Variable Patents (Class 244/46)
  • Patent number: 10967956
    Abstract: A fluid interaction apparatus includes a wing having a first configuration with a first profile drag coefficient and a second configuration with a second profile drag coefficient that is less than the first profile drag coefficient. The fluid interaction apparatus further includes a body having a longitudinal axis, wherein the body is coupled to the wing. The fluid interaction apparatus further includes an actuator configured to change the wing from the first configuration when moving in a first direction relative to the body to the second configuration when moving in a second direction relative to the body, the second direction having a substantial component parallel to the longitudinal axis of the body.
    Type: Grant
    Filed: May 21, 2018
    Date of Patent: April 6, 2021
    Inventor: Paul Neiser
  • Patent number: 10870488
    Abstract: A braced wing aircraft with a fuselage and a fixed wing arrangement, the fixed wing arrangement comprising at least two braced wings that are arranged laterally and opposite to each other on the fuselage, each one of the at least two braced wings comprising at least one upper wing and at least one lower wing which are staggered and interconnected at a predetermined transition region, the at least one upper wing being connected to the fuselage at an associated upper wing root and the at least one lower wing being connected to the fuselage at an associated lower wing root.
    Type: Grant
    Filed: October 8, 2018
    Date of Patent: December 22, 2020
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Martin Blacha, Axel Fink
  • Patent number: 10814955
    Abstract: An aircraft includes a boundary layer ingestion fan defining a centerline and including a plurality of fan blades rotatable about the centerline. The aircraft also includes a fuselage extending between a forward end and an aft end along a longitudinal direction, the boundary layer ingestion fan positioned within the fuselage at the aft end of the fuselage, the fuselage defining an inlet upstream of the boundary layer ingestion fan extending at least about 180 degrees around the centerline of the boundary layer ingestion fan, the fuselage further defining an exhaust downstream of the boundary layer ingestion fan.
    Type: Grant
    Filed: February 7, 2018
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Jixian Yao, Nikolai N. Pastouchenko, Patrick John Lonneman, Patrick Michael Marrinan, Richard David Cedar
  • Patent number: 10661893
    Abstract: A lightweight flying vehicle includes a carrier body, at least two fan-tube propulsion devices, two steering devices and a flight wing. The fan-tube propulsion devices are respectively disposed at two opposite sides of the carrier body and have a sufficient propulsion force. The steering device is disposed on a moving line of the airflow discharged from the fan-tube propulsion devices and is configured to change a direction of the airflow discharged from the air discharge opening, so that the lightweight flying vehicle is in a high-speed flight mode. The flight wing can provide a lift power in the high-speed flight mode.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: May 26, 2020
    Inventor: Yao-Chang Lin
  • Patent number: 10597136
    Abstract: An aircraft including a wing, a fuselage and at least one brace extending between the wing and the fuselage. The brace houses at least one fluid transfer line between the wing and the fuselage, such as an engine air bleed line, a hydraulic line or a fuel pipe. Use in particular to equip high-winged aircraft.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: March 24, 2020
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Jaime Genty De La Sagne
  • Patent number: 10556666
    Abstract: Disclosed herein is an aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. A strut inboard end portion is coupled to and extends from the body and a strut outboard end portion is coupled to and extends from an intermediate portion of the wing. The wing further comprises a first thinned portion adjacent the intermediate portion of the wing. An overall thickness of the first thinned portion of the wing decreases and increases in a spanwise direction along the wing. The strut further comprises a second thinned portion adjacent the outboard end portion of the strut. An overall thickness of the second thinned portion of the strut decreases and increases in a spanwise direction along the strut.
    Type: Grant
    Filed: March 31, 2017
    Date of Patent: February 11, 2020
    Assignee: The Boeing Company
    Inventors: Anthony J. Sclafani, Adam D. Grasch, Christopher K. Droney, Neal A. Harrison
  • Patent number: 10370082
    Abstract: An aircraft includes: a fuselage having opposing leading and trailing extremities along a vertical axis; a fixed wing airframe having opposed at least two main wings connected to the fuselage and extending on a horizontal axis; at least two electric coplanar main wing motors respectively attached to the main wings; a duct frame attach to the trailing extremity of the fuselage; at least two horizontal stabilizers connected to the duct frame and extending on the horizontal axis; an electric tail motor fitted an inner side of the duct frame; multiple battery packs installed inside the fuselage and suitable for supply power to the main wing motors and the tail motor; and support beams suitable for connecting the duct frame to the fuselage.
    Type: Grant
    Filed: December 27, 2016
    Date of Patent: August 6, 2019
    Assignee: KOREA ADVANCED INSTITUTE OF SCIENCE AND TECHNOLOGY
    Inventors: Dongsoo Har, Celso Moraes, Dongsuk Kum
  • Patent number: 10273001
    Abstract: Systems, apparatuses, and methods are provided herein for unmanned flight optimization. A system for unmanned flight comprises a set of motors configured to provide locomotion to an unmanned aerial vehicle, a set of wings coupled to a body of the unmanned aerial vehicle via an actuator and configured to move relative to the body of the unmanned aerial vehicle, a sensor system on the unmanned aerial vehicle, and a control circuit. The control circuit being configured to: retrieve a task profile for a task assigned to the unmanned aerial vehicle, cause the set of motors to lift the unmanned aerial vehicle, detect condition parameters based on the sensor system, determine a position for the set of wings based on the task profile and the condition parameters, and cause the actuator to move the set of wings to the wing position while the unmanned aerial vehicle is in flight.
    Type: Grant
    Filed: September 7, 2017
    Date of Patent: April 30, 2019
    Assignee: Walmart Apollo, LLC
    Inventors: Robert L. Cantrell, John P. Thompson, David C. Winkle, Michael D. Atchley, Donald R. High, Todd D. Mattingly, John J. O'Brien, John F. Simon
  • Patent number: 10139838
    Abstract: Embodiments for managing drones by a processor are described. A plurality of drones are detachably coupled to each other at a first location. While the plurality of drones are detachably coupled to each other, the plurality of drones travel from the first location to a second location. At least one of the plurality of drones detaches from the others of the plurality of drones at the second location. The at least one detached drone travels from the second location to a third location.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: November 27, 2018
    Assignee: INTERNATIONAL BUSINESS MACHINES CORPORATION
    Inventors: David B. Lection, Sarbajit K. Rakshit, Mark B. Stevens, John D. Wilson
  • Patent number: 10131424
    Abstract: A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: November 20, 2018
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Axel Fink, Martin Blacha
  • Patent number: 9950780
    Abstract: An apparatus of an aircraft, the apparatus may include a wing comprising an unfixed portion and a fixed portion. The unfixed portion movably may connect to the fixed portion. The unfixed portion may include a rotating portion to rotate the unfixed portion between a flight position and a folded position. The fixed portion may connect to the unfixed portion of the wing. A joint may allow rotation of the unfixed portion of the wing with respect to the fixed portion of the wing about a rotation axis.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: April 24, 2018
    Assignee: THE BOEING COMPANY
    Inventors: Gregory M. Santini, Seiya Sakurai
  • Patent number: 9903526
    Abstract: A force engine operable to counterbalance a load. The force engine includes one or more energy reservoirs operable to store energy. The one or more energy reservoirs are operable to generate a force to balance the load through the displacement in an operating mode. A traveling member is hingedly connected to the one or more energy reservoirs. The force generated by the one or more energy reservoirs is transferred to the load through the traveling member and an associated linkage. A variable member is coupled to the one or more energy reservoirs. In the adjusting mode the variable member is displaced to configure an operating relationship between the one or more energy reservoirs and the traveling member. A release interacts with the variable member to fix a position of the variable member.
    Type: Grant
    Filed: April 29, 2011
    Date of Patent: February 27, 2018
    Inventors: Jonathan Roberts, Clark Davis, Ian Davis, Jonathan George
  • Patent number: 9802083
    Abstract: A throwing and/or catching toy includes a generally elongated spheroidal body defining a longitudinal axis. A length of the body is longer than an equatorial diameter. A lift-generating wing is non-movably attached to the body near and/or at a center of the wing. At least one finger hold extension extends from a distal end of either a left or right wing portion. The finger hold extension is configured to allow a user to throw the toy in a discus-launched manner and the body is configured to be caught by the user. The lift-generating wing may be made as an injection molded, polymer wing. A manual adjuster may be associated with and controlling the shape of a horizontal stabilizer. A front end of the elongated body may be a resilient foam having a Shore A durometer hardness equal to or less than 25.
    Type: Grant
    Filed: March 24, 2016
    Date of Patent: October 31, 2017
    Inventor: Marc Gregory Martino
  • Patent number: 9714087
    Abstract: A vertical takeoff/landing capable, multi-engine aircraft with an airfoil without elevator or rudder surfaces is provided. Strut apertures accommodate vertical and horizontal translation of the airfoil in reference to engine supporting struts which are disposed through the apertures, opposite ends of the struts extending to opposite sides of the airfoil, wherein the struts are adjustably attached to the airfoil. A first and second plurality of engines are attached to ends of the struts, an attachment position of the plurality of engines to the struts is horizontally adjustable. A computerized engine controller, controls thrusts of the engines, to enable the aircraft to vertically lift off/land and re-orient itself to horizontally fly, and perform thrust-initiated elevator and rudder emulating flight. An external payload-to-delivery mating mechanism is attached to the bottom of the payload, which mates to a pole leading to the payload receptacle. Transceivers facilitate precise transfer of the payload.
    Type: Grant
    Filed: December 26, 2014
    Date of Patent: July 25, 2017
    Inventor: Hari Matsuda
  • Patent number: 9702254
    Abstract: Lift propulsion and stabilizing system and procedure for vertical takeoff and landing aircraft that consists in applying simultaneously and combined as lifters during the initial portion of the climb and at the end of the descent of: a) some fans or electric turbines, EDF, and b) at least one rotor with external blades and/or rotary and/or c) the engine flow directed downwards and/or d) pressure air jets injected on leading edges control fins, and/or e) water jets and/or f) supplemented with aerodynamic lift produced during frontal advance of the aircraft, the stabilization is achieved by the gyroscopic stiffness of the rotor and two or more lifting fans oscillating fins and/or air jets located on two or stabilizers more peripheral points in a plane perpendicular to the vertical axis of the aircraft.
    Type: Grant
    Filed: April 12, 2011
    Date of Patent: July 11, 2017
    Inventor: Manuel M. Saiz
  • Patent number: 9359073
    Abstract: An aircraft tail rotor system is provided and includes a rotating element, a translating element and a structure including a first bearing in series with a second bearing, the first bearing including a component rotatable with and movable within the rotating element in accordance with translational movement of the translating element. The structure is configured to selectively use the second bearing to prevent transmission of rotational energy from the rotating element to the translating element in an event of a seizing of the first bearing.
    Type: Grant
    Filed: August 2, 2013
    Date of Patent: June 7, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: John E. Hewitt
  • Patent number: 9321521
    Abstract: An apparatus has a first structure, a second structure, and an activated seal. The second structure has a first position adjacent to the first structure such that the first structure is not in contact with the second structure. The activated seal is attached to at least one of the first structure and the second structure. The activated seal has a variable stiffness that may be changed in response to a stimuli such that the activated seal is capable of being deformed when at least one of the first structure and the second structure are moved relative to each other.
    Type: Grant
    Filed: June 10, 2013
    Date of Patent: April 26, 2016
    Assignee: THE BOEING COMPANY
    Inventors: Christopher P. Henry, Geoffrey P. McKnight, Guillermo A. Herrera, Robert E. Doty, Richard Lee Clemons, Donald V. Drouin, Jr.
  • Patent number: 9012825
    Abstract: Disclosed are systems and methods for retaining and deploying a plurality of canards and canard covers on a projectile. The projectile includes a projectile housing defining an interior chamber and a longitudinal axis, canards rotatably mounted to the housing, canard covers, a bobbin movably disposed in the interior chamber of the housing along the longitudinal axis, and rocker arms. The canards mounted for movement from a stowed position to a deployed position. The canard covers have a hook element and are adapted to cover respective slots formed in the housing. The bobbin has first and second ends and a retaining surface proximate the second end. Rocker arms have a first and second arm end, with a canard retaining slot defined therebetween. The first arm end includes a latch element for engaging with the canard cover element, and the second arm end is positioned proximate the retaining surface.
    Type: Grant
    Filed: January 23, 2013
    Date of Patent: April 21, 2015
    Assignee: Simmonds Precision Products, Inc.
    Inventors: Matt Plumer, Jeff Gibson, Jim Byrne, Brian Richardson
  • Publication number: 20150097076
    Abstract: An aircraft includes a fuselage, a wing, and a decoupled joint interconnecting the fuselage and the wing. The decoupled joint can be an active suspension system. A method of adapting an aircraft to attenuate forces between a main wing and a fuselage thereof includes providing a plurality of sensors upon the aircraft, configured for sensing motion and/or mechanical stress of the main wing and/or the fuselage and producing signals indicative thereof, and providing a plurality of active suspension elements interconnecting the wing and the fuselage, the active suspension elements being configured to move at least in response to the signals to adjust a position of the wing with respect to the fuselage.
    Type: Application
    Filed: October 9, 2013
    Publication date: April 9, 2015
    Inventors: Branko Lakic, Jonathan B Vance
  • Patent number: 8985504
    Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: March 24, 2015
    Inventors: Tony Shuo Tao, Nathan Olson, Carlos Thomas Miralles, Robert Nickerson Plumb
  • Patent number: 8895908
    Abstract: A low cost, lightweight frangible wing slot seal can be applied to a guidance wing slot of a folding fin aerial rocket or missile, providing a barrier against exposure of internal missile components to external contaminants, while allowing unhindered deployment of missile guidance wings simply by bursting through the seals. The simple design is nearly foolproof, and has no impact the likelihood of weapon failure. The seal is a flexible sheet which is sufficiently thin so as not to exceed the required volume envelope of the missile. The sheet includes a burst seam, which is breached when impacted by the leading edge of a deploying wing. No additional wing deployment force is required, and after deployment the seal has minimal impact on the aerodynamic performance of the wing.
    Type: Grant
    Filed: April 7, 2011
    Date of Patent: November 25, 2014
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: William D. Barry, Robert Winkler, John R. Franzini, Kenneth D. Cleveland, Adam Butland
  • Patent number: 8864065
    Abstract: An air vehicle wing includes foldable ribs coupled to a leading-edge spar. The ribs each have multiple rib segments which are foldable (hinged) relative to each other. Extension linkages, each with multiple extension linkage segments, pass through openings in the rib segments, and may be coupled to the rib segments with pin couplings, able to change relative angle between the individual rib segments and the extension linkage segments to which they are coupled. A skin may cover the ribs, to provide an outer surface of the wing that may be unfolded as the wing is expanded from a stowed, small-chord condition, to a deployed, large-chord condition.
    Type: Grant
    Filed: October 25, 2012
    Date of Patent: October 21, 2014
    Assignee: Raytheon Company
    Inventors: Frederick B Koehler, Terry M Sanderson, Jack W Reany
  • Patent number: 8809755
    Abstract: The present invention relates to an aircraft, missile, projectile or underwater vehicle with an improved control system, an improved control system and a method of maneuvering an aircraft, missile, projectile or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, projectile or underwater vehicle with control surfaces that are movable along a track. The present invention further relates to a method of controlling a aircraft, missile, projectile or underwater vehicle using such a control system. One of the technical advantages of the control system on a track (or “tracked control surface”) over other aircraft, missile, projectile or underwater vehicle control systems is that the tracked control surface system enables the aircraft, missile, projectile or underwater vehicle to have an unlimited number of configurations, each configuration being tailored to the specific stability or maneuverability requirements during a specific portion of the flight.
    Type: Grant
    Filed: December 2, 2005
    Date of Patent: August 19, 2014
    Assignee: Orbital Research Inc.
    Inventors: Mehul Patel, T. Terry Ng, Paul Suchy
  • Patent number: 8757538
    Abstract: An aircraft having a variable geometry for adapting the flight characteristics to different flight situations includes a fuselage with a pair of wings projecting on both sides of the fuselage in the transverse direction (y), each of which wings has an inner wing section arranged stationarily with respect to the fuselage and an outer wing section adjacent thereto and pivotable about a pivot axis. The pivot axis is oriented in a direction deviating from the longitudinal direction (x) of the aircraft by a maximum of 40°.
    Type: Grant
    Filed: October 10, 2011
    Date of Patent: June 24, 2014
    Assignee: EADS Deutschland GmbH
    Inventor: Jost Seifert
  • Publication number: 20140131511
    Abstract: An aircraft lifting surface attached to the rear or frontal end of the aircraft fuselage with a variable sweep angle ? in an inboard part and with a constant sweep angle ?1 in an outboard part. The aircraft lifting surface can be for example a horizontal tail plane or a vertical tail plane attached to the rear end fuselage or a canard attached to the frontal end fuselage.
    Type: Application
    Filed: July 16, 2013
    Publication date: May 15, 2014
    Inventors: Angel Pascual Fuertes, Sergio Rodriguez Sanchez
  • Patent number: 8714476
    Abstract: A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example located at the trailing edge of the wing. The lock may be a mechanical mechanism that automatically locks the wing in the deployed state, preventing the wing from returning to the stowed state.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: May 6, 2014
    Assignee: Raytheon Company
    Inventors: Jack W. Reany, Terry M. Sanderson
  • Patent number: 8703268
    Abstract: A panel structure includes a composite facesheet and a stiffening core having a plurality of core members in an intersecting web configuration provided on the composite facesheet.
    Type: Grant
    Filed: February 2, 2010
    Date of Patent: April 22, 2014
    Assignee: The Boeing Company
    Inventors: Christopher P. Henry, Sloan P. Smith, Andrew C. Keefe
  • Patent number: 8651431
    Abstract: A method and apparatus for improved aircraft control through the use of adjustable winglets. The adjustable winglets are located at the terminal ends of an aircraft's wings and may pivot about an axis parallel to the yaw axis of the aircraft. The adjustable winglets may also include outboard ailerons for improved control of the aircraft.
    Type: Grant
    Filed: August 9, 2011
    Date of Patent: February 18, 2014
    Assignee: The Boeing Company
    Inventors: Edward Val White, Blaine Knight Rawdon, Zachary C. Hoisington, Christopher K. Droney
  • Patent number: 8590831
    Abstract: An aircraft includes a fuselage and takeoff and landing wings that are extended at takeoff and landing and serve as the main aerodynamic elements producing the lift. The takeoff and landing wings are in a retracted position in cruising flight to attain a minimum possible drag coefficient of the aircraft and, as a result, reduce fuel requirements in the cruising configuration significantly. When retracted, the takeoff and landing wings are integrated compactly into the fuselage surface. The retracted takeoff and landing wings are fixed in position by retracted position locks of the fuselage. A takeoff and landing wing has a turbine blade profile in cross-section. A takeoff and landing wing has longitudinal rows of slots simulating the operation of a slat and a two-slot flap. The slots are closed with shutters on the outer side of the wing.
    Type: Grant
    Filed: February 8, 2011
    Date of Patent: November 26, 2013
    Inventor: Sergey Nikolaevich Afanasyev
  • Patent number: 8586176
    Abstract: A plurality of reversible active composite materials are disclosed, including composites based on a shape memory alloy member (SMA) and a shape memory polymer member (SMP), as well as composites based on two different SMP members. Each different member (SMA or SMP) will be trained to remember a specific shape at a specific temperature. Where two different SMP members are employed, the members exhibit different glass transition temperatures. Such composite materials can be implemented in many form factors, including two generally planar members, a single generally planar SMP member with SMA fibers distributed throughout the SMP, and a SMA fiber/wire coated with a SMP coating. In particular, the SMA fiber/wire coated with a SMP layer can be used to form helical coils that can be used in paired hinges to achieve reversible bending of a structure into which such paired hinges are incorporated.
    Type: Grant
    Filed: November 3, 2008
    Date of Patent: November 19, 2013
    Assignee: University of Washington
    Inventors: Minoro Taya, Yuanchang Liang
  • Patent number: 8544790
    Abstract: The aircraft includes a fuselage, horizontal front and tail empennages and take-off and landing wings, which wings are jointed to the fuselage by means of attachment joints, the axes of which are situated above the fuselage central line along the longitudinal axis of symmetry thereof so that the take-off and landing wings are arranged below the attachment joints along the longitudinal axis of symmetry of the fuselage. The outer surface of the wings is the extension of the outer surface of the fuselage and in a stow position the take-off and landing wings cover at least 30% of the fuselage surface area between the horizontal front and tail empennages.
    Type: Grant
    Filed: June 1, 2009
    Date of Patent: October 1, 2013
    Inventor: Sergey Nikolaevich Afanasyev
  • Patent number: 8474747
    Abstract: An aircraft (1) horizontal stabilizer (2) which can vary its sweep angle (6) by rotating around an essentially vertical axis (4) with respect to the direction of flight of the aircraft (1) when the aircraft (1) is in flight at high speeds, close to the speed of sound, this axis (4) being contained in the plane of symmetry of the aforementioned aircraft (1), the aforementioned horizontal stabilizer (2) being is a single and structurally continuous component such that it does not transmit a bending moment to the fuselage (14) structure of the aircraft (1), which permits it to be of reduced weight, such that the horizontal stabilizer (2) rotates in a single way and a single direction around the axis (4) to achieve the sweep angle (6) required for high-speed flight.
    Type: Grant
    Filed: February 23, 2010
    Date of Patent: July 2, 2013
    Assignee: Airbus Operations, S.L.
    Inventor: Raul Carlos Llamas Sandin
  • Patent number: 8444082
    Abstract: An air vehicle can be folded into or unfolded from a compact tubular storage container without assembly or disassembly of the air vehicle. The air vehicle includes a fuselage, two aerodynamic surfaces rotatably mounted on the fuselage along a common axis with at least one pivot mechanism, and at least one spring mechanism configured to deploy the aerodynamic surfaces so they extend outwardly from the body. In a stowed configuration, both aerodynamic surfaces are parallel to the fuselage for stowage of the aircraft in a container. Each aerodynamic surface has a winglet located at an outer edge of the tail portion of the aerodynamic surface, and a rudder on each winglet. The aircraft does not require a vertical stabilizer or rudder system on the fuselage. An outer backward-swept wing portion can be unfolded from the outer edge of each aerodynamic surface to increase the wing aspect ratio.
    Type: Grant
    Filed: August 19, 2010
    Date of Patent: May 21, 2013
    Assignee: The United States of America, as represented by the Secretary of the Navy
    Inventor: Richard J Foch
  • Publication number: 20130099049
    Abstract: A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example located at the trailing edge of the wing. The lock may be a mechanical mechanism that automatically locks the wing in the deployed state, preventing the wing from returning to the stowed state.
    Type: Application
    Filed: October 21, 2011
    Publication date: April 25, 2013
    Inventors: Jack W. Reany, Terry M. Sanderson
  • Patent number: 8371520
    Abstract: A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: February 12, 2013
    Inventor: William Craig Easter
  • Patent number: 8360356
    Abstract: A flying apparatus having a thrust directing wing is disclosed. The flying apparatus can include a wing that receives a thrust flow from a thrust flow generator, and selectively redirect the flow in at least one of a plurality of directions. The wing can redirect the thrust flow so as to generate vertical thrust, forward thrust, and combinations thereof. The thrust flow generator can include a gas turbine engine, which can include two rotating shafts and a common burner, with each shaft coupling a compressor with a turbine.
    Type: Grant
    Filed: July 13, 2009
    Date of Patent: January 29, 2013
    Inventor: W. Eric Moore
  • Patent number: 8360357
    Abstract: An aircraft has a fuselage a wing integral with the fuselage at a point on a rigid central wing box. Sections of the wing are located on sides of the central wing box and integral and fixed relative to the wing box to form a rigid wing. The wing is mounted movably in translation relative to the fuselage along a longitudinal direction of the aircraft parallel to an axis of the fuselage between an extreme forward position and an extreme rear position of a point of reference of the wing. The central wing box is determined in the front by a wing box front spar, in the rear by a wing box rear spar, and laterally by root ribs. Sections of the wing include external front and external rear spars integral with and fixed relative to the wing box front spars and wing box rear spars to form the rigid wing.
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: January 29, 2013
    Assignee: Airbus Operations SAS
    Inventors: Olivier Cazals, Thierry Druot
  • Patent number: 8356770
    Abstract: An aircraft tail section has a first tail component and a second tail component, the first tail component being positioned further forward than the second tail component with respect to a nose of the aircraft. Each tail component has two surfaces, each of the two surfaces of at least one of the first and second tail components comprises a solar panel configured to collect solar energy. Each tail component is rotatable with respect to a centerline of the aircraft such that an offset angle of between zero degrees and 180 degrees is formed between corresponding surfaces of the first and second tail components. Preferably, the tail components are rotated into (i) a takeoff and landing configuration that is substantially horizontal, and (ii) a crosswise configuration during flight such that collection of solar energy is maximized.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: January 22, 2013
    Assignee: Aurora Flight Sciences Corporation
    Inventor: Robert Parks
  • Patent number: 8336811
    Abstract: An aircraft includes a reference system including a longitudinal X axis, a vertical Z axis perpendicular to the X axis, and a lateral Y axis perpendicular to the plane defined by the X and Z axes, a fuselage, a wing affixed to an upper central part of the fuselage, a set of rear airfoils situated behind the wing, and propulsion engines mounted on the wing, where the wing, the set of rear airfoils and the propulsion engines are parts of an aero-propulsive unit forming a structure independent of the fuselage, and where the aero-propulsive unit is connected to the fuselage by a six degrees of freedom connection system using arms with lengths modified to control a position of the aero-propulsive unit relative to the fuselage along the X, Y and Z axes and in rotation about the X, Y and Z axes, during flight.
    Type: Grant
    Filed: August 14, 2009
    Date of Patent: December 25, 2012
    Assignee: Airbus Operations SAS
    Inventors: Olivier Cazals, Thierry Druot
  • Publication number: 20120267473
    Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently mounted trailing edges opposed by fuselage-house house deflecting actuator horns (621,622). Embodiments include one or more rudder elements (1045, 1046,1145, 1146,1245, 1345, 1346,1445, 1446,1545, 1546) which may be rotatably attached and actuated by an effector member (1049,1149,1249,1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.
    Type: Application
    Filed: September 9, 2010
    Publication date: October 25, 2012
    Inventors: Tony Shuo Tao, Nathan Olson, Carlos Thomas Miralles, Robert Nickerson Plumb
  • Patent number: 8292216
    Abstract: A method and apparatus may be present for moving a wing. A plurality of lifting assemblies may be attached to a first plurality of channels in a ring associated with the wing of an aircraft. A plurality of base assemblies may be attached to a plurality of fittings with a second plurality of channels associated with a fuselage of the aircraft. The plurality of lifting assemblies may be moved away from the plurality of base assemblies using a plurality of biasing systems such that the ring may move away from the fuselage.
    Type: Grant
    Filed: December 16, 2009
    Date of Patent: October 23, 2012
    Assignee: The Boeing Company
    Inventor: William Elmer Rumberger, Jr.
  • Patent number: 8258447
    Abstract: A frangible seal includes a first region penetratable by a deployable structure configured to selectably extend through an opening in a housing and extend beyond an outer surface of the housing, and a second region configured to adhere to a portion of the outer surface of the housing surrounding the opening. The first region and the second region includes a polymer layer having a metalized surface (e.g., aluminized polyimide) and a non-metalized surface, and an ablative coating provided on the metalized surface of the polymer layer.
    Type: Grant
    Filed: December 1, 2009
    Date of Patent: September 4, 2012
    Assignee: Raytheon Company
    Inventors: Alexandra L. Blake, David B. Hatfield, Rudy A. Eisentraut, Peter J. Drake
  • Patent number: 8201773
    Abstract: A composite flexible and aerodynamic load bearing wing structure suitable for compact unmanned vehicles, is described. Flexible printed circuitry and micro fuel cells can be incorporated as, or part of, the flexible aerodynamic structure. Accordingly, the overall system configuration can be optimized with respect to weight, space and size requirements. The flexible aerodynamic structure for the unmanned vehicle may be configured with a flexible dielectric substrate having an electrical contact on at least one surface of the substrate, and a flexible printed circuit disposed upon the substrate. The printed circuit can flex with the substrate and the substrate, with the printed circuit, to form a load lifting aerodynamic wing configuration when unfolded from a folded position.
    Type: Grant
    Filed: July 2, 2008
    Date of Patent: June 19, 2012
    Assignee: The United States of America as represented by Secretary of the Navy
    Inventors: Jayson T. Durham, Joshua Blanchi
  • Publication number: 20120119017
    Abstract: A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft.
    Type: Application
    Filed: September 2, 2011
    Publication date: May 17, 2012
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Daniel B. Robertson, Kirk L. Groninga
  • Publication number: 20120091263
    Abstract: A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a complementary hinge interface on another wing panel. When a first and second wing panel are coupled together via the rotational interface, they can rotate with respect to each other within a predetermined angular range. The aircraft further comprises a control system that is configured to acquire aircraft operating information and atmospheric information and use the same alter the angle between the wing panels, even if there are multiple wing panels. One or more of the wing panels can include photovoltaic cells and/or solar thermal cells to convert solar radiation energy or solar heat energy into electricity, that can be used to power electric motors.
    Type: Application
    Filed: October 13, 2011
    Publication date: April 19, 2012
    Applicant: AURORA FLIGHT SCIENCES CORPORATION
    Inventor: ROBERT PARKS
  • Publication number: 20120085858
    Abstract: An aircraft having a variable geometry for adapting the flight characteristics to different flight situations includes a fuselage with a pair of wings projecting on both sides of the fuselage in the transverse direction (y), each of which wings has an inner wing section arranged stationarily with respect to the fuselage and an outer wing section adjacent thereto and pivotable about a pivot axis. The pivot axis is oriented in a direction deviating from the longitudinal direction (x) of the aircraft by a maximum of 40°.
    Type: Application
    Filed: October 10, 2011
    Publication date: April 12, 2012
    Applicant: EADS Deutschland GmbH
    Inventor: Jost Seifert
  • Patent number: 8146855
    Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.
    Type: Grant
    Filed: September 3, 2008
    Date of Patent: April 3, 2012
    Inventor: Anvar Ismailov
  • Patent number: 8115149
    Abstract: A Hybrid Projectile is provided for delivering an explosive payload to a target wherein the Hybrid Projectile may be steered in flight using relatively inexpensive means. The Hybrid Projectile is exteriorly configured in the same physical exterior configuration of conventional ammunition of various standard types so it can be launched in conventional manner from the same weapon systems. However, internal features allow the Hybrid Projectile to be transformed in flight from a command signal to deploy wings and fins, and in some projectiles to telescope open to deploy such wings and fins. An inexpensive televisual means is activated in the fore region of the round which through RF uplink command can be used to select a path, while motors on the wings can then be used to more precisely glide the projectile to a target, or otherwise to abort the target run.
    Type: Grant
    Filed: July 21, 2009
    Date of Patent: February 14, 2012
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Leon R. Manole, Ernest L. Logsdon, Jr., Mohan J. Palathingal, Anthony J. Sebasto
  • Patent number: 8056853
    Abstract: A reconfigurable air vehicle wing may be selectively reconfigured to increase its chord. The wing has a leading edge portion and a trailing edge portion that are moved relative to one another to change the chord of the wing. The wing may be reconfigured from a compact configuration with a smaller chord, to and expanded configuration with a larger chord. The wing may include a foam material that forms part of the outer surface of the wing when the wing is in the expanded configuration. The foam may be a shape memory foam. Alternatively the leading edge section and the trailing edge section may be composed substantially fully of rigid materials. In either case the trailing edge section may be hingedly coupled to the leading edge section.
    Type: Grant
    Filed: November 25, 2008
    Date of Patent: November 15, 2011
    Assignee: Raytheon Company
    Inventors: Rudy A. Eisentraut, Terry M. Sanderson, Brian J. Gowler
  • Patent number: 8014910
    Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.
    Type: Grant
    Filed: May 4, 2006
    Date of Patent: September 6, 2011
    Assignee: Airbus France
    Inventors: Gerard Mathieu, Franck Delaplace, Xavier Le Tron