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公开(公告)号：US11091246B2
公开(公告)日：2021-08-17
申请号：US16236247
申请日：2018-12-28
Applicant: Amazon Technologies, Inc.
Inventor： Dominic Timothy Shiosaki , Ricky Dean Welsh
Abstract: Aerial vehicles may include propulsion units having motors with drive shafts that may be aligned at a variety of orientations, propellers with variable pitch blades, and common operators for aligning the drive shafts at one or more orientations and for varying the pitch angles of the blades. The common operators may include plate elements to which a propeller hub is rotatably joined, and which may be supported by one or more linear actuators that may extend or retract to vary both the orientations of the drive shafts and the pitch angles of the blades. Operating the motors and propellers at varying speeds, gimbal angles or pitch angles enables the motors to generate forces in any number of directions and at any magnitudes. Attributes of the propulsion units may be selected in order to shape or control the noise generated thereby.
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公开(公告)号：US20210114715A1
公开(公告)日：2021-04-22
申请号：US16655400
申请日：2019-10-17
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas CRAVENER , Andrew MARESH , Chyausong TZENG
Abstract: An exemplary length adjustable link includes a tube having an internal bore and internal surface, a first rod end having a first shaft disposed in a first end of the internal bore, a second rod end having a second shaft disposed in a second end of the internal bore, and a member threadably connecting the first rod end to the second rod end.
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公开(公告)号：US20210107624A1
公开(公告)日：2021-04-15
申请号：US16599483
申请日：2019-10-11
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas CRAVENER , Christopher Edward FOSKEY , Andrew MARESH
IPC: B64C11/28 , B64C29/00 , B64C27/80 , B64C27/605 , B64C27/64 , B64C27/59 , B64C11/32 , B64C27/57 , B64C11/38
Abstract: An exemplary spring-loaded link for an aircraft including a spring interposed between a first and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.
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公开(公告)号：US20200324877A1
公开(公告)日：2020-10-15
申请号：US16378698
申请日：2019-04-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Jasraj CHAHAL , Carmine LISIO , Darragh MCGRATH , Michael YOUSSEF , Giancarlo ZINGARO
Abstract: Methods and systems for feathering a propeller are described herein. A solenoid is configured to cause a propeller to feather when the solenoid is energized. An electronic controller is connected to the solenoid through a first electrical connection for energizing the solenoid to feather the propeller. A secondary mechanism is connected to the solenoid through a second electrical connection for energizing the solenoid to feather the propeller. The second electrical connection is independent from the first electrical connection.
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公开(公告)号：US10737765B2
公开(公告)日：2020-08-11
申请号：US15972461
申请日：2018-05-07
Applicant: Textron Innovations Inc.
Inventor： Paul K. Oldroyd , John Richard McCullough
Abstract: An aircraft has an airframe with a distributed thrust array attached thereto that includes a plurality of propulsion assemblies each of which is independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto and operable to tilt about a single axis. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector with a magnitude in the longitudinal direction. Actuation of each gimbal is operable to tilt the respective propulsion system relative to the airframe in the longitudinal direction to change the rotational plane of the respective rotor assembly relative to the airframe, thereby controlling the magnitude of the respective thrust vector in the longitudinal direction.
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Patent Agency Ranking
公开(公告)号：US20200024981A1
公开(公告)日：2020-01-23
申请号：US16188373
申请日：2018-11-13
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Darek Tomasz Zatorski , Brandon Wayne Miller
IPC: F01D7/00 , B64C11/32 , F02C7/32 , F01D17/12 , F01D7/02 , F02C9/58 , F02C3/10 , F02C7/04 , F02K3/06
Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.
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公开(公告)号：US20190161179A1
公开(公告)日：2019-05-30
申请号：US16091687
申请日：2016-10-03
Applicant: AileLinX Inc.
Inventor： Takakazu Uebori , Shunichi Suzuki
Abstract: A variable pitch mechanism for a helicopter is configured to have a simple configuration with a small number of members, and to be capable of precisely controlling a pitch angle of blades without accurate adjustment. A pitch plate 16 and a pitch plate boss 17 are slidably mounted on an outer periphery of a main mast 61, and an output shaft of a servomotor 19 is directly connected to a pitch lever 18 that vertically moves the pitch plate boss 17. By actuating the servomotor 19 and rotating the pitch lever 18, the pitch plate boss 17 and the pitch plate 16 are displaced upward or downward along the main mast 61, thereby tilting blade holders 13, 13 connected to the pitch plate 16 and changing a pitch angle of the blades 14.
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公开(公告)号：US20190144110A1
公开(公告)日：2019-05-16
申请号：US16090652
申请日：2017-04-03
Applicant: Philip - Bogrash
Inventor： Philip - Bogrash
Abstract: To eliminate stability issues in forward flight due to oncoming flow interfering with the flows produced inside the rotor, rotor shielding or enclosure are used giving it the ability to operate steadily at various forward speeds. Furthermore to improve performance and flows cycloidal rotor/propeller has blades travelling along generally non-circular and elongated track and is able to transition to a variety of other track shapes having corresponding blade orbit shapes. Track shape variation designs similar to such track designs for blade trajectory determination are used for the purpose of changing the blades pitch and their cross-sectional shape. One embodiment uses fixed elliptic shape track upon which run carriages connected to blade shafts. Said track can be inclined about its major axis thereby changing its shape projection onto the plane in which blades travel thus changing the elliptic shape of their orbit. Another embodiment during rotor's transitional phase of operation has computer controlled actuators dynamically varying the blades radial positions and thus their trajectory while each blade also runs on and flexes the track containing electro-rheological fluid in the pivots which, once desired orbital trajectory and corresponding track shape are reached and voltage is applied, instantly solidifies making the track rigid and the actuators disengage until the orbit has to change again. Third embodiment uses flexible track with size varying elements built-in; when these elements are activated in proper sequence by computer control system track flexes into shape corresponding to desired orbit shape. Fourth embodiment uses camshaft with continuous surface around which run rollers linked to blades. Camshaft's axial movement accomplishes change of camshaft cross-section shape being followed by rollers and accordingly results into orbit shape changes. Other embodiments feature the neutralization of centrifugal forces acting on the blades, adjustable shape and position vanes control the flows in, out and inside of rotor to further improve rotor performance, forward thrust and prevent rotorcraft destabilization.
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公开(公告)号：US10259577B2
公开(公告)日：2019-04-16
申请号：US15974473
申请日：2018-05-08
Applicant: AEROVIRONMENT, INC.
Inventor： Dana J. Taylor , Phillip T. Tokumaru , Bart Dean Hibbs , William Martin Parks , David Wayne Ganzer , Joseph Frederick King
IPC: B64C11/32 , B64C29/00 , B64C39/02 , G05D1/08 , B64C27/605 , B64C29/02 , B64C27/26 , B64C27/54 , B64D27/24
Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.
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公开(公告)号：US20190061915A1
公开(公告)日：2019-02-28
申请号：US15693397
申请日：2017-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps
CPC classification number: B64C11/32 , B64C11/06 , B64C11/30 , B64C27/605 , B64C29/0033 , B64C2027/7216 , B64C2027/7255
Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
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