With Thrust Diverting Patents (Class 244/12.5)
  • Patent number: 11897610
    Abstract: An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body.
    Type: Grant
    Filed: May 14, 2021
    Date of Patent: February 13, 2024
    Assignee: The Boeing Company
    Inventors: Keith A. Etling, Hilary G. Knight
  • Patent number: 11718394
    Abstract: Tail boom drive systems for helicopters are described which utilize a fan internal to the tail boom to provide yaw control, and an external propulsor to provide forward thrust. In one embodiment, the tail boom drive system includes a shaft, a fan, and a propulsor. The shaft is disposed lengthwise within an interior space of the tail boom, and the shaft has a first end and a second end. The fan is mechanically coupled coaxially to the shaft within the interior space between the first end and the second end, and the fan generates a variable airflow directed towards the second end that is ejected from the interior space substantially perpendicular to the tail boom. The propulsor is external to the tail boom and is mechanically coupled coaxially to the shaft at the second end, and the propulsor generates a variable thrust directed towards the first end.
    Type: Grant
    Filed: April 16, 2019
    Date of Patent: August 8, 2023
    Assignee: The Boeing Company
    Inventors: Michael J. McNulty, Glenn T. Pyle
  • Patent number: 11628929
    Abstract: Air acceleration at slot of aircraft wing. In one embodiment, a wing includes an air duct configured to transport air in a spanwise direction along a leading edge of the wing from an air supply source of the aircraft. The wing further includes a discharge duct configured to transport the air in an aft direction from the air duct to an aft end of the wing, and one or more nozzles disposed on the aft end of the wing and configured to accelerate air into a slot between the wing and a flap of the aircraft to increase lift and reduce drag for the wing.
    Type: Grant
    Filed: October 20, 2021
    Date of Patent: April 18, 2023
    Assignee: The Boeing Company
    Inventors: Arvin Shmilovich, Abdollah Khodadoust, Christopher Colletti
  • Patent number: 11597509
    Abstract: An aircraft that closely integrates thrust and aerodynamics to achieve VTOL flight, forward flight, and smooth transitions from VTOL to forward flight. The invention combines a Box wing, Ducted Rotors and movable Flaperons for VTOL and sustained forward flight of an aircraft. In forward flight, the concept uses a plurality of fixed Ducted Rotors to not only provide thrust, but also enhance dynamic lift and controllability by interacting closely with the two fixed primary lifting bodies of each ducted wing section. In VTOL flight and transitioning to forward flight, the Ducted Rotors direct air through movable Flaperons attached to the trailing end of the ducted wings, providing smooth power, controllability, and aircraft orientation throughout transition. Throughout all phases of flight, differential actuation of Ducted Rotors and Flaperons provide control.
    Type: Grant
    Filed: November 2, 2021
    Date of Patent: March 7, 2023
    Inventor: Reynaldo Thomas Alfaro
  • Patent number: 11507115
    Abstract: A technique for controlling an unmanned aerial vehicle (UAV) includes monitoring a sensed airspeed of the UAV, obtaining a commanded speed for the UAV, wherein the commanded speed representing a command to fly the UAV at a given speed relative to an airmass or to Earth, and when the commanded speed is greater than the sensed airspeed, using the commanded speed in lieu of the sensed airspeed to inform flight control decisions of the UAV.
    Type: Grant
    Filed: October 9, 2019
    Date of Patent: November 22, 2022
    Assignee: WING Aviation LLC
    Inventors: Kevin Jenkins, Brandon Jones
  • Patent number: 11505316
    Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.
    Type: Grant
    Filed: November 5, 2019
    Date of Patent: November 22, 2022
    Assignee: JETOPTERA, INC.
    Inventor: Andrei Evulet
  • Patent number: 11299284
    Abstract: This instant invention provides an airplane design mainly to eject rearward the high-speed exhaust gas from the engine of the airplane to flow through the upper surface of the wing, such that the forward propulsion forcing can be obtained via rearward ejecting the high-speed exhaust gas to push the air rearward, and also larger uplift forcing induced by a larger velocity difference vertically across the wing can be obtained to ascend the airplane at the same time. This velocity difference is generated because the air over the wing is accelerated by the ejected high-speed exhaust gas, but the air below the wing stays the same velocity, such that a bigger velocity difference is directly produced vertically across the wing, and thus more uplift forcing can be provided to ascend the airplane.
    Type: Grant
    Filed: June 5, 2020
    Date of Patent: April 12, 2022
    Inventor: Zhenkun Wang
  • Patent number: 11300077
    Abstract: A thrust reverser may include a frame, an actuation arrangement, a reverser door pivotally coupled to the frame, and a deployable fairing pivotally coupled to the frame, wherein the deployable fairing is configured to move away from a central axis of the thrust reverser to provide clearance for one of more thrust reverser pivot doors to rotate into a deployed position.
    Type: Grant
    Filed: September 4, 2019
    Date of Patent: April 12, 2022
    Assignee: ROHR, INC.
    Inventor: Timothy Gormley
  • Patent number: 10875658
    Abstract: A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: December 29, 2020
    Assignee: JETOPTERA, INC.
    Inventor: Andrei Evulet
  • Patent number: 10870486
    Abstract: A diamond quadcopter is described with tilting propulsion modules attached to a diamond faceted fuselage providing vertical thrust for Vertical Takeoff and Landing (VTOL) and transitioning to horizontal thrust for flight. The diamond faceted fuselage generates lift as a low aspect ratio lifting body. The diamond-like facet geometry enables propulsor placement to minimize interaction between the slipstream and fuselage in all modes of operation. A retractable landing gear with powered wheels allows Vertical/Short Takeoff and Landing (V/STOL) including emergency landings, and maneuverability on the ground. Landed and with gear retracted the bottom fuselage facet is close to ground level allowing an aft facet ramp for walk-on or roll-on access of passengers and payload. With the landing gear extended the vehicle can maneuver over cargo using the wheeled hub motors and then retract for insertion of cargo through a fuselage bottom door.
    Type: Grant
    Filed: September 18, 2018
    Date of Patent: December 22, 2020
    Inventor: Stephen Lee Bailey
  • Patent number: 10837359
    Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.
    Type: Grant
    Filed: February 27, 2017
    Date of Patent: November 17, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, Michael E. McCune, Jesse M. Chandler, Alan H. Epstein, Steven M. O'Flarity, Christopher J. Hanlon, William F. Schneider, Joseph B. Staubach, James A. Kenyon
  • Patent number: 10800538
    Abstract: A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: October 13, 2020
    Assignee: JETOPTERA, INC.
    Inventor: Andrei Evulet
  • Patent number: 10788047
    Abstract: An aircraft includes an airframe, ducted fans, and ducts for carrying pressurized air for lift and thrust supplied by the fans. The ducts form part of the airframe and carry static and dynamic loads applied to the airframe. Ducting members supply lift and thrust and transmit them to other airframe components. The ducts also carry the ducted air to exits set distant from the fans to permit flight control of the aircraft. Ducting members also form airfoils creating lift for the aircraft.
    Type: Grant
    Filed: March 28, 2019
    Date of Patent: September 29, 2020
    Assignee: AvionOne Innovations, LLC
    Inventor: Thomas G. Stephens
  • Patent number: 10773802
    Abstract: The present disclosure provides an aircraft system in the tilt-rotor category with four propulsion units where the tilt angle and thrust of each unit is controlled independently of the other units. The tilt angle for each unit can be adjusted anywhere from below horizontal, to fully forward, and to greater than 180 degrees (i.e. tilted backwards). As a result, the system enables greater control during all phases of flight. Due to continuous, independent tilt control of the angle and thrust of each rotor, the present aircraft can avoid stalls much easier than traditional fixed-wing aircraft and other VTOL designs, as thrust vectors can at any moment be adjusted to compensate for loss of wing lift, making the aircraft safer to use.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: September 15, 2020
    Assignee: Forward Robotics Inc
    Inventors: Tamara Jean Finlay, Meng Wei
  • Patent number: 10696414
    Abstract: An unmanned aerial vehicle comprises a housing, a plurality of first arms, a plurality of second arms, and a landing gear. The housing includes a gimbal attachment to couple a gimbal with a camera. Each of the plurality of first arms and the plurality of second arms rotatably couple with the housing at one end and has a motor coupled with a propeller on the other end. The landing gear includes a plurality of foldable legs and releasably couples with an underside of the housing. The aerial vehicle may be programmed with aerial flight path data that corresponds with a prior traced route.
    Type: Grant
    Filed: October 21, 2016
    Date of Patent: June 30, 2020
    Assignee: GoPro, Inc.
    Inventors: Nicholas D. Woodman, Pablo German Lema, Seung Heon Lee
  • Patent number: 10562620
    Abstract: In various embodiments, a tilt-wing aircraft includes a fuselage; a first wing tiltably mounted at or near a forward end of the fuselage; and a second wing rotatably mounted to the fuselage at a position aft of the first wing. A first plurality of rotors is mounted on the first wing at locations on or near a leading edge of the first wing, with two or more rotors being mounted on wing portions on each side of the fuselage; and a second plurality of rotors mounted on the second wing at locations on or near a leading edge of the second wing, with two or more rotors being mounted on wing portions on each side of the fuselage. A flight control system generates a set of actuators and associated actuator parameters to achieve desired forces and moments.
    Type: Grant
    Filed: September 27, 2017
    Date of Patent: February 18, 2020
    Assignee: WISK AERO LLC
    Inventors: Ilan Kroo, Herve Martins-Rivas, Eric Allison
  • Patent number: 10464668
    Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.
    Type: Grant
    Filed: March 10, 2017
    Date of Patent: November 5, 2019
    Assignee: JETOPTERA, INC.
    Inventor: Andrei Evulet
  • Patent number: 10427784
    Abstract: A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off.
    Type: Grant
    Filed: December 5, 2011
    Date of Patent: October 1, 2019
    Assignee: Aurora Flight Sciences Corporation
    Inventor: Robert Parks
  • Patent number: 10302042
    Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body that defines an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies by location on the wall in accordance with a desired flutter characteristic at the location.
    Type: Grant
    Filed: June 9, 2016
    Date of Patent: May 28, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Oliver V. Atassi, Oleg Petrenko
  • Patent number: 10287991
    Abstract: A gas turbine engine comprises a gas generator rotating along a first axis of rotation, with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine rotates along a second axis of rotation, downstream of at least one gas generator turbine rotor. The fan drive turbine drives a pair of shaft portions extending in opposed directions beyond the axis of rotation of the gas generator.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: May 14, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler
  • Patent number: 10272986
    Abstract: An unmanned aerial vehicle includes a body and a heat source disposed in the body. The heat source includes at least one of an electronic controller system and a motor. The unmanned aerial vehicle further includes a plurality of rotor blades. At least a portion of the body is constructed of crystalline carbon fibers.
    Type: Grant
    Filed: October 12, 2015
    Date of Patent: April 30, 2019
    Assignee: RAPID UNMANNED AERIAL SYSTEMS, LLC
    Inventor: Alan Taylor
  • Patent number: 10099794
    Abstract: A vertical take-off and landing aircraft using a hybrid electric propulsion system includes an engine, a generator that produces electric power using power supplied by the engine, and a battery that stores the produced electric power. A motor receives the electric power stored in the battery and electric power produced by the generator but not stored in the battery and provides the power to a thrust generating apparatus. A controller selects either silence mode or normal mode, and determines the amount of electric power stored in the battery and the amount of electric power not stored in the battery from the electric power supplied to the motor. In the silence mode, the controller supplies only the electric power stored in the battery and controls a duration by adjusting output power of motor. In the normal mode, the controller supplies electric power not stored in the battery.
    Type: Grant
    Filed: February 15, 2018
    Date of Patent: October 16, 2018
    Assignee: HANKUK CARBON CO., LTD.
    Inventors: Jeong-Gyu Bak, Jinsoo Cho, Boseong Kim, Senghyun Yun, Sunghong Won, Tae-Chul Jeong, Sooyoung Cho, Geunho Lee, Kyusung Park, Juhyung Ha, Changmo Moon, Sunho Beck, Changjun Meang, Hanki Lee, Minjun Kim, Dain Lee
  • Patent number: 10040547
    Abstract: An unmanned aerial vehicle includes a vehicle body and a vehicle wing on the vehicle body. A front motor assembly is provided in the vehicle body and the vehicle wing. A front vertical air discharge pathway and a front horizontal air discharge pathway communicate with the front motor assembly. A front air diverter is disposed between a retracted position unblocking the front vertical air discharge pathway to impart vertical lift to the vehicle and an extended position blocking the front vertical air discharge pathway to impart horizontal thrust to the vehicle. A pair of rear motor assemblies is provided in the vehicle wing and each includes a rear vertical air discharge pathway and a rear horizontal air discharge pathway communicating with the rear motor assembly.
    Type: Grant
    Filed: November 18, 2015
    Date of Patent: August 7, 2018
    Inventor: Samuel Pedigo
  • Patent number: 10035604
    Abstract: A vertical take-off and landing aircraft using a hybrid electric propulsion system includes an engine, a generator that produces electric power using power supplied by the engine, and a battery that stores the produced electric power. A motor receives the electric power stored in the battery and electric power produced by the generator but not stored in the battery and provides the power to a thrust generating apparatus. A controller selects either silence mode or normal mode, and determines the amount of electric power stored in the battery and the amount of electric power not stored in the battery from the electric power supplied to the motor. In the silence mode, the controller supplies only the electric power stored in the battery and controls a duration by adjusting output power of motor. In the normal mode, the controller supplies electric power not stored in the battery.
    Type: Grant
    Filed: February 15, 2018
    Date of Patent: July 31, 2018
    Assignee: HANKUK CARBON CO., LTD.
    Inventors: Jeong-Gyu Bak, Jinsoo Cho, Boseong Kim, Senghyun Yun, Sunghong Won, Tae-Chul Jeong, Sooyoung Cho, Geunho Lee, Kyusung Park, Juhyung Ha, Changmo Moon, Sunho Beck, Changjun Meang, Hanki Lee, Minjun Kim, Dain Lee
  • Patent number: 9994100
    Abstract: A vehicle includes a shutter system cooperating with at least one grille opening in the body of a vehicle. The shutter system includes a shutter assembly to regulate airflow entering through the at least one grille opening. The shutter assembly includes a frame and at least one vane operably connected to the frame and selectively positionable between at least an open position and a closed position. The at least one vane includes a body shaped as a cambered airfoil defining a leading edge and an opposing trailing edge. The at least one vane is pivotally connected at a pivot point and is adjustable relative to the frame between at least the open position and the closed position in response to an airflow entering through the at least one grille opening interacting with the leading edge of the body of the at least one vane.
    Type: Grant
    Filed: October 27, 2017
    Date of Patent: June 12, 2018
    Assignee: GM Global Technology Operations LLC
    Inventors: Steven A. Del Gaizo, William Fang
  • Patent number: 9957055
    Abstract: A propulsion system for an aircraft including a plurality of primary engines is provided. The plurality of primary engines includes at least a first primary engine and a second primary engine, each configured for mounting to a respective one of a pair of wings of the aircraft. The propulsion system additionally includes an aft engine configured for mounting at a tail section of the aircraft. The plurality of primary engines are sized to provide an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine, such that the aft engine may be configured as a non-prime reliable engine.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: May 1, 2018
    Assignee: General Electric Company
    Inventors: Patrick Michael Marrinan, Thomas Lee Becker, Kurt David Murrow
  • Patent number: 9950800
    Abstract: A propulsion system for a transport aircraft employs a gas turbine core coupled to a wing. A ducted fan is coupled to the core gas turbine extending downstream from and integrated in a trailing edge of the airplane wing.
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: April 24, 2018
    Assignee: The Boeing Company
    Inventors: Sina Golshany, Todd W. Erickson, Christopher R. Holtorf, Derek R. Alderks
  • Patent number: 9932118
    Abstract: A vertical take-off and landing aircraft using a hybrid electric propulsion system includes an engine, a generator that produces electric power using power supplied by the engine, and a battery that stores the produced electric power. A motor receives the electric power stored in the battery and electric power produced by the generator but not stored in the battery and provides the power to a thrust generating apparatus. A controller selects either silence mode or normal mode, and determines the amount of electric power stored in the battery and the amount of electric power not stored in the battery from the electric power supplied to the motor. In the silence mode, the controller supplies only the electric power stored in the battery and controls a duration by adjusting output power of motor. In the normal mode, the controller supplies electric power not stored in the battery.
    Type: Grant
    Filed: July 15, 2016
    Date of Patent: April 3, 2018
    Assignee: HANKUK CARBON CO., LTD.
    Inventors: Jeong-Gyu Bak, Jinsoo Cho, Boseong Kim, Senghyun Yun, Sunghong Won, Tae-Chul Jeong, Sooyoung Cho, Geunho Lee, Kyusung Park, Juhyung Ha, Changmo Moon, Sunho Beck, Changjun Meang, Hanki Lee, Minjun Kim, Dain Lee
  • Patent number: 9835044
    Abstract: A bypass turbine engine including an inner casing, an inter-duct casing and an outer casing, wherein a primary duct is defined between the inter-duct casing and the inner casing, wherein a secondary duct is defined between the inter-duct casing and the outer casing wherein a rotary shaft includes, at the upstream end, a movable fan including radial blades of which the free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct, wherein a plurality of variable-pitch radial stator vanes are mounted upstream of the movable fan, the variable-pitch vanes being configured to deflect the incident axial air, wherein the movable fan is configured to axially rectify the air deflected in the secondary duct, and the turbine engine not being provided with stator vanes in the secondary duct downstream of the movable fan.
    Type: Grant
    Filed: July 29, 2013
    Date of Patent: December 5, 2017
    Assignee: SNECMA
    Inventor: Jean-Loic Herve Lecordix
  • Patent number: 9682772
    Abstract: The present invention provides a multi-stage tilting and multi-rotor flying car including: a main frame externally shaped like a rectangle and internally partitioned to have a grid structure; a body mounted at a center of the main frame in consideration of balance; a plurality of rotors mounted to the main frame to face upward; a plurality of wheels mounted to the main frame to face downward; body wings provided at opposite sides of the body; and an automatic driving controller provided in the body and controlling the rotors and the wheels, thereby having effects on spending only the minimum necessary flying time for taking off and landing in a narrow area, and improving flight performance three times higher in flight time and flight speed and five times higher in fight distance than a rotary-wing aircraft such as a helicopter while flying in the fixed-wing mode.
    Type: Grant
    Filed: February 25, 2013
    Date of Patent: June 20, 2017
    Assignee: EXENS
    Inventor: Kwang Joon Yoon
  • Patent number: 9637217
    Abstract: An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: May 2, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Patrick Michael Marrinan, Thomas Lee Becker, Kurt David Murrow, Jixian Yao
  • Patent number: 9387929
    Abstract: The invention is to an optionally piloted aircraft that can takeoff and land conventionally or vertically, and can convert between the two. The aircraft is immune to one or more engine failures during vertical flight through multiple engines and the use of a virtual nozzle. Aerodynamic controls are similarly redundant. Hovering flight is enabled with a novel stabilization system. Long range efficient cruise is achieved by turning off some engines in flight and sealing them into an aerodynamic fairing to achieve low drag. The resulting aircraft is capable of CTOL and VTOL, and is capable of converting between the two modes while in the air or on the ground. The aircraft can also be easily taxied on the ground in the conventional manner. Automatic controls considerably reduce the amount of training a pilot needs to fly and land the aircraft in either VTOL or CTOL mode.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: July 12, 2016
    Inventors: Ian Todd Gaillimore, Kenneth Dean Driver
  • Patent number: 9371739
    Abstract: A power-producing device, such as a ram air turbine, includes a controller that is used to control operation of a turbine of the power-producing device. The controller uses an input based on an airspeed of the aircraft as part of a control mechanism in the controller for controlling the turbine. For example controller may be used to control backpressure of the turbine, for example by controlling the angle of doors of that are used to adjust backpressure of the turbine. The control mechanism may include a PID controller, with the gain of one or more of the values of the PID controller being a function of the airspeed of the aircraft. In addition the control mechanism may include manipulating a setpoint as a function of load on the power-producing device. The power-producing device may be part of a detachable pod that is installed on the aircraft.
    Type: Grant
    Filed: January 4, 2013
    Date of Patent: June 21, 2016
    Assignee: Raytheon Company
    Inventors: Brendan H Robinson, John K Yook, John H Steele
  • Patent number: 9193436
    Abstract: A wing assembly, a wing applique and an associated method for controlling the flow of air over a wing are provided. A wing assembly may include a wing having leading and trailing edges. The wing assembly also includes a flow control structure, such as an applique, carried by the surface of the wing so as to extend from a first end to a second end. The flow control structure defines an inlet proximate to the first end, an outlet proximate to the second end and the internal passage extending from the inlet to the outlet. The wing assembly may also include a control surface, such as a wedge, positioned downstream of the outlet. The flow control structure is configured to control the flow of air exiting from the outlet in order to correspondingly control attachment of the air with the control surface.
    Type: Grant
    Filed: July 3, 2013
    Date of Patent: November 24, 2015
    Assignee: The Boeing Company
    Inventor: Roger D. Bernhardt
  • Patent number: 9176499
    Abstract: A method is provided for managing the flight of an aircraft flying a trajectory calculated by a flight management system. The trajectory necessitates at least one transition between two different aerodynamic configurations of the aircraft. The method comprises: extraction of performance data of the aircraft from a database, at least one item of performance data being a function of an aerodynamic configuration, selection between a first determination step and a second determination step, a step of determination of a start point and of an end point of the transition between two aerodynamic configurations and engine speeds of an aircraft during a flight, the determination step being implemented by the flight management system and chosen from among the first and second determination steps, the determination step calculating the trajectory by numerical integration of the equations representative of the dynamics of the aircraft making use of the performance data of the aircraft.
    Type: Grant
    Filed: October 22, 2014
    Date of Patent: November 3, 2015
    Assignee: Thales
    Inventors: Francois Coulmeau, Jerome Sacle, Johan Boyer
  • Patent number: 8960592
    Abstract: An aircraft, such as a radio controlled aircraft, capable of vertical take-off and landing. The aircraft has a compressor in a fuselage that contains an interconnected first and second fans driven by a motor. An intake provides air to the first fan, while a bypass duct directs airflow to the second fan. Air flow from the first fan to the second fan is controlled by a valve, which is operated in tandem with doors in the bypass duct. Nozzles direct air flow out of the compressor in a selected one of a vertical or non-vertical direction for conventional flight or for hover. Hover tubes are provided to adjust the aircraft in pitch, yaw and roll. The hover tubes operate simultaneously with conventional flight controls.
    Type: Grant
    Filed: July 19, 2012
    Date of Patent: February 24, 2015
    Inventor: D. Anthony Windisch
  • Patent number: 8925665
    Abstract: An apparatus for controlling the propulsion and direction of an air cushion vehicle including a housing and a first vane pivotally coupled to the housing and pivotable about a first axis. A second vane assembly including at least one second vane is disposed within the first vane. The second vane assembly is pivotally coupled to the first vane and pivotal about a second axis. The second axis is orthogonal to the first axis. A first actuator is operably coupled to the first vane and a second actuator is operably coupled to the second vane assembly. The first actuator pivots the first vane and the second vane assembly about the first axis. The second actuator pivots the second vane assembly relative to the first vane and about the second axis to control the flow of air through the housing.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: January 6, 2015
    Inventor: Charles J. Trojahn
  • Patent number: 8918235
    Abstract: Technologies are described herein for providing additional yaw control to a multi-engine aircraft experiencing engine thrust asymmetry. A primary flight control system of the aircraft is configured to limit the operational thrust of an operating engine of the aircraft to provide additional yaw control when the aircraft is experiencing thrust asymmetry. The system includes a thrust limit module for calculating the maximum engine thrust limit to be imposed on an operating engine. The maximum engine thrust limit is calculated using inputs corresponding to the sideslip angle and the roll rate of the aircraft. The maximum engine thrust limit is imposed on the operating engine of the aircraft such that the operational thrust generated by the operating engine is limited to the maximum engine thrust limit. By reducing the operational thrust generated by the operating engine, the yawing caused by the thrust asymmetry is likely to be reduced.
    Type: Grant
    Filed: January 7, 2013
    Date of Patent: December 23, 2014
    Assignee: The Boeing Company
    Inventors: David P. Eggold, Daniel R. Shapiro, Kyle J. Gardner
  • Patent number: 8807484
    Abstract: 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: Grant
    Filed: August 2, 2010
    Date of Patent: August 19, 2014
    Assignee: Airbus Operations Limited
    Inventors: Hugo Alexandre Duart Mendes Raposeiro, Bruno Stefes, Holger Bammann, Thomas Selchert, James Brown, Heiko Rothe, Alexander Solntsev
  • Patent number: 8692489
    Abstract: A control system for controlling an electrical device of a nacelle, the device having at least one element that is movable to a closed position and an open position. The control system includes at least one electromechanical member for actuating the movable element, a unit for electrically driving the electromechanical actuation member, and a controlling and monitoring unit for controlling the electrical drive unit so as to move the movable element to the closed and/or open position. The control system further includes a system for recovering braking power from the electrical drive unit during the movement of the movable element to the closed and/or open position.
    Type: Grant
    Filed: October 11, 2012
    Date of Patent: April 8, 2014
    Assignee: Aircelle
    Inventor: Hakim Maalioune
  • Patent number: 8646721
    Abstract: A fluid dynamic device (100) for directing fluid flow to generate thrust comprising a thrust control shroud (130) disposed about a central axis (210) of said fluid dynamic device (100) for directing a fluid flow between an upstream fluid intake region (220) and a downstream fluid exit region (222), forming a fluid exit area, of said shroud (130) to generate thrust wherein a displacement of said fluid exit region (222) of said shroud (130) with respect to said central axis (210) results in a translation of said fluid exit area (222) such that the level of shear stress induced in that part of the shroud (130) disposed laterally to the direction of translation of the shroud (130) is minimized.
    Type: Grant
    Filed: May 7, 2009
    Date of Patent: February 11, 2014
    Assignee: Entecho PTY Ltd.
    Inventors: Greg Chapman, Jakub Kawka, Christopher Kim Schlunke
  • Patent number: 8608104
    Abstract: The invention relates to a propulsion device (10) comprising a body (11) arranged for receiving a passenger (1) and engaging with a thrust unit (12a, 12b, 13a, 13b) supplied with a pressurized fluid from a compression station. The arrangement of such a device offers great freedom of movement through the air or under the surface of a fluid. The invention also relates to a propulsion system in which the compression station can be remote in the form of a motorized marine vehicle.
    Type: Grant
    Filed: October 10, 2012
    Date of Patent: December 17, 2013
    Assignee: Personal Water Craft Product
    Inventor: Frankie Zapata
  • Patent number: 8579227
    Abstract: Novel aircraft for vertical and horizontal flight having powered air acceleration means installed within its structure drawing air thereinto and delivering the resulting airflow upon airfoils installed in opposed pairs on opposite sides of its exterior structure thereby producing lift without forward travel of the aircraft.
    Type: Grant
    Filed: January 24, 2011
    Date of Patent: November 12, 2013
    Inventor: J. Kellogg Burnham
  • Patent number: 8523101
    Abstract: An aircraft capable of making short takeoffs and landings includes essentially a fuselage, a wing secured to the fuselage, a front horizontal stabilizer secured to the fuselage on the front end of the fuselage and at least two jet engines for propulsion. According to the architecture proposed, the propulsion engines are arranged side by side above the fuselage in a rear part of the fuselage with a width at least equal to the width of the propulsion group, a fuselage flap device is arranged in the back of the fuselage so that the fuselage flaps adopt at least a position in which the flaps are considerably in a horizontal plane and take at least a high-lift position in which the flaps are turned downward in such a way that the blast created by the jet engines is channeled towards the top surface of the fuselage flaps to induce a blowing effect.
    Type: Grant
    Filed: July 24, 2008
    Date of Patent: September 3, 2013
    Assignee: Airbus Operations SAS
    Inventors: Olivier Cazals, Alexander Koch
  • Patent number: 8500061
    Abstract: An aircraft includes a jet engine with a downward deflectable propelling nozzle; an auxiliary power unit with a downward deflectable propelling nozzle; and a transformable wing. The transformable wing includes a fixed wing, hydraulic sleeve, an air intake duct including an upper wall and a lower wall, a thin wing connected to the hydraulic sleeve, a sliding wing, leading edge flaps, trailing edge flaps, an aileron, and a hinge. The transformable wing is configured, during vertical take-off/landing, to transform such that a leading end to an air intake duct in a vertical direction is formed on the fixed wing, and the air intake duct is formed internally in and along a direction of the wingspan of the fixed wing to cause air taken in by the jet engine to flow, in a common direction, over upper and lower surfaces of the thin wing, thereby generating lift for vertical take-off/landing.
    Type: Grant
    Filed: December 1, 2010
    Date of Patent: August 6, 2013
    Inventor: Li Jing Chen
  • Patent number: 8408488
    Abstract: One embodiment of a Vertical Take-off and Landing (VToL) air-vehicle (FIG. 1.) having a horizontal rotor, a. providing lift and propulsion, and communicating at or near its centre to structural elements, or fuselage, b. Upon or within the fuselage structure is attached a platform, to which a payload, or occupant or pilot, d. is secured in such a manner as to permit a movement, or range-of-motion, of the payload, as a means of weight-shifting, or mass-balancing, of the vehicle for stability and control in flight. At least two planar elements, or descent-vanes, c.i & c.ii are connected to a structural element of the fuselage at a location which provides vertical and horizontal separation between the rotor and the descent-vanes, thus creating a tandem, biplane arrangement of two aerodynamically active elements which are aerodynamically balanced to provide stability and controllability in hovering flight, in forward flight, and in un-powered gliding and vertical descents.
    Type: Grant
    Filed: January 4, 2010
    Date of Patent: April 2, 2013
    Inventor: Glenn Leaver
  • Patent number: 8376268
    Abstract: A flight control system use in relation to an aviation vehicle having a thrust vectoring device for producing thrust, an air deflecting device for producing thrust having a box structure, and a computing system for receiving operation requirements is used to orient the thrust device and/or air deflecting device.
    Type: Grant
    Filed: April 9, 2012
    Date of Patent: February 19, 2013
    Inventor: Paul Robert Otto
  • 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: 8336806
    Abstract: A flow path is disclosed that is capable of being deployed when needed and stowed in a relatively small space when not in use. The flow path device is flexible and may be made from a variety of materials. In an illustrative embodiment the flow path device is annular and transitions from an ellipsoidal annular shape to a quadrilateral annular shape. A vane box can be disposed at one end of the flow path device. Doors can be coupled to the vane box to cover the flow path device. The doors can be used to provide a structural load path for the flow path device and vane box. The doors and the flow path device can be moved together such that the doors uncover the flow path device as the device is deployed.
    Type: Grant
    Filed: December 3, 2009
    Date of Patent: December 25, 2012
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Douglas David Dierksmeier
  • Patent number: 8317126
    Abstract: An aircraft having a lift/propulsion unit which includes a power unit such as a turboshaft engine which drives a fan through a transmission mechanism. The fan discharges to vectoring nozzles which can be independently swivelled to provide lift or propulsion thrust. An output shaft of the transmission mechanism serves as the main shaft of a motor/generator of modular form. The motor/generator can act as a generator to charge an electrical storage device such as a battery, or as a motor to drive the fan, either alone or to supplement the output of engine. Reaction control nozzles are provided at extremities of the aircraft to provide stabilizing thrust. The aircraft is capable of vertical take off and hovering, with the vectoring nozzles swivelled to a lift position, and forward thrust with the vectoring nozzles swivelled to a propulsion position.
    Type: Grant
    Filed: April 15, 2010
    Date of Patent: November 27, 2012
    Assignee: Rolls-Royce PLC
    Inventors: Paul J. H. Harris, Frank A. Hewitt, Martin C. Johnson, Christopher Wright