With Auxiliary Propulsion, Counter-troque Or Steering Device Patents (Class 244/17.19)
  • Patent number: 10465656
    Abstract: A rotor blade of a wind turbine, comprising a first rotor-blade portion and a second rotor-blade portion. In this case, the first and the second rotor-blade portion constitute a total length of the rotor blade and, upon a rotation of the rotor blade, the first rotor-blade portion and the second rotor-blade portion can be moved relative to each other, along a longitudinal axis of the rotor blade, as a result of a centrifugal force acting upon the rotor blade, in such a way that the total length of the rotor blade can be altered.
    Type: Grant
    Filed: June 17, 2015
    Date of Patent: November 5, 2019
    Assignee: Wobben Properties GmbH
    Inventor: Alexander Hoffmann
  • Patent number: 10427775
    Abstract: An aircraft with a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region being arranged inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement, the at least one fire protection zone accommodating at least one engine within the at least one associated firewall arrangement such that the associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage, wherein the at least one associated firewall arrangement comprises at least one air duct for ducting a hot air flow that is generated in operation of the aircraft independent from heat generation of the at least one engine.
    Type: Grant
    Filed: February 15, 2016
    Date of Patent: October 1, 2019
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Sebastian Mores, Frank Loeser, Johannes Frese, Ralf Braeutigam, Christian Wehle
  • Patent number: 10407163
    Abstract: An aircraft control system includes a propeller shaft assembly. Also included is first rotor operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades mounted thereto, the first blades disposed at a substantially identical nominal pitch during rotation of the first rotor, the first rotor rotatable in a first direction. Further included is a second rotor operatively coupled to the propeller shaft assembly and rotatable in a second direction, the second rotor having a second plurality of blades mounted thereto, wherein a pitch of the second blades cyclically changes during rotation of the second rotor, the first rotor and the second rotor disposed and rotated proximate a fixed wing of an aircraft about a common axis extending parallel to a longitudinal axis of the aircraft, cyclically changing the pitch of the second plurality of blades generating a moment for controlling the aircraft.
    Type: Grant
    Filed: January 31, 2017
    Date of Patent: September 10, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Chad M. Henze, Robert H. Perkinson
  • Patent number: 10407166
    Abstract: A rotor system of an aircraft includes a rotor hub rotatable about an axis of rotation, and a power generation system. The power generation system includes a generator stator and a generator rotor. The generator rotor is coupled to the rotor hub. At least one induction type magnet is mounted to at least one of the generator stator and the generator rotor. A control unit is operably coupled to the at least one induction type magnet to selectively deliver power to the at least one induction type magnet to alter a torque of the rotor hub without decreasing a rotational speed of the rotor hub.
    Type: Grant
    Filed: January 8, 2018
    Date of Patent: September 10, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Timothy F. Lauder
  • Patent number: 10377479
    Abstract: The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: August 13, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Thomas Dewey Parsons, Carlos Alexander Fenny, Erik John Oltheten
  • Patent number: 10329015
    Abstract: Generally, an inventive aircraft (1) having at least a first lift body (2) and a second lift body (3) each controllably configurable to correspondingly generate an amount of lift (4) sufficient to remain aloft at a first elevation (5) and a second elevation (6) a sufficient distance apart (7) to subject the first lift body (2) and the second lift body (3) to sufficiently disparate fluid flow characteristics (8) to propel the aircraft (1).
    Type: Grant
    Filed: May 18, 2012
    Date of Patent: June 25, 2019
    Inventor: Henry C. DeBey
  • Patent number: 10308357
    Abstract: Methods and apparatus to control pitch and twist of blades are disclosed. An example apparatus includes a twist input assembly driven by a drive shaft that drives a rotation of blades of a rotorcraft, the twist input assembly comprising a twist shaft, a first gear set driven by the drive shaft, and a first frequency controller to create a first rotational speed difference between a first gear of the first gear set and the drive shaft, the first rotational speed difference to cause the twist shaft to oscillate. The examples apparatus includes a pitch input assembly driven by the drive shaft, the pitch input assembly comprising a pitch link in communication with a first one of the blades of the rotorcraft, a second gear set driven by the drive shaft, and a second frequency controller to create a second rotational speed difference between a second gear of the second gear set and the drive shaft, the second rotational speed difference to cause the pitch link to oscillate.
    Type: Grant
    Filed: September 30, 2014
    Date of Patent: June 4, 2019
    Assignee: The Boeing Company
    Inventors: Ian M. Gunter, Thomas R. Kenow, Chris Jorgens
  • Patent number: 10301011
    Abstract: An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.
    Type: Grant
    Filed: July 28, 2015
    Date of Patent: May 28, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Michael Peter Strauss, Mark Denton Bystry, Jr., Michael Joseph DeVita
  • Patent number: 10293927
    Abstract: While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.
    Type: Grant
    Filed: April 19, 2018
    Date of Patent: May 21, 2019
    Assignee: Kitty Hawk Corporation
    Inventors: Gregory Mainland Horn, Damon Vander Lind
  • Patent number: 10279899
    Abstract: A strake may extend along a portion of an approaching side of a tail boom of a helicopter. A number of vortex generators (VGs) may extend along a portion of a retreating side of the tail boom. For tail booms with circular cross sections, the strake and the VGs are positioned between approximately 5 and 15 degrees below a horizontal plane of the tail boom when viewed end on, on respective sides of the tail boom. For tail booms with non-circular cross sections, the strake and the VGs is positioned between approximately 5 and 15 degrees above a location where a change in curvature is greatest (e.g., where flow separation would otherwise occur) on a bottom half of the tail boom when viewed end on, on respective sides of the tail boom. A fairing may be located on the retreating side on the upper half of the tail boom, to create an asymmetric profile.
    Type: Grant
    Filed: June 29, 2016
    Date of Patent: May 7, 2019
    Assignee: BLR AEROSPACE L.L.C.
    Inventors: Michael Carpenter, Daniel A. Smith
  • Patent number: 10259575
    Abstract: A system and method for counteracting a rotor moment of one or more rotors of a coaxial rotor helicopter includes receiving signals with a processor indicative of a displacement command from a controller during a flight maneuver; receiving one or more signals with the processor from a sensor indicative of an airspeed and air density for the helicopter; determining a commanded rate of acceleration for the helicopter during the flight maneuver; and adjusting with one or more control servos a cyclic pitch for the one or more rotors to counteract the rotor moment during the flight maneuver.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: April 16, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Matthew T. Luszcz, Matthew A. White, Kenneth S. Wittmer
  • Patent number: 10259433
    Abstract: An electromechanical actuator is provided comprising a housing, a rotor disposed in the housing, an selective gearbox mechanically coupled to the rotor and disposed in the housing, a first output of the selective gearbox configured to rotate at a different speed than the rotor, and a second output of the selective gearbox configured to rotate at a same speed as the rotor.
    Type: Grant
    Filed: December 6, 2016
    Date of Patent: April 16, 2019
    Assignee: GOODRICH CORPORATION
    Inventors: Kevin Rehfus, David Drennen, Robert French
  • Patent number: 10243424
    Abstract: A generator with relatively high (Length/Diameter) aspect ratio, which may be mounted within the rotating mast of a helicopter, and which may generate power that is conditioned by a rotating power conditioning unit and delivered to the rotating rotor blades without the use of slip rings, is disclosed. The generator may be arranged to take advantage of the available space within the mast. Temperature of the mast and generator may be controlled by varying the wall thickness of the mast wall and using cooling fins on the mast and a cooling dome.
    Type: Grant
    Filed: April 17, 2014
    Date of Patent: March 26, 2019
    Assignee: OECO, LLP
    Inventor: Bernard Anthony Raad
  • Patent number: 10220942
    Abstract: In some embodiments, a rotorcraft includes a fuselage having a rotor hub assembly protruding therefrom that is rotatable relative thereto. A generator having an armature is mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly. A braking unit is in selective electrical communication with the generator. The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly.
    Type: Grant
    Filed: August 19, 2016
    Date of Patent: March 5, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventor: John Robert Wittmaak
  • Patent number: 10167078
    Abstract: An aircraft assembly is provided and includes a first member extending from an aircraft airframe, a propeller, which is drivable to rotate and a secondary member on which the propeller is supportable and which is aerodynamically pivotable with respect to the first member.
    Type: Grant
    Filed: September 16, 2016
    Date of Patent: January 1, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Peter James Waltner
  • Patent number: 10112697
    Abstract: An aircraft is provided and includes an airframe having an upper section and a tail section, a main rotor assembly operably disposed at the upper section and one or more tail rotor assemblies operably disposed at the tail section. The one or more tail rotor assemblies respectively include one or more articulated propellers with thrust vectoring capability that are each independently rotatable about a respective variable rotational axis.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: October 30, 2018
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Peter James Waltner
  • Patent number: 10106255
    Abstract: A tiltrotor aircraft can include a pylon rotatable about a conversion axis. A first differential planetary assembly can include a first housing; a first ring gear; a first differential planetary gear having a first output portion; and a first differential sun gear. A second differential planetary assembly can include a second housing; a second ring gear; a second differential planetary gear having a second output portion; and a second differential sun gear. The first output portion is coupled to the second housing such that the second housing rotates at a first output speed. Further, the second output portion is coupled to the shaft, the shaft being coupled to the pylon such that rotation of the shaft rotates the pylon.
    Type: Grant
    Filed: May 14, 2015
    Date of Patent: October 23, 2018
    Inventors: Charles Eric Covington, Eric S. Olson, David R. Bockmiller, Carlos A. Fenny
  • Patent number: 10106253
    Abstract: In some embodiments, an aircraft includes a fuselage having a forward portion and an aft portion. First and second ducted fans are supported by the forward portion of the fuselage. The first and second ducted fans are tiltable relative to the fuselage between a generally horizontal orientation, in a vertical takeoff and landing mode, and a generally vertical orientation, in a forward flight mode. A tailboom having an aft station extends from the aft portion of the fuselage. A cross-flow fan is disposed in the aft station of the tailboom and is operable to generate a pitch control moment.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: October 23, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kirk Landon Groninga, Daniel Bryan Robertson
  • Patent number: 10066608
    Abstract: A method for repairing an electrical heating element of a wind turbine rotor blade has the steps of identifying a region of the heating element that has a defect and applying a thermally conductive repair layer to the identified region. The repair layer is thermally conductive and is electrically insulating at least on an underside facing the defect.
    Type: Grant
    Filed: February 10, 2015
    Date of Patent: September 4, 2018
    Assignee: Nordex Energy GmbH
    Inventors: Bernhard Krueger, Tobias Ahrens
  • Patent number: 10060350
    Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.
    Type: Grant
    Filed: April 13, 2015
    Date of Patent: August 28, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Harold W. Hipsky, Thomas M. Zywiak
  • Patent number: 10035590
    Abstract: A shrouded rotor assembly for an aircraft. The shrouded rotor assembly comprises a stator hollow structure comprises formed from a plurality of composite angular segments. Each composite angular segment includes: a core arched section of a central hub casing, a peripheral rim section of an external hollow duct and a pair of angularly opposed sliced portions, respectively for one of a pair of guide vanes. The resulting stator hollow structure is a unitary one-piece, integrating together continuously the composite angular segments. The invention typically applies e.g. to aircrafts such as rotary wing aircrafts.
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: July 31, 2018
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
    Inventors: Stefan Probst, Marc Nothen, Christian Wehle
  • Patent number: 9975629
    Abstract: While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.
    Type: Grant
    Filed: May 18, 2017
    Date of Patent: May 22, 2018
    Assignee: Kitty Hawk Corporation
    Inventors: Gregory Mainland Horn, Damon Vander Lind
  • Patent number: 9944388
    Abstract: A method of rotorcraft state control includes receiving command input indicative of an intended state change in a rotorcraft. The method also includes issuing command output to a rotor actuation system to carry out the intended state change by varying drag and/or efficiency on one or more rotor blades of the rotorcraft. Issuing command output can include issuing a command output to the rotor actuation system to carry out the intended state change by increasing drag at a substantially constant thrust on one or more rotor blades of the rotorcraft.
    Type: Grant
    Filed: August 26, 2016
    Date of Patent: April 17, 2018
    Assignee: Sikorsky Aircraft Corporation
    Inventor: Peter J. Waltner
  • Patent number: 9919488
    Abstract: Methods of manufacturing rotor blade components for a wind turbine and rotor blade components produced in accordance with such methods are disclosed. In one embodiment, the method generally includes heating first and second sheets of thermoplastic material to a forming temperature; placing the first sheet of thermoplastic material within a first half of a thermoforming mold and the second sheet of thermoplastic material in an opposite, second half of the thermoforming mold; forming the first sheet of thermoplastic material to the first half of the thermoforming mold; forming the second sheet of thermoplastic material to the second half of the thermoforming mold; compressing the first and second halves of the thermoforming mold so as to join at least a portion of the first and second sheets together; and, releasing the joined first and second sheets of thermoplastic material from the thermoforming mold so as to form the rotor blade component.
    Type: Grant
    Filed: March 19, 2014
    Date of Patent: March 20, 2018
    Assignee: General Electric Company
    Inventors: Michael Christopher Booth, Scott Gabell Riddell, James Robert Tobin, William Max Gobeli
  • Patent number: 9902491
    Abstract: A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base.
    Type: Grant
    Filed: March 5, 2015
    Date of Patent: February 27, 2018
    Inventors: Alistair K. Chan, Jesse R. Cheatham, III, Hon Wah Chin, William David Duncan, Roderick A. Hyde, Muriel Y. Ishikawa, Jordin T. Kare, Tony S. Pan, Robert C. Petroski, Clarence T. Tegreene, David B. Tuckerman, Thomas Allan Weaver, Lowell L. Wood, Jr.
  • Patent number: 9841077
    Abstract: Some examples of rotating shaft damping with electro-rheological fluid can be implemented as a method. At least a portion of a circumferential surface area of a portion of a rotorcraft rotating shaft is surrounded with multiple hollow members. Each hollow member includes an electro-rheological fluid having a viscosity that changes based on an electric field applied to the electro-rheological fluid. A vibration of the rotorcraft rotating shaft is controlled by changing the viscosity of the electro-rheological fluid in response to the electric field applied to the electro-rheological fluid.
    Type: Grant
    Filed: June 18, 2014
    Date of Patent: December 12, 2017
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brian S. M. Modrezejewski, Steven Spears
  • Patent number: 9826792
    Abstract: Devices that facilitate offsetting of weight of heard borne equipment such as helmets and other devices associated with helmets are provided. Through the use of pivots and an arm assembly that distributes weight from a person's head to his or her torso, additional and heavier objects can be carried on a person's head without causing undesirable levels of discomfort.
    Type: Grant
    Filed: October 28, 2014
    Date of Patent: November 28, 2017
    Assignee: Creative Engineering, LLC
    Inventors: Paul Dowd, Philippe M. Putzeys
  • Patent number: 9725164
    Abstract: A rotorcraft extends longitudinally along a first anteroposterior plane separating a first side from a second side of the rotorcraft. The rotorcraft includes at least one main rotor, an auxiliary rotor, and at least one steerable airfoil. The rotorcraft further includes a processor unit connected to a first measurement system configured to measure a current value of a speed parameter (V) of the rotorcraft and to a second measurement system configured to measure a current value of a power parameter (W) of a power plant of the rotorcraft. The processor unit is configured to adjust the deflection angle of the airfoil as a function of the current speed and power parameter values (V, W) to cause the auxiliary rotor to move towards at least one predetermined operating point which optimizes performance of the rotorcraft and minimizes noise generated by the auxiliary rotor.
    Type: Grant
    Filed: December 9, 2014
    Date of Patent: August 8, 2017
    Assignee: Airbus Helicopters
    Inventor: Manousos Kelaidis
  • Patent number: 9663237
    Abstract: A vertical takeoff and landing aircraft (101) for transporting persons or loads, including a plurality of preferably equivalent and redundant electric motors (3) and propellers (2), substantially arranged in one surface, wherein each propeller is assigned an individual electric motor to drive the propeller, the aircraft being characterized in that at least one attitude sensor is provided for attitude control of the aircraft (101) in an active signal connection to at least one signal processing unit which is designed or set up to automatically perform the attitude control based on measurement data from the attitude sensor by regulating the speed of at least some of the electric motors (3), preferably with signal actions of the speed controller assigned to each electric motor such that the aircraft (101) is positioned in space with the surface defined by the propeller (2) substantially horizontal at all times, without control input by a pilot or a remote control.
    Type: Grant
    Filed: February 20, 2013
    Date of Patent: May 30, 2017
    Assignee: e-volo GmbH
    Inventors: Thomas Senkel, Stephan Wolf, Alexander Zosel
  • Patent number: 9656747
    Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: May 23, 2017
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Ken Shundo, Mithat Yuce, Frank B. Stamps
  • Patent number: 9630713
    Abstract: Methods, devices, and systems of various embodiments are disclosed for operating a UAV. Various embodiments include a UAV having a pivotal platform, a tilt assembly, and a processor. The pivotal platform may be configured to selectively tilt relative to a frame of the UAV. The tilt assembly may be configured to change a tilt angle of the pivotal platform. The processor may be coupled to the tilt assembly and configured with processor-executable instructions to determine whether to implement a first change of the tilt angle of the pivotal platform in order to causes a first adjustment of a lift/drag profile of the UAV. The processor may also be configured to activate the tilt assembly to implement the determined first change in the tilt angle of the pivotal platform in response to determining that the first change should be implemented.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: April 25, 2017
    Assignee: QUALCOMM Incorporated
    Inventor: William Henry Von Novak, III
  • Patent number: 9616995
    Abstract: An aircraft (10) comprising a fuselage (12) having a longitudinal axis (16), at least one helicopter main rotor (40) operably mounted to the fuselage (12), the at least one helicopter main rotor (40) comprising rotor blades (41) rotatable about a rotation axis (44), wherein the rotor blades (41) can be stopped in flight and adapted to provide symmetrical wing surfaces relative to the longitudinal axis (16); and the aircraft (10) having at least one control surface (62, 82) operable to provide a relative airflow (306) in flight substantially aligned with the rotation axis (44) of the at least one helicopter main rotor (40).
    Type: Grant
    Filed: December 6, 2013
    Date of Patent: April 11, 2017
    Assignee: STOPROTOR TECHNOLOGY PTY LTD
    Inventor: Rowan John Watkins
  • Patent number: 9616994
    Abstract: An asymmetric multirotor helicopter has a structure supporting at least one main and two secondary propulsion systems. A flight control unit controls the helicopter by varying the relative speed of each of the main and secondary propulsion systems. Each main propulsion system includes at least one main motor drive and a main drive shaft that carries and propels a main differential contra-rotating transmission configured to share the power provided by the main drive shaft with two contra-rotating output shafts. Each secondary propulsion system includes at least one secondary motor drive and a secondary drive shaft that carries and propels respective secondary propulsion blades. The two contra-rotating output shafts support and propel for mutually contra-rotation motion two sets of main propulsion blades. The main drive shaft rotates in the same direction as one of the secondary drive shafts and at least one secondary drive shaft rotates in an opposite direction.
    Type: Grant
    Filed: March 25, 2015
    Date of Patent: April 11, 2017
    Inventor: Yefim Kereth
  • Patent number: 9604729
    Abstract: An aircraft control system includes a co-axial, counter-rotating propeller shaft assembly. Also included is a first rotor operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades mounted thereto, wherein the first plurality of blades are disposed at a substantially identical nominal pitch during rotation of the first rotor. Further included is a second rotor operatively coupled to the propeller shaft assembly, the second rotor having a second plurality of blades mounted thereto, wherein a pitch of the second plurality of blades is configured to cyclically change during rotation of the second rotor.
    Type: Grant
    Filed: October 16, 2013
    Date of Patent: March 28, 2017
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Chad M. Henze, Robert H. Perkinson
  • Patent number: 9545903
    Abstract: An electromechanical actuator is provided comprising a housing, a rotor disposed in the housing, an selective gearbox mechanically coupled to the rotor and disposed in the housing, a first output of the selective gearbox configured to rotate at a different speed than the rotor, and a second output of the selective gearbox configured to rotate at a same speed as the rotor.
    Type: Grant
    Filed: February 2, 2015
    Date of Patent: January 17, 2017
    Assignee: GOODRICH CORPORATION
    Inventors: Kevin Rehfus, David Drennen, Robert French
  • Patent number: 9527577
    Abstract: A rotorcraft with a fuselage and at least one main rotor, the at least one main rotor being drivable for controlling an associated pitch attitude of the rotorcraft in operation, and the fuselage being equipped with at least one passive wing-type aerodynamic device that is adapted for generating independently of the associated pitch attitude a lift force acting on the fuselage, the lift force being oriented perpendicular to an air flow that is directed in operation of the rotorcraft against the passive wing-type aerodynamic device.
    Type: Grant
    Filed: January 26, 2015
    Date of Patent: December 27, 2016
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventor: Martin Embacher
  • Patent number: 9453516
    Abstract: An inside vessel arrangement (5) is fixedly secured in a stator hollow structure (8) and has at least one enlarged static circumference housing (20), and an aerodynamic outer toroid spoiler (18) has an outer external surface (35) complementary to the static circumference housing (20). The aerodynamic outer toroid spoiler (18) radially secured to each of outer tips (23) of rotor blades (10) of a driven rotor system (7). A torus air gap (G) is provided, so that an outer laminar flux (56) is admitted simultaneously with an inlet inner stream (54) and guided through the torus air gap (G), with the inlet main stream and outer laminar flux being converged to merge together in single outlet control airflow (C). The invention typically applies e.g. to vehicles (A) such as aircrafts like rotary wing aircrafts.
    Type: Grant
    Filed: April 9, 2014
    Date of Patent: September 27, 2016
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventor: Wolfgang Kreitmair-Steck
  • Patent number: 9409643
    Abstract: A helicopter with a fuselage (4), at least one engine, a roll axis, at least one main rotor, and at least one housing (2) mounted to said fuselage (4). An air inlet (8) and an air outlet (7) are provided along at least a part of a circumference of the at least one housing (2), said air inlet (8) and said air outlet (7) being formed by angularly offset and separate gaps between an inside segment (33) and an outside segment (34) essentially extending respectively longitudinally in direction of said roll axis. At least one rotatable compressor (1) with a plurality of airfoil blades (6) is provided radial inside said at least one housing (2) between said air inlet (8) and said air outlet (7), said at least one rotatable compressor (1) being drivable by said at least one engine about a fan axis (5) and each chord of said airfoil blades (6) is essentially radial oriented with regard to said fan axis (5).
    Type: Grant
    Filed: May 22, 2014
    Date of Patent: August 9, 2016
    Assignee: AIRBUS HELICOPTERS DEUTSCHLAND GmbH
    Inventors: Sebastian Mores, Alessandro D'Alascio, Marius Bebesel
  • Patent number: 9376213
    Abstract: This invention relates to a method and apparatus for controlling power distribution in an electrical aircraft propulsive system having at least one electrical propulsion unit which includes a plurality of rotatable blades, each blade having an adjustable pitch; a pitch adjusting mechanism for adjusting the pitch of the blades; at least one electrical machine electrically connected to the electrical propulsion unit so as to provide electrical power when in use; and, a control system, the method comprising the steps of: determining the required propulsion; determining whether the propulsive units are delivering the required propulsion; and, adjusting the pitch angle of the blades of at least one propulsive unit so as to increase or decrease the propulsion provided by that propulsive unit.
    Type: Grant
    Filed: October 4, 2012
    Date of Patent: June 28, 2016
    Assignee: ROLLS-ROYCE plc
    Inventor: Andrew Martin Rolt
  • Patent number: 9297290
    Abstract: An exhaust system for reducing infrared emissions of a rotary wing aircraft includes an exhaust duct having a fore end for connection with an aft turbine section of an engine of the rotary wing aircraft, the exhaust duct having an aft end having an exhaust opening to expel engine exhaust proximate to a tail fairing of the rotary wing aircraft; and a drive shaft collocated with the exhaust duct, the drive shaft configured to provide rotational force to an aft propeller of the rotary wing aircraft.
    Type: Grant
    Filed: October 9, 2013
    Date of Patent: March 29, 2016
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Joseph Pantalone, III, John S. Chapkovich, III, Ashley Devito, Erez Eller
  • Patent number: 9278754
    Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: March 8, 2016
    Inventor: Walter Gerd Oskar Sonneborn
  • Patent number: 9199720
    Abstract: A stationary ground tube for use in an aircraft rotor fairing includes a first cylindrical portion including a first bore aligned along a longitudinal axis, the cylindrical body portion having a tubular body from a first end to a second end; and a second cylindrical portion coupled to the first cylindrical portion, the second cylindrical portion including a second bore aligned along the longitudinal axis. The second cylindrical portion is coupled to the aircraft rotor fairing via at least one attachment device.
    Type: Grant
    Filed: August 31, 2011
    Date of Patent: December 1, 2015
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Michael C. Lonergan, Fred W. Kohlhepp, Robert D. Beatty
  • Patent number: 9139298
    Abstract: A multirotor rotorcraft control system for effectuating flight control. The multirotor rotorcraft has at least two or more rotor assemblies. The control system preferably includes at least one flap for each rotor blade and at least one actuator for each rotor assembly. The rotor assemblies and the flap(s) and actuator(s) for each assembly are used for flight control. This invention does not require a complex fixed pitch control system or a high frequency servo control system. This invention can control blade angle of attack during autorotation.
    Type: Grant
    Filed: August 1, 2013
    Date of Patent: September 22, 2015
    Inventors: Alfred Alan Gates, Fu-Shang John Wei
  • Publication number: 20150142219
    Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps.
    Type: Application
    Filed: May 28, 2014
    Publication date: May 21, 2015
    Applicant: GROEN BROTHERS AVIATION, INC.
    Inventor: Walter Gerd Oskar Sonneborn
  • Patent number: 8991747
    Abstract: A method of modifying a helicopter includes providing a tail boom of the helicopter and modifying a surface profile of the tail boom on at least a first side of the tail boom to improve flow attachment of air flowing over the first side of the modified tail boom during operation of the helicopter. The first side of the tail boom is located on an opposite side of the tail boom from a second side of the tail boom towards which a main rotor blade of the helicopter approaches during rotation.
    Type: Grant
    Filed: April 26, 2013
    Date of Patent: March 31, 2015
    Assignee: BLR AeroSpace, L.L.C.
    Inventor: Robert J. Desroche
  • Patent number: 8985503
    Abstract: A method of modifying a helicopter includes providing a tail boom of the helicopter. The tail boom includes a first side located on an opposite side of the tail boom from a second side of the tail boom. A main rotor blade of the helicopter approaches the second side of the tail boom during rotation. The first side and the second side of the tail boom include asymmetrical surface profiles about a vertical plane of the tail boom. The method further includes securing a plurality of vortex generators to the first side of the tail boom.
    Type: Grant
    Filed: March 27, 2014
    Date of Patent: March 24, 2015
    Assignee: BLR AeroSpace, L.L.C.
    Inventor: Robert J. Desroche
  • Patent number: 8985502
    Abstract: An aircraft (1) provided with a main gearbox (3) fastened to a load-bearing structure (2) via at least three suspension bars (5). An active vibration absorber (10) is fastened around each suspension bar (5), each vibration absorber (10) being provided with a first mass (11) connected to the associated suspension bar (5) via first resilient means (21), and with a second mass (12) connected to the first mass (11) via second resilient means (22), said vibration absorber (10) having a force generator (15) interposed between the first mass (11) and the second mass (12) and inputting a control force on being instructed by a control unit (16) as a function of information coming from at least one first measurement sensor (17) for sensing monitoring parameters for monitoring the associated suspension bar.
    Type: Grant
    Filed: May 22, 2012
    Date of Patent: March 24, 2015
    Assignees: Airbus Helicopters, Ecole Naitonale Supérieure d'Arts et Métiers—E.N.S.A.M
    Inventors: Tomasz Krysinski, Francois Malburet
  • Patent number: 8985501
    Abstract: A vibration control system includes four mass discs located at a central axis and rotatable thereabout. Each mass disc includes a mass secured thereto wherein rotation of the four mass discs creates a vibratory force output. A power transfer assembly is located between adjacent mass discs of the four mass discs and is configured to transfer rotational energy between the adjacent mass discs. The power transfer assembly includes a power transfer shaft rotatable about a power transfer shaft axis and a power transfer disc connected to the power transfer shaft and in frictional contact with each of the adjacent mass discs at a contact point. When the power transfer shaft is rotated, a radial location of the contact point at each of the adjacent mass discs relative to the central axis is changed, altering the vibratory force.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: March 24, 2015
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Erez Eller, Todd A. Garcia
  • Patent number: 8979015
    Abstract: A tail assembly (10) for a rotorcraft (20), the tail assembly (10) comprising a first stabilizer (3) extending transversely on either side of an anteroposterior plane (P1), and a second stabilizer (4, 4?) extending in elevation. Two propellers (31, 41) positioned on either side of the anteroposterior plane (P1) provide the rotorcraft (20) with at least part of its yaw control and its propulsion. The axes of the two propellers (31, 41) are situated in a plane substantially parallel to the horizontal plane (P3) and they intersect at a position in the anteroposterior plane (P1) of the rotorcraft (20) that is located between the front end of the rotorcraft (20) and the propellers (31, 41). Using both propellers (31, 41) of the tail assembly (10) simultaneously makes it possible to provide the rotorcraft (20) with longitudinal thrust while conserving its transverse thrust for the anti-torque function, it being possible to control these two thrusts independently.
    Type: Grant
    Filed: November 16, 2012
    Date of Patent: March 17, 2015
    Assignee: Airbus Helicopters
    Inventor: Christophe Gaillard
  • Patent number: 8967525
    Abstract: A helicopter with a longitudinal axis and with a tail portion (1) with a transverse duct (6) and a drive shaft (23) inside a drive shaft fairing (14) for an aerodynamic and acoustic optimized counter-torque device (2) supported within said transverse duct (6).
    Type: Grant
    Filed: June 4, 2013
    Date of Patent: March 3, 2015
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Sascha Schneider, Dieter Schimke, Christian Wehle