Responsive To Carrier Tilt Patents (Class 416/102)
  • Patent number: 11822348
    Abstract: A flight vehicle includes a main body, a thrust generating unit, and one or more joints. The thrust generating unit includes one or more thrust generating subunits. Each joint is respectively associated with a corresponding thrust generating subunit. Each joint couples a corresponding thrust generating subunit to the main body and permits the associated thrust generating subunit to freely pivot relative to the main body. Each thrust generating subunit includes a plurality of thrust generators. Within each thrust generating subunit, one or more of the thrust generators is arranged to generate thrust that induces a first torque in one direction along a circumference of a circle centered on a first pivot axis, and other one or more of the thrust generators is arranged to generate thrust that induces a second torque in an opposite direction along the circumference of the circle centered on the first pivot axis.
    Type: Grant
    Filed: November 13, 2020
    Date of Patent: November 21, 2023
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Noriaki Katayama, Yuichi Kumamoto
  • Patent number: 11643196
    Abstract: An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.
    Type: Grant
    Filed: June 28, 2022
    Date of Patent: May 9, 2023
    Assignee: BETA AIR, LLC
    Inventors: Daniel Spira, Kyle Brookes, David Churchill, Mark Page
  • Patent number: 11505309
    Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.
    Type: Grant
    Filed: May 11, 2021
    Date of Patent: November 22, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Brady Garrett Atkins, Michael David Trantham, Paul David Ruckel
  • Patent number: 11499522
    Abstract: A rotor assembly includes a rotor mast, a rotor and a pivot arrangement. The rotor mast is for rotatable attachment of the rotor assembly to a support structure for rotation of the rotor assembly relative to the support structure about a rotation axis. The rotor has two rotor blades extending in a virtual plane in a longitudinal direction. The two rotor blades are arranged to be propelled by air flow. The pivot arrangement defines a pivot axis. The rotor is pivotably connected to the rotor mast for pivoting the two rotor blades simultaneously relative to the rotor mast about the pivot axis. The longitudinal direction and a projection of said pivot axis in the virtual plane enclose a constant acute angle in the virtual plane. A windmill and a wind farm includes the rotor assembly with a capacity in the range of 15-50 MW/km2.
    Type: Grant
    Filed: June 5, 2019
    Date of Patent: November 15, 2022
    Assignee: TouchWind Blue B.V.
    Inventor: Frederikus Van De Klippe
  • Patent number: 11472543
    Abstract: A convertiplane is described that has a fuselage with a first axis, a pair of half-wings, and a pair of rotors arranged on mutually opposite ends of the half-wings. The rotor comprises a mast hinged on a second axis and a plurality of blades hinged on the mast. The mast of the rotor can be tilted with the second axis about a third axis transversal to the second axis and with respect to the fuselage to transform the convertiplane between a helicopter mode and an aeroplane mode; the second axis is transversal to the first axis in the helicopter mode and is parallel to the first axis in the aeroplane mode. The rotor disc can be tilted about a fourth axis.
    Type: Grant
    Filed: December 27, 2018
    Date of Patent: October 18, 2022
    Assignee: LEONARDO S.P.A.
    Inventors: Paolo Brughera, Paolo Sportelli, Pierre Abdel Nour, Andrea Bernascone, Cristian Lilliu
  • Patent number: 11454280
    Abstract: A bearing system includes an inboard bearing assembly and an outboard bearing assembly. The inboard bearing assembly includes an inboard fitting and an inboard race. The inboard fitting includes a plate with a convex mating surface and a first aperture formed through the plate for receiving a blade root of a rotor blade. The inboard race comprising a concave mating surface configured to receive the convex mating surface a second aperture formed the inboard race. The outboard bearing assembly includes an outboard bearing assembly comprising an outboard fitting having an aperture formed therethrough for receiving the blade root of the rotor blade.
    Type: Grant
    Filed: June 30, 2020
    Date of Patent: September 27, 2022
    Assignee: Textron Innovations Inc.
    Inventors: George Matthew Thompson, Joseph Richard Carpenter, Jr., Paul Sherrill, Jonathan Andrew Knoll
  • Patent number: 11174011
    Abstract: A rotor assembly includes a first rotor hub and a second rotor hub. The second rotor hub is coupled to the first rotor hub via a shaft fairing. The first rotor hub has a flat first surface coupled to the shaft fairing and a curved second surface opposite the flat first surface. The second rotor hub has a flat first surface on the lower side and a curved second surface opposite the flat first surface.
    Type: Grant
    Filed: February 5, 2019
    Date of Patent: November 16, 2021
    Assignee: LOCKHEED MARTIN CORPORATION
    Inventors: Byung-Young Min, Patrick Ormande Bowles, Brian Ernest Wake, Margaret G. Battisti, Peter F. Lorber
  • Patent number: 10988243
    Abstract: A tension-torsion strap, for example for a rotor aircraft, including a continuous length of carbon fiber tow arranged in multiple loops to form an elongated member extending between opposing ends and a flexible cover encasing the carbon fiber tow.
    Type: Grant
    Filed: March 15, 2019
    Date of Patent: April 27, 2021
    Assignee: Bell Textron Inc.
    Inventors: Andrew Paul Haldeman, Gary Miller
  • Patent number: 10975732
    Abstract: A rotor turning device for balancing a rotor secured atop a tower of a wind turbine during installation and/or repair of one or more rotor blades of the wind turbine includes a hydraulic drive mechanism for operably engaging with a brake disc of the wind turbine. The brake disc is positioned adjacent to a gearbox of the wind turbine. The rotor turning device also includes a mounting device for securing the rotor turning device adjacent to the brake disc of the wind turbine. Thus, when the hydraulic drive mechanism engages the brake disc, the rotor is rotated to a desired position so as to position one or more rotor blades of the wind turbine in a balanced configuration.
    Type: Grant
    Filed: April 4, 2019
    Date of Patent: April 13, 2021
    Assignee: General Electric Company
    Inventors: Brian William Manikas, John Carl Bell, Sebastian Freiheit, Christoph Graf, Adam Sean Philip David Davis, Michael Royce Johnson, Ulrich Werner Neumann, Christoph Lammen
  • Patent number: 10676182
    Abstract: An electric propulsion system includes a static mast fixed to the airframe and a secondary mast positioned in overlapping arrangement with the static mast. The secondary mast defines an axis of rotation. An elastomeric bearing is arranged at an interface between the static mast and the secondary mast. An actuator assembly includes at least one actuator connected to the secondary mast. The actuator assembly is operable to pivot the secondary mast relative to the axis of rotation.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: June 9, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventor: Timothy F. Lauder
  • Patent number: 10577096
    Abstract: A flapping control system for a proprotor assembly of a tiltrotor aircraft includes one or more sensors operable to detect one or more flight parameters of the tiltrotor aircraft to form sensor data. The sensors include a proprotor flapping sensor to detect a proprotor flapping measurement. The flapping control system includes a flapping control module in data communication with the sensors. The flapping control module includes a maneuver detection module to detect whether the tiltrotor aircraft is in a maneuver mode using the sensor data. The flapping control module identifies a maneuver flapping threshold associated with the maneuver mode. The flapping control module generates a swashplate command using the proprotor flapping measurement and the maneuver flapping threshold, and sends the swashplate command to the proprotor assembly to reduce flapping of the proprotor assembly.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: March 3, 2020
    Assignee: Textron Innovations Inc.
    Inventors: Brad John Roberts, Paul David Ruckel
  • Patent number: 10569870
    Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.
    Type: Grant
    Filed: November 18, 2016
    Date of Patent: February 25, 2020
    Assignee: Textron Innovations Inc.
    Inventors: Jouyoung Jason Choi, Gary Miller, Richard Erler Rauber, Thomas Clement Parham, Jr., Alan Carl Ewing, Frank Bradley Stamps
  • Patent number: 10350753
    Abstract: A device and method for easily detecting an abnormality of a joint part of a delta-type parallel link robot having a link ball structure, by estimating a friction torque of a ball joint of the robot. A controller of the robot has: a control section configured to control the motion of the robot; a torque measurement section configured to measure or calculate, during the robot is operated, an amount of change in a drive torque, based on a current value of the motor, before and after the robot represents a specified posture where a sign of a relative angular velocity between a ball and a housing of the ball joint is changed; and a judgment section configured to judge that, when the measured amount of change in the drive torque exceeds a predetermined threshold, a friction state of the ball joint corresponding to the motor is abnormal.
    Type: Grant
    Filed: May 30, 2017
    Date of Patent: July 16, 2019
    Assignees: FANUC CORPORATION, TOKYO INSTITUTE OF TECHNOLOGY
    Inventors: Kenichiro Abe, Yunfeng Wu, Hikaru Yamashiro, Yukio Takeda, Yusuke Sugahara, Daisuke Matsuura, Masumi Ohno
  • Patent number: 10279898
    Abstract: A rocket or ballistic launch rotary wing air vehicle may include a rocket or ballistic launch propulsion system for launching the vehicle, a rotary wing flight system for providing powered flight comprising dual counter rotating coaxial rotors, and a control system programmed to adjust the pitch of a rotor to anyh determined degree of pitch independently of a flap angle of the flap hinge during a transition of the dual counter rotating coaxial rotors from a stowed position to a deployed position.
    Type: Grant
    Filed: May 23, 2012
    Date of Patent: May 7, 2019
    Assignee: BLUE BEAR SYSTEMS RESEARCH LIMITED
    Inventors: John Green, Philip Geoghegan, Michael Alexander Snook
  • Patent number: 9428262
    Abstract: A hydraulic system of an aircraft, the system comprising at least one servo-control, each servo-control comprising at least one cylinder together with a drive rod and a piston arranged in each cylinder. Between each cylinder of servo-control and the drive rod of that servo-control, at least one servo-control presents main sealing means with controlled leakage allowing a hydraulic fluid to leak out from the cylinder, the hydraulic system further comprising at least one enclosure, each cylinder of the servo-control being arranged inside the enclosure so that the fluid is collected in the enclosure.
    Type: Grant
    Filed: April 14, 2015
    Date of Patent: August 30, 2016
    Assignee: Airbus Helicopters
    Inventors: Jean-Romain Bihel, Clement Coic, Thibaut Marger, Gerard Couderc
  • Patent number: 9410531
    Abstract: A wind turbine generator includes a plurality of blades that radially protrude from a rotor head about an axis of a main shaft, and a pitch axis rotation mechanism that is provided in the rotor head to rotate the blade about a pitch axis P. The pitch axis rotation mechanism includes an actuator that is supported by the rotor head, and has a stretchable rod which is supported by the rotor head, and a link structure that links the rod to the blade. The actuator extends on the axis of the main shaft.
    Type: Grant
    Filed: March 6, 2012
    Date of Patent: August 9, 2016
    Assignee: THK CO., LTD.
    Inventor: Yuki Hayashi
  • Patent number: 8770934
    Abstract: A teeter mechanism for a multiple-bladed wind turbine includes a rotor shaft operable to rotate about a first axis. A spherical member is rotatable about the first axis along with the rotor shaft. A plurality of turbine blades is mounted to a rotor hub. The rotor hub rotationally drives the rotor shaft, and is operable to teeter about the spherical member such that the rotor hub rotates about the first axis in a first position and rotates about a second axis offset from the first axis in a second, teeter position.
    Type: Grant
    Filed: December 16, 2009
    Date of Patent: July 8, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Robert H. Perkinson
  • Patent number: 8529205
    Abstract: A blade pitch control mechanism for a propeller assembly (10) includes an actuation shaft (24) having a spherical member (28) located at a propeller axis (22). A yoke (40) is located around the spherical member (28) and is rotatable thereon about a yoke tilt axis (62) substantially perpendicular to the propeller axis (22). The yoke (40) includes a plurality of propeller blade attachments (44), each receptive of a propeller blade (14). The plurality of blade attachments (44) are configured such that rotation of the yoke (40) about the yoke tilt axis (62) results in rotation of each propeller blade (14) about a blade pitch change axis (48).
    Type: Grant
    Filed: December 10, 2009
    Date of Patent: September 10, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Robert H. Perkinson
  • Patent number: 8303248
    Abstract: An anti-torque mechanism which permits a full range of swashplate assembly motion. The anti-torque mechanism generally includes an anti-torque shaft and a compound bearing mounted thereto to provide five-degrees-of-freedom (spherical-linear-elastomeric) so as to permit a swashplate attachment point to move axially in response to pitch input; pivot in response to swashplate tilt; and move in/out in the radial direction.
    Type: Grant
    Filed: October 3, 2006
    Date of Patent: November 6, 2012
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Pedro L. Cabrera, Stephen V. Poulin, Francis D. Federici
  • Patent number: 8287237
    Abstract: A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub (31) and a plurality of step-over arms (61) connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links (55) connects one of the step-over arms (61) to a flight control system for pivoting the connected step-over arm (61) about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links (69) connects one of the step-over arms (61) to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.
    Type: Grant
    Filed: December 8, 2006
    Date of Patent: October 16, 2012
    Assignee: Textron Innovations Inc.
    Inventors: Frank B. Stamps, Richard E. Rauber, David A. Popelka, Patrick R. Tisdale, Thomas C. Campbell, Keith Stanney, James L. Braswell, Jr., Mark Wasikowski, Tom Donovan, Bryan Baskin, John J. Corrigan, III, Ryan Smith
  • Patent number: 7530785
    Abstract: A wind turbine with improved response to wind conditions is provided. Blade flap angle motion is accompanied by a change in pitch angle by an amount defining a pitch/flap coupling ratio. The coupling ratio is non-constant as a function of a flap angle and is preferably a substantially continuous, non-linear function of flap angle. The non-constant coupling ratio can be provided by mechanical systems such as a series of linkages or by configuring electronic or other control systems and/or angle sensors. A link with a movable proximal end advantageously is part of the mechanical system. The system can provide relatively large coupling ratios and relatively large rates of coupling ratio changes especially for near-feather pitches and low flap angles.
    Type: Grant
    Filed: April 13, 2005
    Date of Patent: May 12, 2009
    Assignee: The Wind Turbine Company
    Inventors: Kenneth J. Deering, Keith P. Wohlwend
  • Patent number: 7037072
    Abstract: A preferred embodiment of a rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft includes a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft, and a hub pivotally coupled to the gimbal for receiving the rotor blades. The rotor head also includes an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal.
    Type: Grant
    Filed: March 3, 2004
    Date of Patent: May 2, 2006
    Inventor: Franklin D. Carson
  • Patent number: 5304036
    Abstract: An autogyro aircraft has freewheeling rotor blades that provide lift. A separate pusher propeller provides forward thrust. The rotor system (20) has a collective arm (30) as a control for selectively setting and maintaining a tension force on a collective cable to regulate the rotor blade angle of attack or pitch angle between a no-lift attitude and a positive lift angle. The collective arm (30) sets a tension on collective cable against a coil spring biasing. The collective arm is connected to pivot or tilt a pitch change horn assembly and, in turn, connected rotor blades. The collective arm can be selectively set and maintained and released and reset both on the ground and in flight.
    Type: Grant
    Filed: December 12, 1990
    Date of Patent: April 19, 1994
    Assignee: Sego Tool, Incorporated
    Inventors: Henry J. Groen, David L. Groen
  • Patent number: 5190243
    Abstract: A device for the adjustment of the maneuver forces of movable members of an aircraft.
    Type: Grant
    Filed: June 29, 1992
    Date of Patent: March 2, 1993
    Assignee: Aerospatiale Societe Nationale Industrielle
    Inventor: Bruno Guimbal
  • Patent number: 4877375
    Abstract: A rotor system according to this invention includes a structurally flexible rotor shaft for transmitting rotor torque and other rotor loads to a rotor hub. The rotor hub is adapted to have rotor blades mounted thereon and is mounted by an elastomeric spherical bearing whose center is located at the rotor center. A flexible shaft made from fiber reinforced resin matrix material, connected to the rotor shaft at a connection located below the bearing center, extends vertically from that location through the bearing to a position located above the bearing center where it is connected to a connecting member fixed to the upper surface of the rotor hub.The flexible shaft is structurally stiff with respect to the mode in which it transmits rotor torque compared to the rotor torque stiffness of the other components.
    Type: Grant
    Filed: September 30, 1986
    Date of Patent: October 31, 1989
    Assignee: The Boeing Company
    Inventor: Rene A. Desjardins
  • Patent number: 4824326
    Abstract: An autogyro has rotor blades carried by a rotor head mounted on a support member (10) rotatable about a pitch axis (18) and independently rotatable about a roll axis (22) for control of the autogyro in pitch and roll respectively. The pitch and roll axes intersect one another in order to overcome the problem of rotation about one axis affecting the radius of rotation about the other axis. Means are provided to prevent rotation of the rotor head and support member about an axis orthogonal to both the pitch and roll axes.
    Type: Grant
    Filed: May 28, 1987
    Date of Patent: April 25, 1989
    Assignee: Property Associates Limited
    Inventor: James A. Watts
  • Patent number: 4759689
    Abstract: A two-bladed aircraft rotor is disclosed having blades mounted for freedom of blade motions, at least in the flapping sense and in the pitch-change sense, with the blades driven by flexible bellows.
    Type: Grant
    Filed: March 27, 1987
    Date of Patent: July 26, 1988
    Inventor: Stephan Roman
  • Patent number: 4755106
    Abstract: The invention provides a balance bar twin blade hub. A beam is formed of a tube made from a composite material of evolutive form whose section is cylindrical at its end on the blade side and progressively elliptical as far as its central connection part. It is connected to a support stirrup 2 conical stratified stops 4 forming balance bar bearings identical to the conical stratified stops forming the centrifugal force take up and angle of attack bearings providing the connection between the blade 16 and the beam.
    Type: Grant
    Filed: November 17, 1986
    Date of Patent: July 5, 1988
    Assignee: Aerospatiale Societe Nationale Industrielle
    Inventor: Rene L. Coffy
  • Patent number: 4737074
    Abstract: A one piece fan blade for a wind machine is sandwiched between a hub and a plate, the fan blade and the hub and is secured thereto by a teeter pin extending through the bore from opposed passageways in the hub. The shaft is centered in the bore of the hub to permit tilting of the hub about an axis coincident with the teeter pin to an angle commensurate with the spacing intermediate the shaft and the bore. Apparatus at the extremities of the teeter pin reduce wear on the teeter pin retaining plates and contribute to lubrication of the opposed journals.
    Type: Grant
    Filed: May 9, 1986
    Date of Patent: April 12, 1988
    Assignee: International Frost Protection Company
    Inventor: Dean A. Wells
  • Patent number: 4708591
    Abstract: A bladed aircraft rotor is disclosed having blades mounted by means of flexible devices providing freedom for blade motions, at least in the flapping sense and in the pitch-change sense, without employment of flapping or pitch bearings or pivots, the rotor also being provided with a central bearingless joint for transmitting thrust forces while providing freedom for angular movement of the rotor as a whole about a center point on the axis of rotation. A constant velocity torque-transmitting system is also provided.
    Type: Grant
    Filed: January 15, 1986
    Date of Patent: November 24, 1987
    Inventor: Stephan Roman
  • Patent number: 4695227
    Abstract: A universal joint for use in a pitch cone rotor system in a helicopter is comprised of crossed lift beams, one beam of which is coupled to the rotor hub and the other beam of which is coupled to the driven rotor shaft. The two crossed lift beams are coupled to each other through a cruciform case. The cruciform case in turn is coupled to each of the crossed lift beams by means of a plurality of flexures. The flexures and cruciform case are made of composite fiber materials and the flexures are soft enough to permit angular and translational deflections of the crossbeams with respect to each other thereby tending to smooth out and reduce sudden changes in rotor speed between the shaft and rotor system and thereby tending to make rotor speeds more uniform. The crossed lift beams are further coupled together at the center of their crossing by a flexible elastomeric tension link which conducts rotor loads between the two beams when the rotor develops negative lift loads on the ground and in flight.
    Type: Grant
    Filed: February 27, 1985
    Date of Patent: September 22, 1987
    Assignee: Hughes Helicopters Inc.
    Inventors: Robert E. Head, Samuel S. Yao
  • Patent number: 4595337
    Abstract: A one piece fan blade for a wind machine is sandwiched between a hub and a plate. A rotatable shaft penetrably engages a bore extending through the plate, the fan blade and the hub and is secured thereto by a teeter pin extending through the bore from opposed passageways in the hub. The shaft is centered radially inwardly in the bore of the hub between opposed journals extending radially inwardly into the bore from the opposed passageways to permit tilting of the hub about an axis coincident with the teeter pin to an angle commensurate with the spacing intermediate the shaft and the bore.
    Type: Grant
    Filed: December 20, 1984
    Date of Patent: June 17, 1986
    Inventor: Scott D. Crowe
  • Patent number: 4565340
    Abstract: A guidance system for small spinning projectiles which is mechanically simple, has low power requirements, uses relatively unsophisticated electronics, and is capable of withstanding large gas pressures and accelerations. The system uses a one-piece fin assembly which is de-spun so that its guidance fins maintain a constant attitude with respect to the ground. The guidance fins and their hub can be nutated simultaneously and independently in two orthogonal planes by pivoting and translating a single control rod. The hub cooperates with the projectile body to reduce its base drag and thereby extend its range.
    Type: Grant
    Filed: August 15, 1984
    Date of Patent: January 21, 1986
    Assignee: Ford Aerospace & Communications Corporation
    Inventor: William R. Bains
  • Patent number: 4449889
    Abstract: Disclosed is an inclined axis windmill. The windmill has a plurality of blades generally transverse to the upstanding rotor shaft. The blades have an airfoil cross-sectional shape and are oriented with a negative angle of attack, thereby allowing the leading edge of the airfoil to turn into the wind. The windmill preferably has a tilting assembly which tilts the rotor shaft and blades at an angle dependent upon the velocity of the wind. As the wind velocity increases the rotor shaft is automatically tilted into a more nearly vertical position by the control tail. This automatic tilting of the windmill provides automatic control of the rotor speed. The rotor blades are preferably pivotally connected to the rotor shaft.
    Type: Grant
    Filed: January 20, 1983
    Date of Patent: May 22, 1984
    Inventor: Ralph A. Belden
  • Patent number: 4439105
    Abstract: An offset-axis type wind generator uses a passive cyclic pitch-change rotor whose shaft axis is inclined downward and aft, with its sense of rotation selected so that the yaw component of the shaft torque at least partially of the shaft torque offsets that component of thrust which accompanies power extraction. A wind-alignment vane extends from a boom mounted on a furling hinge, equipped with mechanism to limit the vane's anti-furling moment to balance only the remainder of the moment of rotor thrust. Hence, disengagement of power extraction does not cause the rotor to overspeed, and the machine may idle even in gale-force winds, furled to nearly 90.degree..
    Type: Grant
    Filed: October 2, 1981
    Date of Patent: March 27, 1984
    Assignee: Jerome A. Gross
    Inventor: Kurt H. Hohenemser
  • Patent number: 4323332
    Abstract: A hingeless helicopter rotor including an aerodynamically shaped hub having a flexible diaphragm as its bottom wall, which diaphragm is connected to the rotor drive shaft and is elastically deformable in response to blade loading to tilt in any direction with respect to the axis of rotation, and further having at least three equally spaced helicopter blades projecting from and supported from within the hub for rotation therewith and for flexing with respect thereto in response to blade loading so that the flexible hub and the blades coact to produce a low equivalent offset rotor and minimized Coriolis effect.
    Type: Grant
    Filed: December 21, 1979
    Date of Patent: April 6, 1982
    Assignee: United Technologies Corporation
    Inventor: Evan A. Fradenburgh
  • Patent number: 4201514
    Abstract: A wind turbine having a wing rotor with two rotor blades supported on a hub; to accommodate different wind velocities nearer and further from the ground and to accommodate the components of wind force transverse to the rotor blade plane of rotation, the pitch of the blade that is then higher above the ground is altered with respect to the pitch of the blade that is nearer to the ground; this can be done by appropriate swivel mounting of the rotor hub for allowing its reorientation to change the effective pitch of the blades as they rotate high and low; or it can be done by a blade swiveling means sensitive to wind conditions.
    Type: Grant
    Filed: December 5, 1977
    Date of Patent: May 6, 1980
    Inventor: Ulrich Huetter
  • Patent number: 4148594
    Abstract: A two-bladed propeller fan for wind machines, having a teetering hub for mounting in spaced relationship on a driving shaft, a pair of tangs 180.degree.
    Type: Grant
    Filed: June 10, 1977
    Date of Patent: April 10, 1979
    Assignee: SSP Agricultural Equipment, Inc.
    Inventor: Thomas P. Stafford
  • Patent number: 4092084
    Abstract: A two-bladed semi-rigid type tilt hub teetering rotor for an autogiro. The otor has a spin-up condition in which it has an relatively small blade angle, and an in-flight condition in which the blade angle is relatively high. The rotor is adapted to alter automatically from its spin-up condition to its in-flight condition upon tilting of the hub at take-off.
    Type: Grant
    Filed: July 22, 1976
    Date of Patent: May 30, 1978
    Assignee: The South African Inventions Development Corporation of Scientia
    Inventor: Austin Barltrop