Aerodynamic Resistance Reducing Patents (Class 244/130)
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Patent number: 9321241Abstract: Ventilated aero-structures include a micro-lattice structure operatively coupled to a honeycomb core. The interface between the honeycomb core and the micro-lattice structure is configured to permit air flow to and from the honeycomb core via the micro-lattice structure. Aircraft include a ventilated aero-structure and a ventilation system configured to circulate air through the ventilated aero-structure. Some methods include coupling a micro-lattice structure to a honeycomb core. Some methods include utilizing a ventilated aero-structure to assemble an aircraft.Type: GrantFiled: May 11, 2012Date of Patent: April 26, 2016Assignee: The Boeing CompanyInventors: Robert E. Doty, Richard W. Burns, Alan Jon Jacobsen, Sophia Shu Yang
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Patent number: 9216807Abstract: Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant.Type: GrantFiled: October 24, 2012Date of Patent: December 22, 2015Assignee: The Boeing CompanyInventor: Bruce Raymond Detert
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Patent number: 9193399Abstract: An active and passive boundary layer control system and method for reducing boundary layer separation and the resulting form drag from ground vehicles. Tubings with multiple venturis connected in series are attached to the side and/or roof of the ground vehicle. A flow of compressed air is created by an engine auxiliary, e.g., a turbocharger or a supercharger, or by a designated blower and injected into the tubings. Suction created by the venturis actively removes decelerated fluid from the boundary layer and keeps the boundary layer flow attached. Optionally, the system exhausts the air in concentrated free jets along the vehicle body to a series of passive boundary layer control devices, such as vortex generators.Type: GrantFiled: September 9, 2014Date of Patent: November 24, 2015Inventor: Peter Schmidt
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Patent number: 9193447Abstract: An aircraft landing gear assembly comprises a landing gear (10) arranged to be moveable between a stowed position and a deployed position. The assembly includes a removably mounted cover plate (20) that covers a void (12) defined by a part of the landing gear assembly. The plate (20) may have a substantially constant thickness, one or more fixing elements (22) on one side only of the plate, and a sealing element (34) that extends around substantially the entire perimeter (20a) of the plate (20).Type: GrantFiled: December 9, 2010Date of Patent: November 24, 2015Assignee: Airbus Operations LimitedInventors: Leung Choi Chow, Christopher Neil Wood, Philip Campbell
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Patent number: 9180958Abstract: Aircraft and airframes include a skin operatively coupled to a structural reinforcement member. The structural reinforcement member and the skin collectively define a run-out region that encompasses a terminal edge of the structural reinforcement member. Within the run-out region, the skin is more flexible than in adjacent portions of the skin. Methods include defining a region of increased flexibility of a skin relative to adjacent portions of the skin, and operatively coupling the skin to a structural reinforcement member.Type: GrantFiled: May 25, 2012Date of Patent: November 10, 2015Assignee: The Boeing CompanyInventors: Victor A. Munsen, David Neal Berry
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Patent number: 9120578Abstract: A guidance apparatus mounted on the belly of a tanker aircraft for providing visual indications to the pilot of the receptor aircraft with respect to the approaching operation to carry out the refueling by means of a refueling boom. The guidance apparatus includes light emitting devices including modules of light emitting diodes and control devices for supplying current to the light emitting diodes that include dimming control units for controlling the intensity of the light emitted by the light emitting devices via a dimming signal depending on a dimming voltage. The dimming control units are adapted to provide to the light emitting devices a pulse-exponential amplitude modulated dimming signal so that the light intensity can be properly controlled in all visibility conditions.Type: GrantFiled: March 6, 2013Date of Patent: September 1, 2015Assignee: EADS Construcciones Aeronauticas S.A.Inventor: Ignacio Yague Martin
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Patent number: 9051057Abstract: Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet.Type: GrantFiled: December 21, 2012Date of Patent: June 9, 2015Assignee: EMBRAER S.A.Inventors: Carlos Roberto Ilário Da Silva, André Luis Roncatto, Antônio Nunes Belém, Marcelo Faria Da Cunha
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Patent number: 9038950Abstract: An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.Type: GrantFiled: August 17, 2012Date of Patent: May 26, 2015Assignee: Airbus Operations GmbHInventors: Peter Kreuzer, Sven Schaber, Iris Goldhahn
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Publication number: 20150136909Abstract: A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit.Type: ApplicationFiled: November 18, 2013Publication date: May 21, 2015Applicant: ROHR, INC.Inventors: Teresa M. Kruckenberg, Vijay V. Pujar, Robert L. Braden
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Patent number: 9027883Abstract: 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: GrantFiled: November 5, 2008Date of Patent: May 12, 2015Assignee: Airbus Operations LimitedInventor: Neil John Lyons
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Patent number: 9016632Abstract: A method and system are provided to weaken shock wave strength at leading edge surfaces of a vehicle in atmospheric flight. One or more flight-related attribute sensed along a vehicle's outer mold line are used to control the injection of a non-heated, non-plasma-producing gas into a local external flowfield of the vehicle from at least one leading-edge surface location along the vehicle's outer mold line. Pressure and/or mass flow rate of the gas so-injected is adjusted in order to cause a Rankine-Hugoniot Jump Condition along the vehicle's outer mold line to be violated.Type: GrantFiled: May 16, 2013Date of Patent: April 28, 2015Assignee: 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, Aaron Howard Auslender, Isaiah M. Blankson, Kenneth J. Plotkin
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Patent number: 9004404Abstract: A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature).Type: GrantFiled: January 6, 2009Date of Patent: April 14, 2015Assignee: Airbus Operations LimitedInventor: Colin John West
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Patent number: 8991759Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage.Type: GrantFiled: September 23, 2011Date of Patent: March 31, 2015Assignee: Airbus Operations, S.L.Inventors: Ma Aránzazu García Patino, Angel Postigo Rodríguez, David López Fernández
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Patent number: 8985676Abstract: A vehicle component includes a surface which, during operation, is exposed to an air flow. The surface includes a separating area where the air flow separates from the surface, and at least one obstructing element associated with the separating area for introducing an obstruction into the air flow. The obstructing element includes at least one guide surface which protrudes into the air flow. The guide surface is inclined relative to the local direction of the main air flow so that it confers on the part of the main air flow that impacts the guide surface a speed component that runs perpendicular to the local direction of the main air flow and induces turbulence in the air flow downstream of the obstructing element.Type: GrantFiled: September 7, 2011Date of Patent: March 24, 2015Assignee: Bombardier Transportation GmbHInventors: Alexander Orellano, Martin Schober, Andreas Tietze, Rene Blaschko
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Patent number: 8960609Abstract: An airfoil tip vortex mitigation device comprising an intake port disposed in a first surface of an airfoil and an exit port in fluid communication with the intake port and disposed in a second surface of the airfoil where air pressure is less than at the first surface when the airfoil is producing lift. The channel and exit port are positioned and configured to direct diverted air in such a way as to weaken an airfoil tip vortex that's produced by the airfoil when the airfoil is producing lift.Type: GrantFiled: December 15, 2011Date of Patent: February 24, 2015Assignee: Lockheed Martin CorporationInventors: Perry Wooden, Ruble E. Moor, Eric F. Charlton, Daniel N. Miller, Edwin L. Blosch, Jeffrey J. Azevedo
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Publication number: 20150048208Abstract: An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The invention employs supercooling (through a combination of superconductivity and/or superemissivity) driven by the cryogenic power of liquid hydrogen and/or regenerative evaporation of liquid hydrogen and/or liquid nitrogen to drive isothermal compression and consequentially usurp the shock front in totality at Mach 1. The ensuing supercool/chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space.Type: ApplicationFiled: August 16, 2013Publication date: February 19, 2015Inventor: Charl Emelio Janeke
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Patent number: 8939410Abstract: An apparatus delays the transition of a boundary layer flow from laminar to turbulent. Flow disruptors are positioned to be in contact with a boundary layer flow moving in a flow direction over a surface. Each flow disruptor generates fluctuations in the boundary layer flow such that the frequency of the fluctuations is a damping region frequency defined by an amplification rate curve associated with the boundary layer flow.Type: GrantFiled: July 9, 2013Date of Patent: January 27, 2015Inventor: Reginald J Exton
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Patent number: 8931518Abstract: Apparatus and methods provide for a flow control actuator having a fluid cavity that is shaped to create periodic waveforms within the resulting resonant actuating flow with predetermined characteristics for actuating a high-speed fluid flow. According to various embodiments, a flow control actuator includes a power source for exciting the actuator fluid at a resonant frequency and a cavity shaped according to resonant macrosonic synthesis principles to maximize the exit velocity of the actuating flow at an orifice of the actuator.Type: GrantFiled: September 23, 2008Date of Patent: January 13, 2015Assignee: The Boeing CompanyInventor: Edward A. Whalen
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Patent number: 8919703Abstract: A hinge sealing element to substantially prevent airflow between an edge of a moveable aero surface structure and an edge of a fixed skin of an aircraft wing in the vicinity of the ribs to which the moveable aero surface structure is pivotally mounted is disclosed. The hinge sealing element comprising a deformable elongate, resiliently flexible strip having an upper face to contact a trailing edge of a fixed skin and one end attachable to a moveable aero surface structure such that said strip extends from an upper surface of said moveable aero surface structure beyond its leading edge and into a space between the edge of the fixed skin and the rib of the aircraft wing to a second, free end. The strip is configured such that it deforms during pivotal movement of the moveable aero surface structure to maintain contact between the upper face of the flexible element and the trailing edge of the fixed skin.Type: GrantFiled: May 13, 2010Date of Patent: December 30, 2014Assignee: Airbus Operations LimitedInventor: Simon John Parker
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Patent number: 8899528Abstract: A blade seal comprises a flexible member having a relatively thick edge opposite a relatively thin edge, and an actuator at least partially embedded in the flexible member for actively deflecting the thin edge with respect to the thick edge upon activation of the actuator. The blade seal may be fixed to an aerodynamic trailing edge of either a fixed aerofoil portion or a flight control surface of an aerofoil for sealing between the fixed aerofoil portion and the flight control surface. Also, a method of sealing an aerofoil using the blade seal.Type: GrantFiled: May 14, 2010Date of Patent: December 2, 2014Assignee: Airbus Operations LimitedInventor: Christopher Coconnier
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Publication number: 20140332631Abstract: An array of aerodynamic riblets is created by a plurality of high stiffness tips with a layer supporting the tips in predetermined spaced relation and adhering the tips to a vehicle surface.Type: ApplicationFiled: November 1, 2013Publication date: November 13, 2014Applicant: The Boeing CompanyInventors: Diane C. Rawlings, Stephen Christensen
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Patent number: 8882043Abstract: An aircraft landing gear (9) includes a wheel (1) having a wheel rim (3) on which a tire (4) is held. The gap (6) between the rim (3) and tire (4) is bridged and covered by a sealing element (7), which thereby presents a smooth surface to the air flowing over the wheel during flight of the aircraft (8). Thus, noise that would otherwise be generated by the interaction of air and the parts of the wheel (1) and/or tire (4) defining the gap (6) is reduced. Such noise reduction benefits may also be achieved by providing a tire (4) and wheel (1) so shaped that there is no gap (6) between the tire (4) and wheel rim (3).Type: GrantFiled: April 7, 2004Date of Patent: November 11, 2014Assignee: Airbus UK LimitedInventors: Leung Choi Chow, Christopher Neil Wood
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Patent number: 8876052Abstract: An array of aerodynamic riblets is formed with a surface layer for adhering to an aerodynamic surface and a plurality of riblet tips having a parabolic cross section extending from the surface layer.Type: GrantFiled: March 7, 2013Date of Patent: November 4, 2014Assignee: The Boeing CompanyInventors: Diane C. Rawlings, James D. McLean, Mary J. Mathews
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Patent number: 8876051Abstract: A bridging seal comprising a stack of two or more layers of elastomer, the bridging seal having a first edge and a second edge opposite the first edge, adjacent layers being attached to each other at the first and second edges, wherein adjacent layers of the bridging seal have opposing surfaces and a substantial portion of the opposing surfaces is unbonded. The bridging seal may be used to seal a gap between two aerodynamic surfaces on an aircraft.Type: GrantFiled: February 1, 2011Date of Patent: November 4, 2014Assignee: Airbus Operations LimitedInventor: David Mark Stewart
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Patent number: 8870124Abstract: A method of improving aerodynamic performance of foils by the application of conformal, elastomeric vortex generators. The novel use of elastomers allows the application of various forms of vortex generators to sections that have been problematic from engineering and cost considerations. A novel and efficient vortex generator profile is identified, which develops an additional co rotating vortex at low energy expenditure. The mechanisms allow for the application of transverse vortex generators, or Gurney Flaps/Lift Enhancement Tabs/Divergent Trailing Edges, to propellers, rotorblades, and to wings/flaps/control trailing edges. Cove Tabs are additionally described using an elastomeric transverse vortex generator to achieve performance improvements of a high lift device.Type: GrantFiled: July 8, 2010Date of Patent: October 28, 2014Inventor: Peter Ireland
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Patent number: 8870122Abstract: Methods and apparatus are provided to control flow separation of an ambient flow along a surface and about a turret, such as by reducing flow separation aft of the turret. By reducing flow separation, the resulting turbulence may be similarly reduced such that the performance of a system, such as a laser system, housed by the turret may be improved. To reduce flow separation, a motive flow may be provided by ejector nozzles that open through the surface and are positioned proximate to and aft of the turret relative to the ambient flow. The motive flow has a greater velocity than the ambient flow to thereby create a region aft of the turret of reduced pressure relative to an ambient pressure. Within this region of reduced pressure aft of the turret, a portion of the ambient flow mixes with the motive flow, thereby reducing or eliminating flow separation.Type: GrantFiled: July 23, 2010Date of Patent: October 28, 2014Assignee: The Boeing CompanyInventor: Alan Z. Ullman
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Patent number: 8844874Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising a balancer fitting, three lugs and a waiting link. When there is a failure in one of the lugs, the balancer fitting acts supporting loads in the transversal direction of the aircraft. The waiting link only acts if a failure in other link occurs. This waiting link is able to support loads in the longitudinal direction of the aircraft.Type: GrantFiled: October 5, 2011Date of Patent: September 30, 2014Assignee: Airbus Operations, S.L.Inventors: José Maria Pina López, Pablo Timoteo Sanz Martinez
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Patent number: 8840451Abstract: An aircraft cabin pressure control system outflow valve includes a frame, a valve element, and a vortex generator structure. The vortex generator structure is coupled to the valve element and is rotatable therewith, and includes a plurality of first vortex generators and a plurality of second vortex generators. The first vortex generators spaced are apart from each other and are configured to generate first vortices when the valve element is in an open position and fluid flows through the flow passage. The second vortex generators are formed in each of the first vortex generators and are spaced apart from each other. The second vortex generators are each configured to generate second vortices, which are smaller than the first vortices, when the valve element is in an open position and fluid flows through the flow passage.Type: GrantFiled: January 24, 2012Date of Patent: September 23, 2014Assignee: Honeywell International Inc.Inventors: Chuck Royalty, Kevin Allan Kingsley Jones, Ralph Warren Leclercq, Laura Tanner
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Patent number: 8800915Abstract: A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.Type: GrantFiled: March 30, 2012Date of Patent: August 12, 2014Assignee: Airbus Operations GmbHInventor: Martin Gerber
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Patent number: 8794571Abstract: This disclosure relates to a cooler for an aircraft cooling system. The cooler includes a matrix body in which a plurality of coolant channels are designed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body. The matrix body of the cooler is designed to form a section of the outer skin of the aircraft.Type: GrantFiled: March 5, 2010Date of Patent: August 5, 2014Assignee: Airbus Operations GmbHInventors: Torben Baumgardt, Ralf-Henning Stolte, Carsten Weber, Remy Reynaud, Christian Mueller
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Patent number: 8789789Abstract: 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: GrantFiled: May 23, 2011Date of Patent: July 29, 2014Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Donald C. Howe, Robert R. Wolz, Jimmy L. Hancock, Jr.
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Publication number: 20140203139Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes an expandable body having an aerodynamic cross-section that reduces parasitic air drag at any given thickness of the body, further being able to change its shape in flight in response to changes in the relative position of the sun; and a flexible solar PV system attached to the surface of the expandable body.Type: ApplicationFiled: November 27, 2013Publication date: July 24, 2014Applicant: SUNLIGHT PHOTONICS INC.Inventors: JOHN PETER MOUSSOURIS, SERGEY V. FROLOV, MICHAEL CYRUS
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Patent number: 8783617Abstract: An air vehicle fuselage adapted for transonic operation is disclosed. The fuselage has a body and a close-out. A lower surface of the body has a waterline value that varies along a fore-aft direction of the fuselage and is equal to a first waterline value at a forward end of the close-out and rise to a second waterline value at an aft end of the close-out. The lower surface has a drag-reduction blivet that includes a first region wherein the lower surface drops to a point comprising a third waterline value that is below the first waterline value and a first inward radius and then rises over a second region disposed aft of the first region wherein a second radius that is a minimum radius of the lower surface within the second region is greater than the first radius.Type: GrantFiled: April 12, 2012Date of Patent: July 22, 2014Assignee: Lockheed Martin CorporationInventors: Michael W. Harbeck, Brian Quayle
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Patent number: 8783611Abstract: An aircraft has an armor releasably attached to the body of an aircraft, an actuator connecting the armor to the body of the aircraft, and a control that, upon operation, actuates the actuator to release the armor from the body.Type: GrantFiled: October 11, 2007Date of Patent: July 22, 2014Assignee: Bell Helicopter Textron Inc.Inventors: Martin Peryea, Jon Stewart Tatro
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Patent number: 8783606Abstract: A method for improving the aerodynamic efficiency of the vertical tail of an aircraft includes varying the thickness of the trailing edge of the rudder as a function of the span of the vertical tail. This variation is intended to adapt the local value of the coefficient of lateral lift applied to the vertical tail closer to a maximum allowable value. The maximum allowable value is specifically the value at which a separation of the aerodynamic flow is observed on the surface of the vertical tail.Type: GrantFiled: April 4, 2012Date of Patent: July 22, 2014Assignee: Airbus Operations (SAS)Inventor: Alain Tanguy
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Patent number: 8763959Abstract: A two element aerofoil, and wing element based thereon, is provided, including a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil. A gap is provided between the primary aerofoil element and the secondary aerofoil element. The primary aerofoil element has at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of the secondary aerofoil element that is configured for minimizing or avoiding accretion of contaminant on the secondary aerofoil element when subjected to an airflow that includes the contaminant, at least at one design set of conditions. A method for designing a two element aerofoil is also provided.Type: GrantFiled: September 16, 2009Date of Patent: July 1, 2014Assignee: Israel Aerospace Industries Ltd.Inventors: Michael Shepshelovich, Danny Abramov
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Patent number: 8746616Abstract: An airplane comprises a twin-deck fuselage in which an upper deck support structure is utilized for carry-through of a mid-mount main wing box. The main landing gear of the airplane is mounted to the fuselage and is stowed in a non-pressurized area below the main wing box (enabled due to an optimized wing box geometry). A pressurized passageway/cargo/galley complex separates the main landing gear box and the main wing box. The upper deck is continuous, while the lower deck is separated by the wheel wells into two distinct fore and aft areas (for either cargo or passengers). The airplane further comprises an integrated vertical fin and an aft-extended pressurized deck area for reduced double-deck wetted area. More specifically, the double-deck pressurized fuselage structure is extended to form a blending structure to which a structural box of the vertical fin is attached.Type: GrantFiled: October 19, 2011Date of Patent: June 10, 2014Assignee: The Boeing CompanyInventors: Sergey D. Barmichev, Mithra M. K. V. Sandrithi, Kevin M. Retz
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Patent number: 8746624Abstract: An airfoil boundary layer control system may be provided. The airfoil boundary layer control system may include at least one airfoil that may include a first surface and a second surface coupled together at a leading edge and a trailing edge; at least one hollow chamber defined within the at least one airfoil; and an aperture defined in the airfoil and positioned substantially near the trailing edge, the aperture coupled in flow communication with the at least one hollow chamber; a pressure source coupled in flow communication with the at least one hollow chamber.Type: GrantFiled: May 26, 2009Date of Patent: June 10, 2014Inventor: David Birkenstock
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Patent number: 8740149Abstract: The present disclosure relates to flow channels comprising a channel length having a first portion approximately parallel to the maximum waterline thickness location of a body and at least a second portion non-parallel thereto, a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of the surface of the body, and at least a portion of the free edge being arcuate. A method comprises providing the fluid channel attachable to a body, modifying resultant vortices and reducing or minimizing shock formations or separation regions of the freestream.Type: GrantFiled: June 3, 2013Date of Patent: June 3, 2014Assignee: The Boeing CompanyInventor: Gregory G. Thumann
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Patent number: 8733696Abstract: A method for enhancing aerodynamic efficiency of a vertical tail includes varying the ratio between the control surface local chord and the vertical stabilizer local chord along the height of the vertical tail. This variation is configured to adapt the local value of the coefficient of the side lift applied to the vertical tail to a maximum acceptable value of the side lift coefficient. As a result, the aerodynamic efficiency is maximized by applying a coefficient approaching the maximum acceptable side lift coefficient.Type: GrantFiled: May 17, 2010Date of Patent: May 27, 2014Assignee: Airbus Operations (SAS)Inventor: Alain Tanguy
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Publication number: 20140131517Abstract: An aerodynamic blunt aft body (10) of a helicopter fuselage with two strakes (7, 8) along an aft surface (9) and/or respective left hand and right hand side fuselage surfaces (5, 6). Each strake (7, 8) is defined by first and second intersection lines (3, 4) resulting from intersections of horizontal planes (z) with the surface of the aft surface (9) or the respective left hand and right hand side fuselage surfaces (7, 8). The strakes are defined by a two or three dimensional spline (12) from the surface (2) towards the aft surface (9) inside said first and second intersection lines (3, 4) and inside the bounding box (15).Type: ApplicationFiled: July 17, 2013Publication date: May 15, 2014Inventors: Alessandro D'Alascio, Sebastian Mores, Frederic Le Chuiton, Marius Bebesel, Qinyin Zhang
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Patent number: 8714488Abstract: A method and apparatus comprising an adhesive layer and a conductive elastic material layer. The adhesive layer is capable of being placed in a channel for a joint. The adhesive layer is capable of resuming an original shape after being deformed. A conductive elastic material layer is on the adhesive layer. The coating covers the conductive elastic material layer and is capable of resuming the original shape after being deformed.Type: GrantFiled: January 8, 2009Date of Patent: May 6, 2014Assignee: The Boeing CompanyInventors: Richard W. Burns, Daryl Tryson, Michael F. McCracken
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Patent number: 8690107Abstract: A high-lift system with a main wing and adjustable flaps as well as guiding devices for holding the adjustable flaps and adjustment devices for adjusting the adjustable flaps, wherein the respective guiding device and/or adjustment device at least in part include/includes a fairing, including a flow influencing device for influencing the flow around the high-lift system, with at least one inlet line with at least one inlet that is situated on or below the bottom of the high-lift system, wherein, furthermore, at least one outlet line for air is provided that includes a fluid-communicating connection to the inlet line and includes at least one outlet situated at the top in the region of at least one adjustable flap of the high-lift system.Type: GrantFiled: June 22, 2012Date of Patent: April 8, 2014Assignee: Airbus Operations GmbHInventor: Burkhard Gölling
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Patent number: 8684310Abstract: A multilayer construction for aerodynamic riblets includes a first layer composed of a material with protuberances, the first layer material exhibiting a first characteristic having long-term durability and a second layer composed of a material, exhibiting a second characteristic with capability for adherence to a surface.Type: GrantFiled: January 29, 2009Date of Patent: April 1, 2014Assignee: The Boeing CompanyInventors: Diane C. Rawlings, Kevin R. Malone
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Patent number: 8686327Abstract: A missile nose fairing system includes sections attached at an aft end thereof to a missile body, a restraint for normally preventing aftward displacement of the plurality of sections, and a drive unit for releasing the restraint in response to a received signal. Each of the sections has an outer surface that converges to a common forward pointed tip for enclosing and protecting a guidance head when in an extended position and is retractable into a corresponding recessed region formed within a missile nose when the drive unit is activated releasing the restraint.Type: GrantFiled: October 14, 2010Date of Patent: April 1, 2014Assignee: Rafael Advanced Defense Systems Ltd.Inventor: Yacov Yacobovitch
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Patent number: 8678316Abstract: An array of aerodynamic riblets is created by a plurality of high stiffness tips with a layer supporting the tips in predetermined spaced relation and adhering the tips to a vehicle surface.Type: GrantFiled: January 29, 2009Date of Patent: March 25, 2014Assignee: The Boeing CompanyInventors: Diane C. Rawlings, Stephen Christensen
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Patent number: 8668164Abstract: An apparatus and method are provided for reducing the drag caused by a complex-section part in an airflow, for example the landing gear of an aircraft, making it possible to optimize the lift/drag ratio and to reduce the aerodynamic noise by reducing the local noise source. To do so, the complex-section part is masked with a special casing. More specifically, the aero-acoustically optimized complex-section metal mechanical part is fitted with an aerodynamically shaped cover made of several longitudinal parts articulated with hinges to facilitate their installation. This cover is attached to at least two supports placed away from one another along the axis of the part, each support locally mating with the section of the part.Type: GrantFiled: June 20, 2011Date of Patent: March 11, 2014Assignee: Airbus Operations (S.A.S.)Inventor: Christelle Seror Goguet
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Patent number: 8668166Abstract: A multilayer construction for an array of aerodynamic riblets incorporates a first layer composed of a material with protuberances, the first layer material having shape memory and a second layer composed of a material exhibiting a second characteristic with capability for adherence to a surface.Type: GrantFiled: January 29, 2009Date of Patent: March 11, 2014Assignee: The Boeing CompanyInventors: Diane C. Rawlings, Terry L. Schneider
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Patent number: 8662440Abstract: This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).Type: GrantFiled: September 17, 2008Date of Patent: March 4, 2014Assignee: Airbus Operations S.A.S.Inventors: Frederic Journade, Eric Renaud, Delphine Jalbert
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Patent number: 8657233Abstract: A tail-cone of an aircraft includes a skin provided with a movable fairing which, by a swing articulated mechanism, is supported on the skin in order to allow the opening/closing of the movable fairing and gain access to the inside of the tail-cone. The tail-cone includes actuators for operating the swing articulated mechanism in order to permit the automatic opening and closing of the movable fairing to be carried out.Type: GrantFiled: November 28, 2011Date of Patent: February 25, 2014Assignee: Airbus Operations, S.L.Inventors: Alejandro Meseguer Mata, Angel Postigo Rodriguez, Rafael Villanueva Montero, Daniel De La Sen Perez