Airplane And Helicopter Sustained Patents (Class 244/6)
  • Patent number: 10604241
    Abstract: A battery powered helicopter uses one or more torque arms as the power source directly driving the propeller to rotate. The helicopter does not require a combustion engine, a clutch, a reducer, a tail driver, a tail boom, a tail rotor, or a fuel supply system. The output shaft of the high-energy motor is coaxial with the main rotor shaft. The centrifugal force of one or more motor(s) is negligible or minimized. The torque arm assembly includes a plurality of torque arms. Each of the torque arms of the plurality of torque arms includes a propeller and a driving system.
    Type: Grant
    Filed: July 29, 2019
    Date of Patent: March 31, 2020
    Inventor: Dawei Dong
  • Patent number: 10549852
    Abstract: Embodiments of the invention include a vehicle including an engine and a rotor including a plurality of rotor blades in a path of exhaust from the engine. The vehicle includes a rotor control assembly configured to connect the rotor to a rotation force source to rotate the rotor and configured to rotate the rotor at a prescribed minimum rotation rate greater than zero based on at least one of disengaging the rotor from the rotation force source and receiving a control signal to disengage the rotor from the rotation force source. The rotor control assembly is designed to rotate the rotor at the prescribed minimum rotation rate based on at least one system attribute of the vehicle that is affected by a rotation rate of the rotor.
    Type: Grant
    Filed: July 6, 2015
    Date of Patent: February 4, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Ashley Devito, Henry E. Voegeli, Joseph Pantalone, III
  • Patent number: 10549839
    Abstract: A wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19?), and an actuating arrangement having an actuator (21) which is coupled to the base section (7) and the tip section (13) and which is operable to effect a pivotal movement of the tip section (13) relative to the base section (7) between a stowed position and a deployed position.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: February 4, 2020
    Assignees: Airbus Operations GmbH, Airbus Operations Limited
    Inventors: Christoph Winkelmann, Johannes Rupp, David Brakes
  • Patent number: 10526077
    Abstract: A flight system for an aircraft and method for controlling a clearance between a first rotor disk and a second rotor disk of an aircraft is disclosed. The flight system includes a sensor for measuring an angle of deviation of at least one of a first rotor disk and a second rotor disk of the aircraft to indicate a clearance between the first rotor disk and the second rotor disk as well as sensors for measuring a flight condition of the aircraft. A control allocation module uses the measured angle of deviation and the flight condition of the aircraft to determine an allocation of control settings to axis-controlling devices of the aircraft to attain a selected pitch of the aircraft, wherein the allocation is based at least on the measured angle of deviation and the flight state of the aircraft.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: January 7, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Ole Wulff, Derek Geiger
  • Patent number: 10338540
    Abstract: The invention relates to a method and to a device for optimized global management of a power network of an aircraft comprising a plurality of items of power equipment, characterized in that it comprises a module 40 for selecting at least one optimization objective (19) from a plurality of predetermined objectives, a module (42) for receiving equipment data, a module (41) for receiving aircraft data, and a module (43) for determining operating setpoints (22) of the power equipment from equipment data (21) and aircraft data (20) which is suitable for achieving at least one selected optimization objective (19).
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: July 2, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Fabien Mercier-Calvairac, Antoine Drachsler, Romain Thiriet
  • Patent number: 10322814
    Abstract: An aircraft design where the one or multiple numbers of vertical stabilizer each has a lifting propeller.
    Type: Grant
    Filed: September 1, 2018
    Date of Patent: June 18, 2019
    Assignee: AutoflightX International Limited
    Inventor: Yu Tian
  • Patent number: 10315759
    Abstract: A vehicle with superior performance and reliability. The vehicle, such as an unmanned aerial vehicle, is capable of vertical takeoff and landing, uses three swashless, variable-pitch vertical lift main rotors with a yaw tail rotor system. Two rear main rotors are optionally tiltrotors, which pivot to increase forward speed without the increased coefficient of drag inherent in tilting the entire vehicle. The three main rotors are positioned in an equilateral triangular configuration, improving balance, increasing load-bearing strength, and making it more compact in size. Movements are controlled through changes in pitch of the rotors, allowing the motors to maintain constant governed rotations per minute, maximizing drivetrain efficiency. Various embodiments allow for smaller vehicle size with greater performance than prior art vehicles.
    Type: Grant
    Filed: April 3, 2016
    Date of Patent: June 11, 2019
    Assignee: California Institute of Technology
    Inventors: Reza Nemovi, Robert Bartlett
  • Patent number: 10099802
    Abstract: A method for providing data associated with rollover of an aircraft is provided. The method detects a potential dynamic rollover condition for the aircraft based on at least one of a current rotor thrust, a slope of terrain surrounding the aircraft, a state of ground contact components, and a position of a lateral center of gravity, by at least one processor onboard the aircraft, wherein the potential dynamic rollover condition indicates imminent rollover of the aircraft occurring within a predetermined period of time; and presents an alert associated with the potential dynamic rollover condition via an aircraft onboard display communicatively coupled to the at least one processor.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: October 16, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Mahipal Reddy, Anil Kumar Songa
  • Patent number: 10093427
    Abstract: An aircraft which has a supporting structure which has at least one fuselage, a wing structure and at least one drive apparatus. The drive apparatus has at least one propeller and a drive motor. The aircraft has at least one energy store for providing energy for operation of the drive apparatus. The at least one drive apparatus and the at least one energy store are mechanically connected to the supporting structure and/or the wing structure of the aircraft by a securing device.
    Type: Grant
    Filed: February 11, 2016
    Date of Patent: October 9, 2018
    Assignee: Airbus Defence and Space GmbH
    Inventor: Simon Burns
  • Patent number: 10054946
    Abstract: An electronic device is provided. The electronic device includes a gimbal; a first camera; a second camera to detect a point of interest on ground; at least one sensor; a first motor; a second motor to operate the first camera and the second camera to maintain horizontality; and at least one processor electrically connected to the first camera, the second camera, the at least one sensor, the first motor, and the second motor, wherein the at least one processor is configured to detect a change in an angle; control the second motor to control the second camera to maintain horizontality; determine whether the point of interest is changed; if the point of interest is not changed, control the first motor to maintain hovering; and, if the point of interest is changed, control the first motor to maintain hovering by moving to original position before moving and compensating for tilt.
    Type: Grant
    Filed: July 24, 2017
    Date of Patent: August 21, 2018
    Assignee: Samsung Electronics Co., Ltd
    Inventors: Young-Chul Shin, Wu Seong Lee
  • Patent number: 10017278
    Abstract: A gyroscopic orbiter with vertical takeoff and vertical landing capabilities can transition between different functional modes while in-flight. The orbiter typically includes a fuselage, a front boom, a front propulsion unit, a rear boom, and a rear propulsion unit. The front boom is mounted at two pivot points to a bow of the fuselage by the front boom. The rear boom is mounted at two pivot points to a stern of the fuselage by the rear boom. One functional mode is the vertical takeoff and landing mode, wherein the propulsion units are oriented parallel to each other and are directed upward. Another functional mode is the shuttle mode, wherein the propulsion units are oriented at an angle with each other, and the front propulsion unit is directed forward. Another functional mode is the high speed mode, wherein the propulsion units are oriented collinear with a roll axis of the fuselage.
    Type: Grant
    Filed: June 16, 2016
    Date of Patent: July 10, 2018
    Inventor: Thomas Norman Hesse
  • Patent number: 9926076
    Abstract: A method and system for controlling maneuverability of an aircraft includes receiving one or more signals indicative of commanded peak rotary acceleration at a first timeperiod; determining a signal indicative of an actual peak rotary acceleration for the first timeperiod in response to the receiving of the one or more signals for commanded pilot acceleration; and determining signals indicative of actual rotary acceleration for a second timeperiod.
    Type: Grant
    Filed: April 29, 2015
    Date of Patent: March 27, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Ashok Agnihotri, Steven D. Weiner, Vineet Sahasrabudhe
  • Patent number: 9889928
    Abstract: The lift, propulsion and stabilizing system for vertical takeoff and landing aircraft of the invention consists of applying during vertical flight on, below or in the interior of the fixed-wing aircraft one or more rotors or large fans each one with two or more horizontal blades, said rotors are activated by means of turboshafts, turbofans or turboprops with a mechanical, hydraulic, pneumatic or electrical transmission, and the respective motors. Using lifting and/or stabilizing and/or controlling fans and/or oscillating fins and/or air blasts. Placing the horizontal lifters near at least one end of the longitudinal axis and of the transverse axis of the aircraft. Generally said stabilizing elements form 90° with one another and with the central application point of the rotor or application of that which results from the lift forces.
    Type: Grant
    Filed: May 5, 2010
    Date of Patent: February 13, 2018
    Inventor: Manuel Salz
  • Patent number: 9845150
    Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
    Type: Grant
    Filed: February 11, 2013
    Date of Patent: December 19, 2017
    Assignee: Kitty Hawk Corporation
    Inventor: Ilan Kroo
  • Patent number: 9845151
    Abstract: A rotorcraft (1) having: a lift rotor (5); a wing (10) extending from a first end (11) carrying a first propulsive propeller (21) to a second end (12) carrying a second propeller (22); landing gear (30); and a tail (40). The rotorcraft (1) is provided with two fuselages (51, 52) secured to said wing (10) between said first and second propulsive propellers (21, 22) in such a manner as to present an inter-fuselage space (60) having no propeller between said fuselages (51, 52), each fuselage (51, 52) including at least one undercarriage of said landing gear (30).
    Type: Grant
    Filed: February 14, 2014
    Date of Patent: December 19, 2017
    Assignee: AIRBUS HELICOPTERS
    Inventor: Jean Nicola
  • Patent number: 9714090
    Abstract: An aircraft for vertical take-off and landing includes an aircraft assembly which includes at least one first wing portion providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion and at least one propeller-based thruster positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents positioned inside at least one of the wing openings. The air vents can further include louvres positioned over or under the air vents to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: July 25, 2017
    Assignee: SUNLIGHT PHOTONICS INC.
    Inventors: Sergey V. Frolov, Michael Cyrus, John Peter Moussouris
  • Patent number: 9499253
    Abstract: Apparatus and methods are disclosed for designing and manufacturing a composite structure, such as a composite rotor blade spar or composite rotor blade. A first mold may define a first mold surface and a second mold may include a rigid layer and a heated layer secured to the rigid layer and defining a second mold surface. A plurality of heating elements embedded in the second mold may be activated according to different temperature progressions to cure portions of the uncured composite rotor blade positioned coextensive therewith. In some embodiments, the second mold defines a root portion and first and second branch portions. A shear web may be placed between the branch portions during curing. The blade spar may define a complete airfoil contour or have fairings secured thereto having lines extending therethrough to a tip jet. A tip jet mounting structure and blade root attachment apparatus are also disclosed.
    Type: Grant
    Filed: November 14, 2011
    Date of Patent: November 22, 2016
    Inventor: Robert Owen White
  • Patent number: 9302762
    Abstract: A pitching stabilization means has at least one stationary stabilization surface extending in a thickness direction from a bottom face to a top face and in a transverse direction from a leading edge towards a trailing edge. The stabilization surface has at least one slot passing through the thickness of the stabilization surface from the top face to the bottom face. The slot is arranged within the stabilization surface between the leading edge and the trailing edge so as to allow a flow of air coming from a rotor to pass from the top face towards the bottom face.
    Type: Grant
    Filed: May 9, 2013
    Date of Patent: April 5, 2016
    Assignee: Airbus Helicopters
    Inventors: Jean-Loup Gatti, Remy-Elian Arnaud
  • Patent number: 9242738
    Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
    Type: Grant
    Filed: June 30, 2013
    Date of Patent: January 26, 2016
    Assignee: Zee.Aero Inc.
    Inventor: Ilan Kroo
  • Patent number: 9169010
    Abstract: A tiltrotor rotor hub comprises first and second configurations of yokes arranged in two parallel and axially offset planes, each having an equal number of two or more yokes substantially equally spaced about a mast, wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is selectively positionable for operation in helicopter/airplane/transition modes and comprises substantially parallel and axially offset first and second planes, each containing a plurality of blade yokes arranged about a central axis and a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke. Another tiltrotor rotor hub is coupled to a tiltrotor mast and comprises a stacked arrangement of blade yokes wherein a portion of each yoke overlaps with a portion of each azimuthally adjacent yoke, and a plurality of mounting components coupling each yoke to the overlapping azimuthally adjacent yoke.
    Type: Grant
    Filed: February 24, 2012
    Date of Patent: October 27, 2015
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Christopher Foskey, Frank B. Stamps
  • Patent number: 9150307
    Abstract: A method of controlling a high speed rotary wing aircraft (1) comprising: a fuselage (2); at least one main rotor (3); at least one variable pitch propulsive propeller (4); at least two half-wings (11, 11?) positioned on either side of said fuselage (2); at least one horizontal stabilizer (20) provided with a movable surface (21, 21?); and at least one power plant driving said main rotor (3) and each propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11?) and the lift of the horizontal stabilizer (20) so that the collective pitch of said blades (31) of said main rotor (3) is equal to a setpoint collective pitch, so that the longitudinal cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint longitudinal cyclic pitch, and so that the lateral cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint lateral cyclic pitch during a stabilized stage of flight.
    Type: Grant
    Filed: May 16, 2013
    Date of Patent: October 6, 2015
    Assignee: Airbus Helicopters
    Inventor: Paul Eglin
  • Patent number: 9139310
    Abstract: Systems and methods are provided for swapping the battery on an unmanned aerial vehicle (UAV). The UAV may be able to identify and land on an energy provision station autonomously. The UAV may take off and/or land on the energy provision station. The UAV may communicate with the energy provision station. The energy provision station may store and charge batteries for use on a UAV.
    Type: Grant
    Filed: September 24, 2014
    Date of Patent: September 22, 2015
    Assignee: SZ DJI TECHNOLOGY CO., LTD
    Inventor: Mingxi Wang
  • Patent number: 9126678
    Abstract: A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed location on a wing member; a prop-rotor pylon mechanically coupled to the engine along a drive path, and a gearbox disposed in the drive path. The prop-rotor pylon is rotatably mounted on a spindle, and the prop-rotor pylon is configured to selectively rotate about a rotational axis of the spindle between a vertical position and a horizontal position. The gearbox comprises a rotational axis aligned with the rotational axis of the spindle.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: September 8, 2015
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Brent C. Ross, David R. Bockmiller, Mark L. Isaac, Brian J. Cox
  • Publication number: 20150136897
    Abstract: The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or Unmanned Aerial System (UAS), comprising a rigid wing (2) which enables aerodynamic horizontal flight, and at least four rotors (4, 4?) which are driven by means of controllable electric motors (5) and which can be pivoted between a vertical starting position and a horizontal flight position by means of a pivoting mechanism (7), wherein all electric motors (5) and rotors (4) are arranged on the wing (2).
    Type: Application
    Filed: May 31, 2013
    Publication date: May 21, 2015
    Applicant: LOGO-TEAM UG (HAFTUNGSBESCHRANKT)
    Inventors: Florian Seibel, Michael Wohlfahrt, Michael Kriegel
  • Patent number: 9026274
    Abstract: An apparatus is described comprising: at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: regulate an operation of a motor based at least in part on a control imposed on an output torque of the motor and a rate of change of a speed of the motor.
    Type: Grant
    Filed: August 31, 2012
    Date of Patent: May 5, 2015
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Jonathan Hartman, Timothy Fred Lauder, Russell L. Halstead, Christopher L. Winslow, Michael L. Hardy
  • Patent number: 9016616
    Abstract: By using the interaction between the wind flow and the stabilizer arranged in the wind flow and along the direction of the wind flow, this invention provides the flying object that secures the stability of device or aircraft or stabilizer itself unified with the stabilizer by above effect. The interaction mentioned above is that when the wind flow hits the stabilizer at a certain angle, the wind flow changes the direction, and the power corresponding its reaction is given to the stabilizer by its reaction.
    Type: Grant
    Filed: July 25, 2011
    Date of Patent: April 28, 2015
    Inventor: Hiroshi Kawaguchi
  • Patent number: 8998125
    Abstract: A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.
    Type: Grant
    Filed: June 15, 2010
    Date of Patent: April 7, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Charles Hollimon, Dudley E. Smith, David Ludolph
  • Patent number: 8967524
    Abstract: A hydraulic control valve (10) provided with at least one body (11) having a jacket (12) with a feed orifice (13). The hydraulic control valve (10) has a transfer rod (15) provided with at least one fluid transfer duct (16), at least one orifice (17) present inside the jacket (12), and a second orifice (18) arranged outside the jacket (12). The jacket (12) has a feed chamber (25) connected to said feed orifice (13) and a main fluid-return chamber (30) connected to discharge means (50) for discharging the fluid, control means (20) being secured to the jacket (12) in order to move the jacket (12) in translation relative to said transfer rod (15) so as to control the flow of fluid within said transfer rod (15).
    Type: Grant
    Filed: June 6, 2013
    Date of Patent: March 3, 2015
    Assignee: Airbus Helicopters
    Inventors: Maxime Leclercq, Bernard Gemmati, Philippe Veron, Francois Malburet
  • Patent number: 8954206
    Abstract: The present disclosure relates to an unmanned aerial vehicle (UAV) able to harvest energy from updrafts and a method of enhancing operation of an unmanned aerial vehicle. The unmanned aerial vehicle with a gliding capability comprises a generator arranged to be driven by a rotor, and a battery, wherein the unmanned aerial vehicle can operate in an energy harvesting mode in which the motion of the unmanned aerial vehicle drives the rotor to rotate, the rotor drives the generator, and the generator charges the battery. In the energy harvesting mode regenerative braking of the generator reduces the forward speed of the unmanned aerial vehicle to generate electricity and prevent the unmanned aerial vehicle from flying above a predetermined altitude.
    Type: Grant
    Filed: February 14, 2013
    Date of Patent: February 10, 2015
    Assignee: The Boeing Company
    Inventor: Alfredo Criado
  • Publication number: 20150028151
    Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing tip mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the wings in a horizontal flight attitude then transitions to a horizontal flight path. An aerial vehicle which uses different configurations of its wing tip mounted, VTOL enabling rotors to reduce drag in all flight modes.
    Type: Application
    Filed: July 25, 2013
    Publication date: January 29, 2015
    Inventors: Joeben Bevirt, Edward Stilson, Alex Stoll, Pranay Sinha
  • Patent number: 8936212
    Abstract: System and method to construct vertical and/or short takeoff and landing (V/STOL) aerial vehicles capable of being folded into compact size, and capable of be combined with one or more such vehicles to form bigger composite aerial vehicles. Airframe of the vehicle comprises a plurality of wings on lateral or periphery of thrust generators, wherein arrangements of wings make it possible to optionally fold wings without moving thrust generators. Folding transforms such vehicles into ground vehicles which can share roads and house parking lots with conventional ground vehicles. Therefore such vehicles can be used as V/STOL flying cars. Means are provided for attaching to and detaching from one or more similarly equipped vehicles in flight or before takeoff, so that multiple vehicles can form a large composite vehicle. Compactness, combinability and V/STOL capability enable versatile applications.
    Type: Grant
    Filed: August 24, 2010
    Date of Patent: January 20, 2015
    Inventors: Qiang Fu, Xu Zhang
  • Publication number: 20150014475
    Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.
    Type: Application
    Filed: May 5, 2014
    Publication date: January 15, 2015
    Inventors: Dana J. Taylor, Phillip T. Tokumaro, Bart Dean Hibbs, William Martin Parks, David Wayne Ganzer, Christopher Eugene Fisher, Jason Sidharthadev Mukherjee, Joseph Frederick King
  • Patent number: 8931728
    Abstract: A rotorcraft is disclosed. The rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and at least one rotor blade having a tip jet. The rotorcraft may further include a plurality of compressors for generating compressed air and a network of conduits connecting the outlets of the plurality of compressors with every tip jet of the rotor. The rotorcraft may further include a control system preventing back flow through each outlet of the plurality of compressors.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: January 13, 2015
    Assignee: Groen Brothers Aviation, Inc.
    Inventor: Jacob Johannes van der Westhuizen
  • Publication number: 20150001336
    Abstract: A hybrid helicopter includes a rotary wing, two half-wings with respective propellers, and an engine installation continuously driving the rotary wing and the propellers by meshing with a mechanical interconnection system. A piloting assistance device for the hybrid helicopter is configured to determine maximum mean pitch (?max) applicable to the propellers without exceeding the power available for the propellers. The piloting assistance device is configured to determine the maximum mean pitch (?max) as a function of the current mean pitch of the blades of the propellers as measured in real time, a maximum power that can be delivered by the engine installation, a current power being delivered by the engine installation, and a relationship determining a power gradient (GRD) as a function of pitch for the propellers.
    Type: Application
    Filed: September 18, 2014
    Publication date: January 1, 2015
    Inventor: Paul Eglin
  • Patent number: 8915465
    Abstract: A rotor system is disclosed for a reactive drive rotary wing aircraft. Rigidity of the rotor is enhanced and play between flight controls and the rotor are eliminated by mounting swashplate actuators to a flange rigidly secured to the mast. Thermal management of the rotor is performed in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. Thermal management of a rotor may be performed by oil and air flow.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: December 23, 2014
    Assignee: Groen Brothers Aviation, Inc.
    Inventor: Jacob Johannes van der Westhuizen
  • Patent number: 8915464
    Abstract: An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: December 23, 2014
    Assignee: Airbus Helicopters
    Inventors: Jean-Jacques Ferrier, Paul Eglin
  • Publication number: 20140353420
    Abstract: A hybrid aircraft (1) having a fuselage (2) extending longitudinally along an anteroposterior plane of symmetry (PSYM) from the rear (4) of the aircraft (1) towards the front (3) of the aircraft (1). The aircraft (1) has a rotary wing (6) carried by the fuselage (2) of a lift surface (10) fastened to the fuselage (2) and constituted by a first half-wing (11) and a second half-wing (12). The aircraft (1) has a first propulsion unit (30) carried by the first half-wing (11) and a second propulsion unit (40) carried by the second half-wing (12). Each propulsion unit (30, 40) includes at least one tractor propeller (31, 32, 41, 42), and at least one propulsion unit has two propellers (31-32, 41-42) on the same axis, each of said propellers rotating about an axis of rotation (AX) that is offset transversely from said anteroposterior plane of symmetry (PSYM).
    Type: Application
    Filed: May 30, 2014
    Publication date: December 4, 2014
    Applicant: AIRBUS HELICOPTERS
    Inventor: Pierre PRUD'HOMME-LACROIX
  • Publication number: 20140353419
    Abstract: A hybrid aircraft (1) having a fuselage (2) extending longitudinally along an anteroposterior plane of symmetry (PSYM) from the rear (4) of the aircraft (1) towards the front (3) of the aircraft (1). The aircraft (1) has a rotary wing (6) carried by the fuselage (2) of a lift surface (10) fastened to the fuselage (2) and constituted by a first half-wing (11) and a second half-wing (12). The aircraft (1) has a first propulsion unit (30) carried by the first half-wing (11) and a second propulsion unit (40) carried by the second half-wing (12). Each propulsion unit (30, 40) includes at least one tractor propeller (31, 32, 41, 42), and at least one propulsion unit has two propellers (31-32, 41-42) on the same axis, each of said propellers rotating about an axis of rotation (AX) that is offset transversely from said anteroposterior plane of symmetry (PSYM).
    Type: Application
    Filed: May 30, 2014
    Publication date: December 4, 2014
    Applicant: AIRBUS HELICOPTERS
    Inventor: Pierre PRUD'HOMME-LACROIX
  • Publication number: 20140319265
    Abstract: A method of automatically triggering an emergency buoyancy system (10) for a hybrid helicopter (20) having a fuselage (21), two half-wings (23, 23?), and two propulsive propellers (24, 24?). During the method, said emergency buoyancy system (10) is primed, and then if a risk of said hybrid helicopter (20) ditching is detected, two retractable wing undercarriages (28, 28?) are deployed, each wing undercarriage (28, 28?) being fastened under a respective half-wing (23, 23?) and being provided with at least one immersion sensor (16). Finally, if the beginning of said hybrid helicopter (20) ditching is detected, at least one main inflatable bag (11, 11?) 7B suitable for being arranged under such fuselage (21) and at least one secondary inflatable bag (12, 12?) suitable for being arranged under each half-wing (23, 23?) are inflated so as to ensure that said hybrid helicopter (20) floats in stable manner.
    Type: Application
    Filed: November 4, 2013
    Publication date: October 30, 2014
    Applicant: EUROCOPTER
    Inventor: Bruno Cacciaguerra
  • Patent number: 8840057
    Abstract: An aircraft (1) having a fuselage (2), a power plant (10), a rotary wing (15) having at least one main rotor (16), and a fixed wing (20) comprising two half-wings (21, 22) extending on either side of the fuselage (2). The aircraft (1) also has at least two propulsive propellers (30) on either side of the fuselage (2). Each is positioned on respective ones of the half-wings (21, 22), and an anti-torque and yaw-control tail rotor (35). A transmission system (40) connects the power plant (10) to each main rotor (16) and the tail rotor (35). The transmission system (40) connects the power plant (10) to each propeller (30) via a respective differential mechanism (50) that is controllable on request so that each propeller (30) can be driven in cruising flight and need not be driven in rotation by the power plant (10) on the ground or while hovering.
    Type: Grant
    Filed: September 27, 2012
    Date of Patent: September 23, 2014
    Assignee: Airbus Helicopters
    Inventor: Robin Moret
  • Patent number: 8827204
    Abstract: An aircraft includes a powerplant system operable to power a main rotor system and a secondary thrust system, the secondary thrust system is selectively driven through operation of a clutch system, and a clutch system synchronization time corresponds to a response time of the powerplant system.
    Type: Grant
    Filed: January 12, 2012
    Date of Patent: September 9, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Charles E. Long, Dean A. Norem, Raymond N. Weyl, Ricky D. Reimers
  • Patent number: 8820673
    Abstract: An aircraft (1) having a fuselage (2), the aircraft (1) comprising a rotary wing (9) above the fuselage (2) and an extra fixed wing (10), the rotary wing (9) being above both the fuselage (2) and the fixed wing (10), said fixed wing (10) comprising at least one closed wing (20) comprising a first half-wing (21) and a second half-wing (22). Each half-wing (21, 22) is provided with a top lift portion (30) and a bottom lift portion (40), said bottom lift portion (40) of a half-wing being arranged in the wake (S) of the top lift portion (30) of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing (9) and impacting against the top face (30?) of the top lift portion (30) when said aircraft (1) has a forward speed less than a predetermined threshold.
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: September 2, 2014
    Assignee: Airbus Helicopters
    Inventor: Bruno Cacciaguerra
  • Publication number: 20140239116
    Abstract: A rotorcraft (1) having: a lift rotor (5); a wing (10) extending from a first end (11) carrying a first propulsive propeller (21) to a second end (12) carrying a second propeller (22); landing gear (30); and a tail (40). The rotorcraft (1) is provided with two fuselages (51, 52) secured to said wing (10) between said first and second propulsive propellers (21, 22) in such a manner as to present an inter-fuselage space (60) having no propeller between said fuselages (51, 52), each fuselage (51, 52) including at least one undercarriage of said landing gear (30).
    Type: Application
    Filed: February 14, 2014
    Publication date: August 28, 2014
    Applicant: Airbus Helicopters
    Inventor: Jean NICOLA
  • Publication number: 20140217229
    Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes.
    Type: Application
    Filed: September 14, 2012
    Publication date: August 7, 2014
    Applicant: SINGAPORE TECHNOLOGIES AEROSPACE LTD
    Inventor: Keen Ian Chan
  • Patent number: 8798814
    Abstract: A method and apparatus for managing a flight of a rotorcraft. Parameters for the flight of the rotorcraft are identified. A number of regions, above a terrain, to be avoided by the rotorcraft during the flight of the rotorcraft over the terrain are identified using the parameters for the flight of the rotorcraft. Information about the number of regions is displayed on a display device during the flight of the rotorcraft.
    Type: Grant
    Filed: January 27, 2011
    Date of Patent: August 5, 2014
    Assignee: The Boeing Company
    Inventors: William Foulke Spencer, V, Dan M. Wells
  • Patent number: 8788123
    Abstract: A device (10) for assisted piloting of an aircraft having a rotary wing with a plurality of second blades (3?) and a propulsion unit with a plurality of first blades (2?). The device includes control means (30, 40) for delivering a movement order (O) for moving in a direction, said device (10) having a processor unit (20) for transforming said order (O) into an acceleration setpoint (C) along said direction, and then for transforming said acceleration setpoint (C) into at least one required longitudinal attitude setpoint (?*) that is transmitted to a first automatic system (26) for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades (3?), and into a first required load factor setpoint (Nx*) in a longitudinal direction that is transmitted to a second automatic system (25) for maintaining load factor by controlling the collective pitch of the first blades.
    Type: Grant
    Filed: November 14, 2012
    Date of Patent: July 22, 2014
    Assignee: Airbus Helicopters
    Inventors: Marc Salesse-Lavergne, Nicholas Queiras, Paul Eglin
  • Patent number: 8777150
    Abstract: There is described a convertiplane comprising a pair of semi-wings, a first and a second rotor which may rotate about relative first axes and tilt about relative second axes together with first axes with respect to semi-wings between a helicopter mode and an aeroplane mode; first axes are, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and are, in use, substantially parallel to longitudinal direction in aeroplane mode; first and second rotors may tilt about relative second axes independently of each other.
    Type: Grant
    Filed: July 27, 2012
    Date of Patent: July 15, 2014
    Assignee: Agustawestland S.p.A.
    Inventor: James Wang
  • Publication number: 20140151494
    Abstract: A Vertical Take-off and Landing (VTOL) aerial vehicle (1, 46), e.g. a rotorcraft with long range and high cruising speed capability. The aerial vehicle (1, 46) has a torus-type fuselage (2) with radial inside a duct (5) and at least one main rotor (13, 26). A pair of lateral wings (40) are attached opposed to each other outside the fuselage (2) and at least one engine (18) drives said at least one main rotor (13, 26) and at least two propulsion means (24) fitted to each of said wings (40). The invention relates as well to a method of operating such a VTOL aerial vehicle (1, 46).
    Type: Application
    Filed: November 25, 2013
    Publication date: June 5, 2014
    Applicant: EUROCOPTER DEUTSCHLAND GMBH
    Inventor: Tomislav Cvrlje
  • Patent number: 8702031
    Abstract: VTOL amphibious aircraft comprising two fuselages spaced apart to enable the placement of single center wing and split ailerons, engine and rotor or fan such that they may be rotated from vertical flight to horizontal flight and back while center wing ailerons counter rotor torque. Out board wings remain fixed and the twin fuselages provide buoyant hulls to facilitate water landings. Standard aircraft components are employed such as a vertical tails and horizontal stabilizers.
    Type: Grant
    Filed: June 20, 2011
    Date of Patent: April 22, 2014
    Inventor: Richard David Morris
  • Publication number: 20140097290
    Abstract: An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.
    Type: Application
    Filed: October 4, 2013
    Publication date: April 10, 2014
    Inventor: Markus Leng