Lifting Rotor Having Lift Direction Varying Means Patents (Class 244/17.25)
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Patent number: 8973863Abstract: The rotorcraft may include an airframe, at least one engine connected to the airframe, and a rotor connected to the airframe. The rotor may include a hub, a rotor blade, and a feathering spindle connected to the hub. The rotor blade may have a root and a tip and form a conduit extending in the radial 5 direction from the root to the tip. The root may comprise a wall forming a hollow circular cylinder. The hollow circular cylinder may form a portion of the conduit. A plurality of bolts may be distributed circumferential within the wall of the root. The plurality of bolts may extend in the radial direction from the wall of the root to secure the rotor blade to the feathering 10 spindle.Type: GrantFiled: September 7, 2011Date of Patent: March 10, 2015Assignee: Groen Brothers Aviation, Inc.Inventor: Jacob Johannes van der Westhuizen
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Patent number: 8973864Abstract: According to one embodiment, a radial fluid device includes a cylinder block having a plurality of radially extending cylinders, a plurality of pistons, and a cam disposed about the plurality of radially extending cylinders. A first linear control is coupled to the cam and operable to reposition the cam along a first axis. A second linear control is coupled to the cam and operable to reposition the cam along a second axis. A third linear control is coupled to the cam and operable to resist movement of the cam along a third axis.Type: GrantFiled: August 2, 2012Date of Patent: March 10, 2015Assignee: Bell Helicopter Textron Inc.Inventor: Carlos A. Fenny
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Publication number: 20150060597Abstract: According to one embodiment, a bearing is situated between a pitch link and a swashplate or a hub. The bearing comprises an outer housing having a first opening therethrough, an intermediate housing adjacent the housing inside the first opening and having a second opening therethrough, and an inner housing adjacent the intermediate housing inside the second opening and having a third opening therethrough. The inner housing comprising a first inner surface and a second inner surface defining the third opening. A first member is adjacent the first inner surface inside the third opening having a fourth opening therethrough. A second member is adjacent the second inner surface inside the third opening having a fifth opening therethrough coaxial with the fourth opening.Type: ApplicationFiled: November 5, 2014Publication date: March 5, 2015Applicant: Bell Helicopter Textron Inc.Inventors: Drew Sutton, Frank B. Stamps
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Patent number: 8931729Abstract: A system for increasing the thrust and power capabilities of a side-by-side vertical takeoff and landing vehicle to optimize the coaxial rotor performance. The system includes a first coaxial rotor spaced from an aircraft body and a second coaxial rotor spaced from the aircraft body and opposite the first coaxial rotor. The first coaxial rotor has a first top propeller aligned with a first bottom propeller along a first rotational axis. The second coaxial rotor having a second top propeller aligned with a second bottom propeller along a second rotational axis. A gyroscopic moment to maintain pitch stability is controlled by modulating the first and second top propellers, which have a different angular speed or different torque from the first and second bottom propellers, and tilting the first and second coaxial rotors towards the central axis with a common tilt angle and a common tilt rate.Type: GrantFiled: October 31, 2011Date of Patent: January 13, 2015Assignee: King Abdullah II Design and Development BureauInventors: Hamzeh Mahmoud Abde Qader Alzu'bi, Imad Abd Allateef, Yahya Zweiri, Basim Alkhateeb, Yahya Taha Ayed Al-Majali
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Patent number: 8911209Abstract: A helicopter rotor include a blade, a rotor hub which supports the blade, and a lead-lag angle mechanism configured to change the lead-lag angle of the blade in synchronization with the rotation of the rotor hub. The lead-lag angle mechanism changes the lead-lag angle of the blade such that a circumferential speed of a blade tip of the blade (3) is slower on a forward side and faster on a backward side. The result is a helicopter, a helicopter rotor, and a control method of a helicopter that enable higher speed flight.Type: GrantFiled: January 9, 2009Date of Patent: December 16, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventor: Masahiro Nakao
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Patent number: 8876036Abstract: A reconfigurable rotor blade system includes an internal mass that is configured to translate in order to produce a spanwise torsional twist of the rotor blade. An actuator is configured to selectively translate the mass so as to relocate a center of mass of the rotor blade. The torsional twist is selectively produced during operation of the rotorcraft.Type: GrantFiled: July 28, 2011Date of Patent: November 4, 2014Assignee: Textron Innovations Inc.Inventors: James M. McCollough, Mark Wasikowski
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Patent number: 8857757Abstract: According to one embodiment, a rotorcraft pitch link includes a housing and a piston assembly. The housing comprises a first chamber and a second chamber. A first housing opening allows a first fluid to flow into the first chamber, and a second housing allows a second fluid to flow into the second chamber. The piston assembly is at least partially disposed within the housing and comprises a piston head and a piston rod coupled to the piston head. The piston head separates the first chamber from the second chamber.Type: GrantFiled: August 2, 2012Date of Patent: October 14, 2014Assignee: Bell Helicopter Textron Inc.Inventor: Carlos A. Fenny
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Publication number: 20140299709Abstract: A rotor assembly includes a rotor hub rotatable about a central axis including a plurality of rotor hub arms and blade yokes, each blade yoke including yoke arms located at opposing lateral sides of a corresponding one of the rotor hub arms to which the rotor hub arm is operably connected. The rotor assembly further includes blade retention bearings, each blade retention bearing being a single-element bearing disposed at a corresponding one of the rotor hub arms and which is supportive of a corresponding one of the blade yokes. Rotor blades are secured to corresponding ones of the blade yokes.Type: ApplicationFiled: April 3, 2013Publication date: October 9, 2014Applicant: Sikorsky Aircraft CorporationInventor: Sikorsky Aircraft Corporation
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Publication number: 20140299708Abstract: Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.Type: ApplicationFiled: May 23, 2012Publication date: October 9, 2014Inventors: John Green, Philip Geoghegan, Michael Alexander Snook
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Patent number: 8739679Abstract: Apparatus and methods for eliminating back drive in a push pull type control system, are provided. An exemplary apparatus includes a control rod including a pair of spaced apart piston displacement members each configured to carry a check valve. The apparatus also includes a pair of opposite-face check valves each configured to seal against respective opposing face of a piston head to form a hydraulic lock, preventing back drive in the control system.Type: GrantFiled: June 25, 2012Date of Patent: June 3, 2014Assignee: Carter Aviation Technologies, LLCInventors: Jay W. Carter, Jr., M. Keith Robinson, Jeffrey R. Lewis
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Publication number: 20140124615Abstract: According to one embodiment, a rotor system includes an anti-rotation sleeve featuring an outer recess portion and a tilt sleeve positioned about the anti-rotation sleeve and having an opening therethrough. A first swashplate ring is positioned about the tilt sleeve and features an inner recess portion. An anti-rotation mechanism is disposed through the opening and at least partially in the outer recess portion and the inner recess portion. The anti-rotation mechanism is operable to prevent the first swashplate ring from rotating about the anti-rotation sleeve. A second swashplate ring is positioned about the first swashplate ring and rotatable about the anti-rotation sleeve.Type: ApplicationFiled: November 8, 2012Publication date: May 8, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: George M. Thompson, Frank B. Stamps, Glenn A. Shimek
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Patent number: 8708273Abstract: A vertical takeoff and landing aircraft having a fuselage with, preferably, three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight.Type: GrantFiled: June 24, 2011Date of Patent: April 29, 2014Assignee: Oliver Vtol, LLCInventor: Richard David Oliver
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Patent number: 8668162Abstract: A method for equalizing rolling moments at high advance ratios is disclosed including impelling an aircraft in a forward direction at an airspeed by means of a thrust source and rotating a rotor of the aircraft at an angular velocity with respect to the airspeed effective to cause a positive total lift on each blade due to air flow over the blades in the retreating direction when the blade is moving in the retreating direction. The rotor includes an even number of blades placed at equal angular intervals around the rotor hub. One or both of cyclic pitch and rotor angle of attack are adjusted such that a rolling moment of the retreating blade due to reverse air flow is between 0.3 and 0.7 times a rolling moment on the advancing blade due to lift.Type: GrantFiled: September 7, 2011Date of Patent: March 11, 2014Assignee: Groen Brothers Aviation, Inc.Inventor: Walter Gerd Oskar Sonneborn
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Publication number: 20140034779Abstract: According to one embodiment, a radial fluid device includes a cylinder block having a plurality of radially extending cylinders, a plurality of pistons, and a cam disposed about the plurality of radially extending cylinders. A first linear control is coupled to the cam and operable to reposition the cam along a first axis. A second linear control is coupled to the cam and operable to reposition the cam along a second axis. A third linear control is coupled to the cam and operable to resist movement of the cam along a third axis.Type: ApplicationFiled: August 2, 2012Publication date: February 6, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventor: Carlos A. Fenny
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Publication number: 20140034777Abstract: According to one embodiment, a rotorcraft pitch link includes a housing and a piston assembly. The housing comprises a first chamber and a second chamber. A first housing opening allows a first fluid to flow into the first chamber, and a second housing allows a second fluid to flow into the second chamber. The piston assembly is at least partially disposed within the housing and comprises a piston head and a piston rod coupled to the piston head. The piston head separates the first chamber from the second chamber.Type: ApplicationFiled: August 2, 2012Publication date: February 6, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventor: Carlos A. Fenny
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Publication number: 20140034778Abstract: According to one embodiment, a rotary blade actuator includes a housing, a vane disposed within the housing, a shaft disposed at least partially within the housing and coupled to the vane. The vane comprises a first vane surface disposed within a first chamber between a first fluid opening and a second fluid opening and a second vane surface disposed within a second chamber between a third fluid opening and a fourth fluid opening. The shaft is operable to rotate in response to movements of the vane.Type: ApplicationFiled: August 2, 2012Publication date: February 6, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventor: Carlos A. Fenny
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Patent number: 8636245Abstract: An aircraft having at least one in-flight attitude control system, in turn having at least one actuator; and a hydraulic circuit connected to the actuator and having at least one pump designed to deliver a first flow when the pressure of the hydraulic circuit is above a presettable threshold value. The pump is designed to deliver a second flow greater than the first flow, and the aircraft has a sensor for detecting a quantity associated with the pressure of the hydraulic circuit; and a programmable central control unit, which controls the pump to deliver the second flow when the quantity detected by the sensor corresponds to a pressure of the hydraulic circuit below the threshold value.Type: GrantFiled: December 29, 2010Date of Patent: January 28, 2014Assignee: Agusta S.p.A.Inventor: Roberto Vanni
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Patent number: 8615980Abstract: A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system.Type: GrantFiled: October 11, 2011Date of Patent: December 31, 2013Assignee: United Technologies CorporationInventors: Rajendra K. Agrawal, Steven J. Sirica, William F. Schneider
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Publication number: 20130341458Abstract: According to one embodiment, a bearing is situated between a pitch link and a swashplate or a hub. The bearing comprises an outer housing having a first opening therethrough, an elastomeric bearing adjacent the housing inside the first opening and having a second opening therethrough, and an inner housing adjacent the elastomeric bearing inside the second opening and having a third opening therethrough. The inner housing comprising a first inner surface and a second inner surface defining the third opening. A first member is adjacent the first inner surface inside the third opening having a fourth opening therethrough. A second member is adjacent the second inner surface inside the third opening having a fifth opening therethrough coaxial with the fourth opening.Type: ApplicationFiled: June 26, 2012Publication date: December 26, 2013Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Drew Sutton, Frank B. Stamps
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Patent number: 8590833Abstract: An aircraft rotor constant-velocity drive system having a differential mechanism that includes a drive disk configured to be integral in rotation with a mast, an upper member at least partially located above the drive disk, a lower member at least partially located below the drive disk, and at least one link connecting the upper member and the lower member to the drive disk such that the drive disk drives the upper member and the lower member in rotation with the drive disk and that the upper member and the lower member are allowed to rotate differently with respect to the drive disk. The link having opposing end joints and a central joint that pivotally engages the drive disk. The system also having a gimbal device configured to drive a rotor hub and to allow gimbaling of the rotor hub with respect to a mast.Type: GrantFiled: November 14, 2012Date of Patent: November 26, 2013Assignee: Textron Innovations Inc.Inventors: Richard Rauber, Frank B. Stamps, James Lee Braswell, Jr.
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Patent number: 8584983Abstract: A magnetic de-rotation system includes an inner ring which supports an eddy current ring and at least one inner ring magnet and an outer ring which supports at least one outer ring magnet, attraction between the at least one inner ring magnet and the at least one outer ring magnet produces a stable rotational position for a fairing.Type: GrantFiled: December 3, 2007Date of Patent: November 19, 2013Assignee: Sikorsky Aircraft CorporationInventors: Jayant Sirohi, Timothy Fred Lauder
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Patent number: 8565941Abstract: In order to suppress induction of precession when the rotor (24, 26) of a helicopter is tilted relative to a fuselage (31), the tilt trajectory is supplemented by transverse components. The helicopter is of the type with a bendable, actuated joint (34) between the rotor and a fuselage. A controller (2) receives an input signal (4) from a steering device (1) and transforms this input signal in an output signal (7) for an actuating system (3) for movement in the joint. The controller calculates on the basis of the input signal an estimation for further input signals, and adds a transverse component to the input trajectory before sending the output trajectory (11).Type: GrantFiled: May 5, 2010Date of Patent: October 22, 2013Assignee: HeliScandia ApSInventor: Gert Lading
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Publication number: 20130240663Abstract: A swash leveling tool for radio controlled (RC) helicopters can fit onto the main shaft under the swash plate to provide a level reference plane. Unlike conventional swash leveling tools that require removal of the head, the swash leveling tool of the present invention provides a level reference plane for the swash without having to take the time to disassemble portions of the helicopter.Type: ApplicationFiled: March 15, 2013Publication date: September 19, 2013Inventor: Richard Lohr
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Patent number: 8523103Abstract: A rotor blade assembly for providing vertical lift to an aircraft, having a rotor head and a plurality of blades, with each blade attached to a mechanism such as a cam surface, whereby movement of the mechanism causes the radial distance between the distal tip of the attached blade and the center of the rotor head to alter, decreasing or increasing the length of the lifting surface. The blades are moved from a fully extended position providing maximum lift, to a retracted position in which the blades are removed from the airstream. The pitch of the blades may be controlled by a pitch controller to achieve full helicopter responsiveness. A plurality of bladeletts may be positioned near the outer periphery of the rotor head. When they are moved into the airstream, passing air impacts the bladeletts exerting a pressure, causing rotational movement of the rotor blade assembly.Type: GrantFiled: December 17, 2008Date of Patent: September 3, 2013Inventor: Allen J. Gerbino
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Publication number: 20130206900Abstract: According to one embodiment, a control assembly includes a post, a grip, and a hand rest. The post has a top, a bottom, and a body joining the top to the bottom. The grip is positioned at least partially above the post and is movable along at least one arc. The hand rest is coupled to the top and comprises an upper surface having a profile corresponding to the at least one arc.Type: ApplicationFiled: January 8, 2013Publication date: August 15, 2013Applicant: BELL HELICOPTER TEXTRON INC.Inventor: Bell Helicopter Texton Inc.
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Patent number: 8496200Abstract: The present application relates to VTOL vehicles with multi-function capabilities and, specifically to ducted fan arrangements that facilitate the control of forces and flows of air to control movement of the vehicle in six degrees of freedom in both primary and secondary modes of operation. Also disclosed are pitch control mechanisms for the lift propellers of VTOL vehicles: drive and transmission arrangements; a specially configured exhaust duct for directing exhaust gases from such vehicles along an upper surface of the vehicle; and shock absorbing components for the landing gear of such vehicles.Type: GrantFiled: April 30, 2008Date of Patent: July 30, 2013Assignee: Urban Aeronautics Ltd.Inventor: Raphael Yoeli
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Publication number: 20130168491Abstract: A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a plurality of blades defining ducts along the length thereof and vents in fluid communication with the ducts. Flow from through the vents may be controlled by valves with piezoelectric actuators. The valves may be adjusted to achieve a lift profile suited for an operational mode such as vertical, autorotative, or unloaded flight. The lift profile may vary along the length of the blade and may vary cyclically with rotation of the blade. The lift profile may be chosen to approximate a figure of merit for the rotor suitable for a given operational mode.Type: ApplicationFiled: July 9, 2012Publication date: July 4, 2013Applicant: GROEN BROTHERS AVIATION, INCInventor: Jacob Johannes van der Westhuizen
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Publication number: 20130168492Abstract: According to one embodiment, a pitch link includes a first link, a second link coupled to a first end of the first link, a third link coupled to a second end of the first link opposite the first end, and a first bearing housing having a first bearing and a second bearing housing having a second bearing. The first bearing housing is removably coupled to the second link. The second link separates the first bearing housing from the first link. The second bearing housing is removably coupled to the third link. The third link separates the second bearing housing from the first link.Type: ApplicationFiled: November 5, 2012Publication date: July 4, 2013Applicant: BELL HELICOPTER TEXTRON INC.Inventor: Bell Helicopter Textron Inc.
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Patent number: 8469307Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.Type: GrantFiled: October 11, 2011Date of Patent: June 25, 2013Inventors: Paul E Arlton, David J Arlton
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Patent number: 8444081Abstract: A flying apparatus having a frame configured to couple to a high voltage tether system, and at least one motor module mounted to the frame, the module including a holding structure attached to the frame, a rotating structure, including a rotor shaft, configured to rotate relative to the holding structure, a rotor attached to the rotor shaft and a plurality of motors attached to the holding structure, each including a drive shaft configured to engage with the rotor shaft, wherein the motors are configured to receive electrical energy from the tether system and drive the drive shafts to create a torque on the rotor shaft to thereby rotate the rotor and create lift to fly the apparatus from the ground to a desired position aloft while remaining coupled to the tether system.Type: GrantFiled: October 19, 2010Date of Patent: May 21, 2013Assignee: JST, LLCInventor: Albert J. Grenier
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Publication number: 20130119187Abstract: The present invention relates to a device (10) for varying blade pitch of a rotary wing aircraft (50) having a main rotor (11) with a plurality of blades (12), each blade (12) including at least one main flap (13) fastened to the trailing edge of the blade (12). The angle of inclination of each flap (13) is controlled via a swashplate (20). The device (10) makes provision for electric actuators controlled by a flight control system (54) to be mounted in a stationary frame of reference for the purpose of moving and varying the angle of inclination of the non-rotary plate of the swashplate (20). The electric actuators provide primary flight control and also multi-cyclic control for the purpose of attenuating noise and vibration as generated in particular by the blades (12) and the rotor (11).Type: ApplicationFiled: November 8, 2012Publication date: May 16, 2013Applicant: EUROCOPTERInventor: Eurocopter
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Patent number: 8408488Abstract: One embodiment of a Vertical Take-off and Landing (VToL) air-vehicle (FIG. 1.) having a horizontal rotor, a. providing lift and propulsion, and communicating at or near its centre to structural elements, or fuselage, b. Upon or within the fuselage structure is attached a platform, to which a payload, or occupant or pilot, d. is secured in such a manner as to permit a movement, or range-of-motion, of the payload, as a means of weight-shifting, or mass-balancing, of the vehicle for stability and control in flight. At least two planar elements, or descent-vanes, c.i & c.ii are connected to a structural element of the fuselage at a location which provides vertical and horizontal separation between the rotor and the descent-vanes, thus creating a tandem, biplane arrangement of two aerodynamically active elements which are aerodynamically balanced to provide stability and controllability in hovering flight, in forward flight, and in un-powered gliding and vertical descents.Type: GrantFiled: January 4, 2010Date of Patent: April 2, 2013Inventor: Glenn Leaver
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Patent number: 8342441Abstract: A VTOL vehicle includes a forward rotor, an aft rotor and a fuselage, the forward and aft rotor lying in a longitudinal axis of the vehicle, with the fuselage located axially between the forward and aft rotors. The vehicle has an in-flight configuration wherein the forward rotor is tilted downwardly at a negative tilt angle relative to the fuselage and the aft rotor is tilted upwardly at a positive tilt angle relative to the fuselage.Type: GrantFiled: August 28, 2009Date of Patent: January 1, 2013Assignee: Urban Aeronautics Ltd.Inventor: Raphael Yoeli
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Patent number: 8336815Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed.Type: GrantFiled: May 19, 2006Date of Patent: December 25, 2012Assignee: Bell Helicopter Textron Inc.Inventors: Richard Rauber, Frank B. Stamps, James Lee Braswell, Jr.
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Publication number: 20120312917Abstract: A vertical take-off aircraft comprising a main propeller 1 at the top of the aircraft which consists of an assembly of blades 2, 3, and a rotor 4. A drive assembly 5 rotates the propeller. The drive assembly comprises a power plant 5a. The drive assembly is connected to the main body 6 of the aircraft by a tilt enabling joint 7. The tilt enabling joint is connected to the main body by a telescopic tube assembly comprising tubes 12 and 13. To counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the blades 2, 3, an additional power plant 15 is attached to the drive assembly. Tilting the drive assembly causes tilting of the additional power plant.Type: ApplicationFiled: June 4, 2012Publication date: December 13, 2012Inventor: Tom Kusic
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Patent number: 8308522Abstract: A flying toy comprises a first wing and a second wing attached to and extending from opposite sides of a fuselage. There is a first propulsion unit, having a first motor and a first propeller system rotated by the first motor, mounted with the first wing; and a second propulsion unit, having a second motor and a second propeller system rotated by the second motor, mounted with the second wing. Each propulsion system has main blades and auxiliary blades which interact with each other. Each of two wings can be angled relative to horizontal independently. The toy can operate as a plane or helicopter.Type: GrantFiled: January 29, 2010Date of Patent: November 13, 2012Assignee: Silverlit LimitedInventors: Alexander Jozef Magdalena Van de Rostyne, Kwok Leung Wong
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Patent number: 8282035Abstract: The present invention relates to a mechanical device (1) suitable for combining first and second pitch control orders for controlling the blade pitch of at least one rotary assembly, the device comprising a carrier structure (10) suitable for being fastened to a support (5) by at least one main fastener pin (13) about which said carrier structure (10) is capable of performing a pivoting movement. In addition, the device includes at least one connection lever (20, 30) per rotary assembly, and at least one secondary fastener pin (25, 35) per connection lever (20, 30), said secondary fastener pin (25, 35) being secured firstly to said carrier structure (10) and being fastened secondly by rotary means (26, 36) to the connection lever (20, 30).Type: GrantFiled: June 2, 2010Date of Patent: October 9, 2012Assignee: EurocopterInventors: Bernard Gemmati, Romuald Biest, Guillaume Franchini
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Publication number: 20120199692Abstract: A rotorcraft is disclosed. The rotorcraft may include an airframe comprising a mast defining an interior cavity, at least one compressor connected to the airframe, and a rotor. The rotor may include a hub and a rotor blade. The hub may connect to the mast to rotate with respect thereto. The hub may also define an interior cavity. The rotor blade may form a radial conduit extending radially therewithin. A flow of compressed air generated by the at least one compressor may pass from the at least one compressor, through the interior cavity defined by the mast, through the interior cavity defined by the hub, and into the radial conduit. A swashplate assembly controlling pitch of the rotor blade may be located exterior to the hub and mast. Accordingly, the swashplate assembly may not be heated by the flow of compressed air.Type: ApplicationFiled: March 29, 2012Publication date: August 9, 2012Applicant: GROEN BROTHERS AVIATION, INCInventor: Jacob Johannes van der Westhuizen
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Patent number: 8235324Abstract: A helicopter uses multiple redundant harmonic drive motors on the rotor head to actuate the angle of attack of rotor blades at the rotor blade roots, providing collective control that, in combination with a system for providing cyclic control on the rotor blades, eliminates the need for a swashplate, thereby advantageously reducing the weight and maintenance cost of the helicopter, increasing its reliability, and reducing its vulnerability to ballistic attack.Type: GrantFiled: March 2, 2010Date of Patent: August 7, 2012Assignee: Orbital Research Inc.Inventors: Matthew C. Birch, Zak Sowle
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Patent number: 8226026Abstract: A single place helicopter comprising a lower airframe and an upper airframe, having a rotor shaft attached thereto, rotor blades, and a hub on said rotor shaft with means to change blade pitch for vertical flight. The upper airframe comprising a rotor system, engine, tail boom and tail rotor tilt as one unit with the pilot forward, rearward and in a lateral attitude for directional flight control by means of a hinged gimbal joint or block fastened between the two airframes. By allowing the pilot to move with the rotor system this configuration combines physical human interface and mechanical airframe manipulation to change the plane of rotation controlling the thrust vector and flight direction of the aircraft.Type: GrantFiled: August 6, 2009Date of Patent: July 24, 2012Inventor: David Allen Hickman
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Publication number: 20120175461Abstract: A fairing system may be assembled about a rotor of a rotorcraft to present an aerodynamically quasi-static region that rotates in an airstream, as well as certain extensions that sweep through the airstream as the rotor hub passes through the air. A spherical interface between the extensions on the rotor hub fairing and the base or root portion of each blade fairing provides three degrees of freedom permitting lead-lag, flapping, and blade pitch pivoting in the blade, while still maintaining an aerodynamic profile that will minimize drag.Type: ApplicationFiled: March 22, 2012Publication date: July 12, 2012Applicant: GROEN BROTHERS AVIATION, INCInventors: Jacob J. van der Westhuizen, Robert Owen White
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Patent number: 8201772Abstract: A method is disclosed for suppressing an external acoustic signature of an aircraft having at least one pair of non-intermeshing multiple-blade rotors. During operation of the aircraft, the at least one pair of rotors are rotated in an asymmetrically indexed manner that causes the blades of one of each pair of rotors to be consistently out of phase from the blades of the other of each pair of rotors. The selected amount in degrees of asymmetrical indexing is equal to the desired phasing in degrees divided by a number of blades of one of the rotors.Type: GrantFiled: April 11, 2008Date of Patent: June 19, 2012Assignee: Textron Innovations Inc.Inventors: Joseph W. Wendelsdorf, Victor L. Berry
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Patent number: 8196857Abstract: The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1) suitable for causing a change in flight attitude. Said bellcrank (40) includes first and second sliders (50, 52). Said first slider (50) is connected to a movable portion (57, 61) of a setpoint flight-attitude-changing linkage (24) that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (27, 25A, 28A) to be adjusted, which gain is proportional to the position of said movable portion (57, 61).Type: GrantFiled: June 1, 2010Date of Patent: June 12, 2012Assignee: EurocopterInventors: Bernard Gemmati, Romuald Biest, Carine Mirman
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Patent number: 8196856Abstract: A method is disclosed for suppressing vibration in an aircraft having at least one pair of multiple-blade rotors. The first step of the method is to install in the aircraft at least one pair of vibration suppression devices to form a system, the devices of each system being mounted on opposing sides of the aircraft. Then, during operation of the aircraft, the next step is to rotate the at least one pair of rotors in a manner that causes the blades one of each pair of rotors to be out of phase from the other of each pair of rotors. The final step is to use the system to suppress vibrations caused by the out-of-phase rotation of the rotors.Type: GrantFiled: April 11, 2008Date of Patent: June 12, 2012Assignee: Textron Innovations Inc.Inventors: James A. Wilson, Charles L. Barkley, Jr., Gerald Smith, Jr., Jeffrey B. Cloud
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Patent number: 8186615Abstract: A remote controlled helicopter of a single rotor type to be used indoors, having a flying operation that can be stabilized and operability that can be improved. The helicopter includes a center hub that supports a rotor head to a mainmast, and is divided into an upper center hub and a lower center hub. The upper and the lower center hubs are fixed around the shaft of the mainmast with a predetermined angle. A phase angle of a main rotor as an output with respect to an operation input from a swash plate becomes an acute angle, and the main rotor and a stabilizer are mounted to rotate with a phase difference of the acute angle.Type: GrantFiled: July 2, 2007Date of Patent: May 29, 2012Assignee: Hirobo Co., LtdInventors: Takakazu Uebori, Kimio Nakamura
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Patent number: 8177600Abstract: A single rotor model helicopter is provided, comprising a spindle, a rotor clamp disposed on the spindle, a pair of rotor blades disposed on the rotor clamp, and a pair of hybrid control rocker arms. The helicopter further includes an operating system and a balancing system. The pair of hybrid control rocker arms are disposed on both sides of the rotor clamp respectively and rotatably connected to a pitch control rocker arm through each axial hole located on a center of each hybrid control rocker arm, so as to control attack angles of the rotor blades. Each hybrid control rocker arm has two control points. A first pair of control points diagonally opposite each other in the pair of hybrid control rocker arms are controlled by a cyclic torque transmitted from the operating system, and a second pair of control points diagonally opposite each other are controlled by the balancing system.Type: GrantFiled: March 25, 2010Date of Patent: May 15, 2012Assignee: Shanghai Nine Eagles Electronic Technology Co., Ltd.Inventors: Guochuan Huang, Yuchen Wu, Yizhen Yu, Huanzhong Ding
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Patent number: 8167234Abstract: A micro air vehicle (MAV) comprises features that emulate insect-like topology and flight, including a dangling three part body (100a, 100b, 100c), wing-like dual side rotors (107, 107a) positioned to either side on rotor arms (103) providing tilt and teeter motions to vector thrust and allow crawling along improved surfaces, and elevators (101) that approximate the center of gravity and center of pressure control employed by insects via the inertial reaction and aerodynamic influence of a repositionable abdomen. Control, sensing, surveillance, and payload elements (114), (401), (402), (403), (404), (405), and (407) enable transmission of surveillance and engagement of an emerging target. Left and right perch hangers and grapples (112, 112a) allow perching on various structures, and energy storage (504) and (505) combined with power line (500) and solar (502) energy scavenging circuitry allow extended loiter and mission duration by replenishing onboard energy supplies.Type: GrantFiled: March 21, 2010Date of Patent: May 1, 2012Inventor: Michael Moore
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Patent number: 8152465Abstract: A rotor blade comprises an inner rotor blade root area, a rotor blade main area disposed adjacent to the inner rotor blade root area along a length of the rotor blade and having an aerodynamically effective rotor blade profile, the profile including a nose area and a rear edge area, and a rotor blade tip disposed adjacent to the rotor blade main area along the length of the rotor blade. The rotor blade tip is configured to be deformable relative to the rotor blade main area and is operatively connected to a first actuator device. The first actuator device is configured to initiate a vertical movement of the rotor blade tip upwards or downwards relative to the lift direction. The vertical movement starts from a neutral position relative to the rotor blade main area.Type: GrantFiled: December 19, 2008Date of Patent: April 10, 2012Assignee: Eurocopter Deutschland GmbHInventors: Peter Jaenker, Valentin Kloeppel
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Publication number: 20120061526Abstract: A rotor system for a rotorcraft, the rotor system is a rotor hub having six rotor blades attached to a rotor mast via a rotor yoke assembly. Each rotor blade is angularly spaced in 30° and 90° alternating angular increment about a mast axis of rotation. Such rotor blades spacing reduces the vibration that is translated into the rotorcraft through the rotor mast.Type: ApplicationFiled: May 22, 2009Publication date: March 15, 2012Applicant: Bell Helicopter Textron Inc.Inventor: John E. Brunken, JR.
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Publication number: 20120056031Abstract: In order to suppress induction of precession when the rotor (24, 26) of a helicopter is tilted relative to a fuselage (31), the tilt trajectory is supplemented by transverse components. The helicopter is of the type with a bendable, actuated joint (34) between the rotor and a fuselage. A controller (2) receives an input signal (4) from a steering device (1) and transforms this input signal in an output signal (7) for an actuating system (3) for movement in the joint. The controller calculates on the basis of the input signal an estimation for further input signals, and adds a transverse component to the input trajectory before sending the output trajectory (11).Type: ApplicationFiled: May 5, 2010Publication date: March 8, 2012Applicant: HeliScandia ApSInventor: Gert Lading