the length of the fuselage. An enclosure is formed between the aerodynamic fairing and the external skin in which a fuel bladder, configured with a reticulated polyurethane foam insert, may be disposed for added fuel capacity of the aircraft. The method includes steps of providing an aerodynamic fairing configured to balance the flow of fluid over the aircraft during flight, and securing the aerodynamic fairing atop the aircraft and adjacent the front windshield.Type: ApplicationFiled: March 23, 2012Publication date: July 12, 2012Inventor: Calvin Burgess
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Patent number: 8210472Abstract: Disclosed is a method for improving the performance of transport aircraft. In particular, the aircraft is provided with a rounded nose cone in front of a center of gravity of the aircraft. The rounded nose cone has an upper longitudinal surface and a lower longitudinal surface configured, respectively, to generate a lifting force and a negative lifting force and produce a resultant that is lifting and to produce an auxiliary nose-up moment. The method involves shaping the nose cone to increase the lifting resultant. This shaping is carried out-by increasing the upper longitudinal surface of the nose cone, so as to increase the lifting force, and by reducing the lower longitudinal surface of the nose cone, so as to decrease the negative lifting force.Type: GrantFiled: October 20, 2009Date of Patent: July 3, 2012Assignee: Airbus Operations SASInventors: Lionel Espagnan, Arnaud Hormiere, Francois Guillaumel
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Patent number: 8210482Abstract: A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generators are provided, each of which is configured to generate a vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each prismatic vortex generator has a prismatic shape with a base, leading and trailing ends, and sidewalls that incline toward and join each other to form an apex. The leading end of each prismatic vortex generators is inclined away from the direction of flow.Type: GrantFiled: October 27, 2009Date of Patent: July 3, 2012Assignee: Lockheed Martin CorporationInventors: Daniel N. Miller, Dan J. Baruzzini
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Patent number: 8210476Abstract: A kit for modifying a strut of an aircraft with an aerodynamic cover includes a rigid sheath formed from a first portion and a second portion. Each of the first portion and the second portion have a curved shape. The rigid sheath includes an angled leading edge and an angled trailing edge. Convex surfaces connect the leading edge and the angled trailing edge. There is an attachment for attaching the rigid sheath to the strut, the attachment securing the sheath to the strut such that the strut is positioned at the camber of the rigid sheath.Type: GrantFiled: June 10, 2010Date of Patent: July 3, 2012Inventor: Garold Toews
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Publication number: 20120138731Abstract: A fairing (1) for a structural element of a rotorcraft, the fairing including a rear portion (2) that is substantially orthogonal to the longitudinal direction (L) of the aircraft, extending between two spaced-apart trailing edges (3, 4) and thus presenting a determined width, said rear portion (2) closing at least part of the internal volume defined by the fairing (1) and generating aerodynamic drag in forward flight. According to the invention, the rear portion presents, at least at the trailing edges (3, 4), a shape that is perturbed on the streamlines (5) of the air-flow.Type: ApplicationFiled: November 30, 2011Publication date: June 7, 2012Applicant: EUROCOPTERInventor: David Alfano
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Patent number: 8191835Abstract: A wing of an aircraft has a mainplane, which has an upper face, a lower face and an aerodynamically shaped area. The wing has an additional airfoil which is articulated on the mainplane and can be extended from a retracted state with a slot area being opened between the mainplane and the additional airfoil. The wing also has a variable-position slot-varying apparatus which is arranged on the lower face, forms a part of the aerodynamic profile of the additional airfoil or mainplane when the additional airfoil is extended, and at least partially covers the slot area between the mainplane and the additional airfoil on the lower face when the additional airfoil is in the retracted state. The slot-varying apparatus can be varied between a curved configuration, in which it forms a part of an aerodynamic profile, and an extended configuration, in which it at least partially covers the slot area.Type: GrantFiled: December 11, 2007Date of Patent: June 5, 2012Assignee: Airbus Deutschland GmbHInventors: Boris Grohmann, Johann Reichenberger, Thomas Lorkowski
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Publication number: 20120132752Abstract: Interface arrangement between a first component (11) and a second component (21) of an aircraft structure having an aerodynamic contour, such as a wing skin and a wing leading edge panel, the first component (11) having a joggle so that it includes a first area (13) which surface (15) belongs to the aircraft aerodynamic contour and a second area (17) where the joint with the second component (21) takes place, the second component (21) having a surface (23) belonging to the aircraft aerodynamic contour, in which a sealing part (31) suitable shaped to maintain the continuity of the aircraft aerodynamic contour in the interface area between said components (11, 13) as well as to fill the expected gap (25) between said components (11, 13) is joined to the second component (21).Type: ApplicationFiled: June 16, 2011Publication date: May 31, 2012Inventors: Ignacio OUTON HERNÁNDEZ, José Luis DELGADO JAREÑO
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Patent number: 8190306Abstract: Disclosed is a method and device for attenuating vertical turbulence on an aircraft. The method and device involve calculating, by a calculating unit, based on a determined vertical wind component a first control order to control movement of at least one first controllable movable member that acts on aircraft lift, and a second control order that controls movement of at least one second controllable movable member to act on aircraft pitch. A verification unit verifies that activation conditions evidencing severe turbulence are in effect, the vertical turbulence being attenuated.Type: GrantFiled: February 9, 2009Date of Patent: May 29, 2012Assignee: Airbus Operations SASInventors: Stephane Puig, Romeo Byzery
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Publication number: 20120126061Abstract: An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening.Type: ApplicationFiled: August 2, 2010Publication date: May 24, 2012Applicant: AIRBUS OPERATIONS LIMITEDInventors: Hugo Alexandre Duart Mendes Raposeiro, Bruno Stefes, Holger Bammann, Thomas Selchert, James Brown, Heiko Rothe, Alexander Solntsev
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Patent number: 8181910Abstract: Fluid having a velocity approaching a surface having a leading edge may be deflected. An electric field may be projected ahead of the leading edge of the surface to ionize at least some molecules of the fluid approaching the wing. The strength of the electric field may vary between a maximum level and a minimum level periodically over time. A magnetic field may be projected from the surface to deflect the ionized molecules of the fluid such that some or all of the deflection is normal to the velocity of the approaching fluid and normal to the leading edge of the surface while the electric field is below its maximum level.Type: GrantFiled: October 31, 2008Date of Patent: May 22, 2012Inventor: Blair J. Lewis
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Patent number: 8177170Abstract: 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: GrantFiled: November 6, 2006Date of Patent: May 15, 2012Assignee: Airbus Operations SASInventors: Thierry Fol, Philippe Jimenez, Arnaud Namer
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Patent number: 8172185Abstract: In order to establish laminar flow on the attachment line (18) of an aerofoil body, a duct entrance (27) is provided on the leading edge of the aerofoil body for receiving spanwise boundary layer flow BLt. The exit (23) of the duct is located spanwise downstream of the duct entrance (27). The boundary layer flow BLt enters the duct (23) and is discharged downstream. The height of the duct entrance (27) above the leading edge of the aerofoil body is greater than the depth of the boundary layer BLt and thus a fresh laminar boundary layer is established on the outer surface (20) of the duct which propagates spanwise along the surface to rejoin the leading edge of the aerofoil body.Type: GrantFiled: December 20, 2007Date of Patent: May 8, 2012Assignee: Gaster Consultants LtdInventor: Micheal Gaster
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Patent number: 8172181Abstract: An apparatus and method for improving the fuel range of an aircraft are provided. The aircraft includes a fuselage with a front windshield, and an external skin providing a top cover for a cockpit of the aircraft. The apparatus includes an aerodynamic fairing secured adjacent the windshield and enclosing the external skin covering the cockpit for a reduction in an abrupt change in area encountered by air flowing along the length of the fuselage. An enclosure is formed between the aerodynamic fairing and the external skin in which a fuel bladder, configured with a reticulated polyurethane foam insert, may be disposed for added fuel capacity of the aircraft. The method includes steps of providing an aerodynamic fairing configured to balance the flow of fluid over the aircraft during flight, and securing the aerodynamic fairing atop the aircraft and adjacent the front windshield.Type: GrantFiled: December 22, 2006Date of Patent: May 8, 2012Inventor: Calvin Burgess
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Publication number: 20120104794Abstract: Methods providing naturally driven routing of air bleed derived from the external air pressure field typically developed about a moving vehicle were conceived. By design, internal ductways are to be used for providing an open flow path from relatively higher air pressure sources (such as that in the undercarriage region of a driven car) into lower base pressure regions (typically developed aft of blunt trailing body regions) as are generally found on road and ‘airdrop’ cargo delivery air vehicles having open rear doors. Low energy air bleed flow injected into the vehicle's separated afterbody region acts to replenish entrained base flow and its base drag reduction is thereby achieved.Type: ApplicationFiled: October 28, 2010Publication date: May 3, 2012Inventor: Henry August
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Patent number: 8167248Abstract: An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled bearing rod is positioned on each of the engine support pylons so as to generate a propulsive resultant force under action of an oblique air flow.Type: GrantFiled: May 11, 2007Date of Patent: May 1, 2012Assignee: Airbus Operations S.A.S.Inventors: Thierry Fol, Marjorie Defos
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Patent number: 8162260Abstract: A monomolecular carbon-based film can be placed on an aircraft part, such as the leading edge designed to directly impinge against air during flight, ascent or descent, in order to form a smooth surface having increased lubricity and reduced air friction. The aircraft part may be in the form of a helicopter rotor, wing, propeller, fin, aileron, nose cone, and the like. The monomolecular carbon-based film can be deposited on the aircraft part, for example, using a reactor that includes a bed of silica and through which emissions from a diesel engine are passed. The monomolecular carbon-based film decreases air friction and increased lift of a modified aircraft that includes an aircraft part treated with the film. It also provides a structured shock absorber.Type: GrantFiled: March 3, 2009Date of Patent: April 24, 2012Inventor: Thomas C. Maganas
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Patent number: 8157216Abstract: A fairing includes three sections: an aft section, a middle section, and a nose section. The aft section includes a first surface having a generally constant conic angle (i.e., a “boat-tail angle”) with respect to the longitudinal axis such that the aft section tapers to a first end configured to attach to a generally cylindrical body. The middle section, which intersects and is axially aligned with the aft section, has a second surface characterized by a constant elliptical cross-section along a plane orthogonal to the longitudinal axis. The nose section intersects and is axially aligned with the middle section. The nose section is further defined by four generally concave trianguloid surfaces, each extending from the middle section to a common apex intersecting the longitudinal axis, wherein each adjacent pair of trianguloid surfaces intersects at an edge (e.g., an incurvate edge).Type: GrantFiled: June 30, 2008Date of Patent: April 17, 2012Assignee: ATA Engineering, Inc.Inventors: Thomas A. Deiters, Tomoya Ochinero, James C. Newman, III
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Patent number: 8146865Abstract: The present invention relates to a leading edge (1) for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement (2) firmly adhered to the mentioned inner face of the leading edge (1) arranged such that it confers the leading edge (1) with better capacity to adapt to deformability and greater absorption of energy due to impacts. The invention also relates to a method of manufacturing a leading edge (1) with a metallic reinforcement (2) for aircraft made of composite material.Type: GrantFiled: May 30, 2007Date of Patent: April 3, 2012Assignee: Airbus Espania S.LInventor: Desiderio Sánchez-Brunete Álvarez
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Patent number: 8141811Abstract: A shock wave in a gas is modified by emitting energy to form an extended path in the gas; heating gas along the path to form a volume of heated gas expanding outwardly from the path; and directing a path. The volume of heated gas passes through the shock wave and modifies the shock wave. This eliminates or reduces a pressure difference between gas on opposite sides of the shock wave. Electromagnetic, microwaves and/or electric discharge can be used to heat the gas along the path. This application has uses in reducing the drag on a body passing through the gas, noise reduction, controlling amount of gas into a propulsion system, and steering a body through the gas. An apparatus is also disclosed.Type: GrantFiled: October 2, 2006Date of Patent: March 27, 2012Inventor: Kevin Kremeyer
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Publication number: 20120068016Abstract: A fairing device for creating an aerodynamic cover for an area of an aircraft structure, including a first fairing part with an outer side forming a first exterior flow contour, and having a fairing section for contacting a first section of the aircraft structure and a connecting section. The first fairing part includes a mounting device for receiving a connecting element. The fairing device includes a second fairing part including a fairing section having an outer side forming a second exterior flow contour and is designed for contacting a second section of the aircraft structure and a connecting section. The shape of the outer side of the second fairing part is adapted to the inner side of the connecting section of the first fairing part in an overlapping area, so the connecting section of the first fairing part forms a joint piece protruding over the second fairing part in the overlapping area.Type: ApplicationFiled: July 12, 2011Publication date: March 22, 2012Applicant: AIRBUS OPERATIONS GMBHInventor: Axel Sauermann
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Patent number: 8136757Abstract: A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and/or reduced local twist, and a second region with an increased local wing camber and/or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.Type: GrantFiled: December 10, 2008Date of Patent: March 20, 2012Assignee: Airbus Operations GmbHInventor: Roland Kelm
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Patent number: 8128037Abstract: A purging system for a laminar flow control system comprises an air scoop and a diffuser fluidly connected thereto. The air scoop is disposable into an external flow of an external atmosphere. The diffuser is configured to fluidly connect the air scoop to a suction cavity of the laminar flow control system wherein the suction cavity may be disposed adjacent a porous skin of an airfoil such as adjacent a leading edge of the airfoil. The laminar flow control system may be configured to suction boundary layer flow passing over the porous skin by drawing a portion of the boundary layer flow through a plurality of pores formed in the porous skin. The diffuser ducts high pressure flow captured by the air scoop to the suction cavity for discharge through the pores to reduce the potential of blockage thereof.Type: GrantFiled: January 19, 2009Date of Patent: March 6, 2012Assignee: The Boeing CompanyInventors: Arthur G. Powell, Paul M. Vijgen
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Patent number: 8128029Abstract: Ventral fairing for an aircraft provided between a left wing and a right wing, which comprises a lower central section of convex transverse cross-section located between the left lower surface of the left wing and the right lower surface of the right wing, and with an angle between the cross-section of the fairing and the line of cross-section corresponding to the lower surface of each wing of less than 90 degrees, separate left and right lower lateral sections of concave transverse cross-section which are respectively extended between the lower surface of each wing and the central section; separate first lines of inflection between the lower surface of each wing and the corresponding lateral section; separate second lines of inflection between the lateral sections and the central section.Type: GrantFiled: March 26, 2007Date of Patent: March 6, 2012Assignee: Airbus Operations, S.L.Inventors: Mario Jiménez Del Lago, Julián Pérez Serrano
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Patent number: 8128035Abstract: Winglets with recessed surfaces, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing having an inboard portion and an outboard portion, and further includes a winglet coupled to the wing at the outboard portion. The winglet can have a first surface facing at least partially inboard and a second surface facing at least partially outboard, with the first surface including a recessed region.Type: GrantFiled: April 15, 2008Date of Patent: March 6, 2012Assignee: The Boeing CompanyInventors: Adam P. Malachowski, Stephen R. Chaney, Norman K. Ebner, Stephen T. LeDoux
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Publication number: 20120049001Abstract: A vortex generation device for reducing drag on an upswept aircraft fuselage afterbody and including a vortex generator vane that extends longitudinally from along an outer mold line of the fuselage of an aircraft adjacent an upswept afterbody of the fuselage and that is configured and positioned to reduce drag on an upswept aircraft fuselage afterbody by developing vortices that counteract vortices generated along such an upswept fuselage afterbody. The vane is disposed aft of a side paratrooper jump door of the aircraft fuselage and has a spine and leading end that are faired smoothly into the mold line of the fuselage.Type: ApplicationFiled: August 27, 2010Publication date: March 1, 2012Inventors: Brian R. Smith, Patrick J. Yagle
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Patent number: 8118252Abstract: A rear lower aerodynamic fairing for an attachment device for an aircraft engine, including two side panels assembled together with transverse stiffening inner ribs spaced apart from each other along a longitudinal direction of the fairing, and a heat protection floor to be closely followed by a primary flow of the engine. The floor includes plural floor segments distributed along the direction and non-rigidly bound to each other, and the fairing further includes an assembling mechanism assembling the floor segments, offsetting the latter of the ribs to which are connected the assembling mechanism.Type: GrantFiled: March 13, 2008Date of Patent: February 21, 2012Assignee: Airbus Operations SASInventors: Jean-Francois Dumont, Frederic Roche
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Patent number: 8113466Abstract: A system and method for drag reduction allows thrust output, fuel efficiency or both to be maximized. Specifically, a rear portion of a body or motor vehicle may be modified to increase thrust output, fuel efficiency or both by creating a stagnation area, a suction inlet and a convex cusp area formed on the rear portion of the motor vehicle. Increasing the concavity or camber or sharpness of the radius of the stagnation area results in greater local pressure coefficient, which results in greater thrust output. The size and shape of the suction inlet and the convex cusp area will also have an effect on thrust output and fuel efficiency. A width and volume of an airplane fuselage may be increased.Type: GrantFiled: September 16, 2008Date of Patent: February 14, 2012Inventor: David T. Birkenstock
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Publication number: 20120032024Abstract: A fairing includes a fairing body having a fairing interior and an interior surface and a spray-on insulation foam layer provided on the interior surface of the fairing body.Type: ApplicationFiled: August 4, 2010Publication date: February 9, 2012Inventors: Juhn-Shyue Lin, Herbert L. Hoffman, Hugh W. Poling
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Patent number: 8096507Abstract: An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.Type: GrantFiled: January 23, 2009Date of Patent: January 17, 2012Assignees: Innovative Technology Applications, University of Notre Dame Du LacInventors: Alan B. Cain, Eric J. Jumper, Donald J. Wittich, III, Edward J. Kerschen, David Cavalieri, T. Terry Ng
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Patent number: 8091824Abstract: An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location.Type: GrantFiled: May 27, 2010Date of Patent: January 10, 2012Inventors: Clark M. Butler, Ian J. Gilchrist
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Patent number: 8087606Abstract: A motion generating system for propelling and/or lifting a craft exploiting explosive and implosive processes, whereby a propulsive or lifting force on the craft arises from two sources: generation of a stream of fluids which imparts thrust to the craft; and generation of zones of reduced pressure and density in front of and above the craft allowing the craft to be thrust forward and lifted by ambient pressure on the rear and underside of the craft. Furthermore, reduction of fluid density in front of the craft results in a reduction of frontal drag allowing the attainment of higher speeds. The motion generating system may have other applications; for example, the motion generating system may be used to propel a stream of liquid in the manner of a pump.Type: GrantFiled: October 4, 2006Date of Patent: January 3, 2012Inventor: Sapoty Brook
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Patent number: 8087617Abstract: A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an underside of the wing. The nacelle may generate a nacelle wake that passes over the wing upper surface at high angles of attack and induces flow separation. The chine is preferably configured such that a vortex generated thereby interacts which the nacelle wake to delay flow separation and stall.Type: GrantFiled: August 15, 2008Date of Patent: January 3, 2012Assignee: The Boeing CompanyInventors: Anthony J. Sclafani, Christopher A. Konings
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Patent number: 8083171Abstract: Method for configuring and operating an aircraft for minimizing sonic boom effects at ground level during supersonic flight of the aircraft. The method includes configuring an aircraft and flying the aircraft at supersonic speed so that in the supersonic flight, a lower profile of the aircraft is presented and generally groundwardly directed; and generating multiple different magnitude pressure disturbances below the aircraft, and radiating therebelow, and controlling the different magnitude pressure disturbances generated below the aircraft so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during the supersonic flight.Type: GrantFiled: May 26, 2007Date of Patent: December 27, 2011Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Donald C. Howe, Robert R. Wolz, Jimmy L. Hancock, Jr.
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Patent number: 8083183Abstract: 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: GrantFiled: January 4, 2008Date of Patent: December 27, 2011Assignee: Airbus Operations SASInventors: David Grossein, Arnaud Hormiere
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Patent number: 8074938Abstract: 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: GrantFiled: December 1, 2006Date of Patent: December 13, 2011Inventors: Roderick A. Hyde, Nathan P. Myhrvold, Lowell L. Wood, Jr., Alistair K. Chan, Clarence T. Tegreene
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Publication number: 20110290935Abstract: The present invention relates to a method of manufacture of a stiffening transverse internal rib for an aerodynamic fairing of an engine mounting device, including: the production of a rib preform by superplastic forming having an outline of a broadly quadrilateral shape, and a central opening (52) traversing this preform; the division of the preform into two parallel straight-line segments (56, 60), which are diagonally opposed, causing the separation into two half-parts (46a?, 46a?) of the rib preform; and fishplating of the two rib preform half-parts (46a?, 46a?) by bolting.Type: ApplicationFiled: May 25, 2011Publication date: December 1, 2011Applicant: Airbus Operations (S.A.S.)Inventors: Stephane Machado, Fabien Raison, Stephane Romani
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Publication number: 20110290936Abstract: The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs (46) for an aerodynamic fairing of an engine mounting device, including: production, for each rib (46), of a given rib preform (46a) by superplastic forming; and in respect of at least one of the ribs (46) of the group having a smaller size than that of the preform (46a), division of the latter into four preform parts (56a-56d) each incorporating one of the four corners of the quadrilateral formed by the preform, followed by the joining of the four parts to one another so as to obtain the rib.Type: ApplicationFiled: May 25, 2011Publication date: December 1, 2011Applicant: Airbus Operations (S.A.S.)Inventors: Stephane MACHADO, Fabien Raison, Stephane Romani
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Patent number: 8066221Abstract: The invention concerns a wall (10) of vertical partitioning for a ventral cowling of an aircraft including a plurality of vertical panels (11, 12, 12?, 13, 13?), each panel being linked to an adjacent panel by a vertical post (14, 15, 16). At least one exterior panel (13, 13?) is mounted in a fixed manner on at least one associated vertical post (14, 16). The upper end of said vertical post is fitted with a means of fastening in transverse rotation intended to be fixed to the structure (8) of an aircraft, the means of fastening in transverse rotation being capable of allowing the displacement (Dy) of the structure of the aircraft with respect to the fixed partitioning wall. It is also possible for at least one intermediary panel (12, 12?) to be mounted floating on at least one associated vertical post (15, 16), in such a way as to have a deflection parallel and perpendicular to the adjacent panels.Type: GrantFiled: November 23, 2006Date of Patent: November 29, 2011Assignee: Airbus FranceInventor: Francois Rouyre
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Patent number: 8056850Abstract: A wing-to-body fairing for reducing noise due to wing-to-body fairing vibrations in an aircraft, spacecraft, or vehicle may include a honeycomb center having a cavity which is at least partially filled with particle material.Type: GrantFiled: January 18, 2008Date of Patent: November 15, 2011Assignee: The Boeing CompanyInventors: Juhn-Shyue Lin, Herbert L. Hoffman, Gary R. Chewning, Melvin Kosanchick, III, Hugh Poling
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Patent number: 8016245Abstract: A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface.Type: GrantFiled: October 18, 2006Date of Patent: September 13, 2011Assignee: The Boeing CompanyInventors: Ahmed A. Hassan, Bradley A. Osborne, Scott Schwimley, Garry Billman, Mary Billman, legal representative
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Patent number: 8006939Abstract: A method to manipulate a fluid flow over a surface is provided. This method may be used to reduce drag, improve the lift to drag (L/D) ratio, attach fluid flow, or reduce flow noise at the surface. This involves flowing a fluid over the surface wherein the fluid contains positively charged ions and electrons. An electric field accelerates ions and electrons in directions parallel to the electric field. A magnetic field at the surface redirects ions and electrons based on their velocity and charge. The magnetic field imparts little force on the relatively heavy and slow moving positive ions but has a significant impact on the relatively fast moving, light weight electrons. This results in a non-zero net change in the total momentum of the positive ions and electrons allowing thrust to be realized. This thrust may be sufficient for vehicle propulsion or manipulation of the fluid flow around the vehicle.Type: GrantFiled: November 22, 2006Date of Patent: August 30, 2011Assignee: Lockheed Martin CorporationInventors: Paul D. McClure, Charles J. Chase
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Publication number: 20110204185Abstract: A shock control fairing for mounting a junction between adjoining aircraft surfaces. The fairing has a cross-sectional profile which varies along the length of the fairing. The cross-sectional profile of the fairing has a maximum area at a location which, when mounted to an aircraft, is substantially proximal to a location on the surface of the aircraft at which a shock would be expected to develop without the fairing.Type: ApplicationFiled: November 5, 2008Publication date: August 25, 2011Applicant: AIRBUS OPERATIONS LIMITEDInventor: Neil John Lyons
