公开(公告)号：US11760471B2

公开(公告)日：2023-09-19

申请号：US16741726

申请日：2020-01-13

申请人： Dave Villard

发明人： Dave Villard

IPC分类号： B64C25/02 ,  B64C27/473 ,  B64C27/80 ,  B64C39/02 ,  F04D25/02 ,  B64U10/13 ,  B64U30/20 ,  B64U50/19

CPC分类号： B64C27/80 ,  B64C27/473 ,  B64C39/024 ,  F04D25/026 ,  B64U10/13 ,  B64U30/20 ,  B64U50/19

摘要： A multi-propeller assembly for a drone, the multi-propeller includes a housing, a motor coupled having a circular cavity surrounded by a plurality of magnets disposed at the opposing second side of the housing, a first, second, and third three-bladed propeller having drive members rotatably coupled within the circular cavity of the motor and nested within each other, wherein the motor is configured to simultaneously rotate the first and third three-bladed propeller in a first direction and the second three-bladed propeller in an opposite second direction using the plurality of magnets.

公开(公告)号：US11702188B2

公开(公告)日：2023-07-18

申请号：US17574383

申请日：2022-01-12

申请人： Kitty Hawk Corporation

发明人： Damon Vander Lind ,  Todd Reichert

IPC分类号： B64C11/32 ,  B64C11/34 ,  B64C11/18 ,  B64C11/46 ,  B64C27/08 ,  B64C27/467 ,  B64C27/80 ,  B64C29/02 ,  B64U30/20

CPC分类号： B64C11/325 ,  B64C11/18 ,  B64C11/343 ,  B64C11/46 ,  B64C27/08 ,  B64C27/467 ,  B64C27/80 ,  B64C29/02 ,  B64U30/20

摘要： A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

公开(公告)号：US20230192290A1

公开(公告)日：2023-06-22

申请号：US17554371

申请日：2021-12-17

申请人： WING Aviation LLC

发明人： Adam Woodworth ,  Giulia B. Pantalone ,  Luis Prado ,  Michelle Suen

IPC分类号： B64C39/02 ,  B64C27/26 ,  B64C27/32 ,  B64C11/00 ,  B64C27/30 ,  B64C27/80 ,  G05D1/10

CPC分类号： B64C39/024 ,  B64C27/26 ,  B64C27/325 ,  B64C11/00 ,  B64C27/30 ,  B64C27/80 ,  G05D1/102 ,  B64C2201/02 ,  B64C2201/108 ,  B64C2201/104 ,  B64C2201/165

摘要： An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.

公开(公告)号：US11597506B2

公开(公告)日：2023-03-07

申请号：US16837509

申请日：2020-04-01

申请人： FT HOLDINGS INC.

发明人： Jason Peter Clarke ,  Daniel John Clarke

IPC分类号： B64C27/605 ,  B64C27/10 ,  B64C27/625 ,  B64D27/24 ,  B64C27/32 ,  B64C27/80 ,  B64C39/02

摘要： A rotor system for aerial vehicles where two or more rotor systems are used in a coaxial or tandem arrangement on the aerial vehicle.

公开(公告)号：US11541998B2

公开(公告)日：2023-01-03

申请号：US16787845

申请日：2020-02-11

申请人： MagLev Aero Inc.

发明人： Ian Morris Randall

IPC分类号： B64C27/20 ,  H02K1/2786 ,  H02N15/00 ,  F01D5/02 ,  B64C27/10 ,  B64D27/24 ,  H02K1/17 ,  H02K1/2793 ,  B64C29/00 ,  B64C13/50 ,  H02K21/22 ,  B64C27/32 ,  H02K1/18 ,  H02K11/21 ,  B64C27/473 ,  H02K21/24 ,  B64C13/26 ,  B64C27/72 ,  B64D35/02 ,  B64D35/04 ,  H02K1/28 ,  H02K16/00 ,  B64C27/68 ,  B64C27/00 ,  B64C29/02 ,  B64C27/14 ,  B64C27/80 ,  B64C39/02 ,  B64D35/06

摘要： Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

公开(公告)号：US11535371B2

公开(公告)日：2022-12-27

申请号：US16647824

申请日：2018-09-06

申请人： AMSL Innovations Pty Ltd

发明人： Andrew Dudley Moore

IPC分类号： B64C29/00 ,  B64C3/38 ,  B64C9/16 ,  B64C27/52 ,  B64C39/06 ,  B64D27/24 ,  B64C9/00 ,  B64C27/80 ,  B64C27/82 ,  B60L15/20 ,  B64C13/00

摘要： A vertical take-off and landing (VTOL) aircraft (10) includes a fuselage and first and second forward wings (20, 22), each wing (20, 22) having a fixed leading edge and a trailing control surface (50) which is pivotal about a generally horizontal pivot axis. The aircraft (10) includes first and second electric motors (60) each having rotors (70), the electric rotors (70) being pivotal with the trailing control surface (50) between a first position in which each rotor (70) has a generally vertical axis of rotation, and a second position in which each rotor (70) has a generally horizontal axis of rotation, a control system (90) is configured to selectively operate the first electric motor (60) and the second electric motor (60) at different rotational speeds to generate a turning moment to pivot the control surface (50) about the pivot axis (33).

公开(公告)号：US20220388647A1

公开(公告)日：2022-12-08

申请号：US17303631

申请日：2021-06-03

申请人： Textron Innovations Inc.

发明人： Steven Ray Ivans ,  Brent Chadwick Ross

IPC分类号： B64C29/00 ,  B64C1/00 ,  B64C7/02 ,  B64C39/04 ,  B64C5/02 ,  B64C39/02 ,  B64C27/80

摘要： A tandem tiltrotor aircraft in which the tiltrotor assemblies are operably coupled at the forward and aft ends of the fuselage of the aircraft is disclosed. The tiltrotor assemblies are capable of rotating between a vertical lift position and a horizontal flight position. The in-line location of the tiltrotor assemblies allow the aircraft to have the vertical take-off and landing capabilities, and, in combination with the at least one wing, can be used in horizontal flight. The aft rotor assembly can assume a horizontal flight position that places the rotor blades forward of a vertical fin of the aircraft. In another embodiment, a winged triple tiltrotor aircraft is disclosed. In another embodiment, a winged quad tiltrotor aircraft is disclosed.

公开(公告)号：US11440650B2

公开(公告)日：2022-09-13

申请号：US15504525

申请日：2015-09-30

申请人： SIKORSKY AIRCRAFT CORPORATION

发明人： Erez Eller ,  Matthew A. White ,  David H. Hunter

IPC分类号： B64C27/10 ,  F16F15/02 ,  B64C27/00 ,  B64C27/14 ,  B64C1/00 ,  B64C7/00 ,  B64C13/18 ,  B64C13/50 ,  B64C19/00 ,  B64C27/12 ,  B64C27/32 ,  B64C27/33 ,  B64C27/473 ,  B64C27/48 ,  B64C27/51 ,  B64C27/52 ,  B64C27/54 ,  B64C27/78 ,  B64C27/80 ,  B64C27/82 ,  B64D39/00 ,  B64D39/06 ,  B64D45/02 ,  F16H37/02 ,  G05D1/00 ,  G05D1/02 ,  B64C27/16 ,  B64C13/04 ,  G05D1/08 ,  B64C27/57 ,  B64D35/06 ,  B64C27/467 ,  F02C9/28 ,  F16D13/52 ,  F16D13/72 ,  F16D13/74 ,  B64C27/08

摘要： An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

公开(公告)号：US20220219807A1

公开(公告)日：2022-07-14

申请号：US17574383

申请日：2022-01-12

申请人： Kitty Hawk Corporation

发明人： Damon Vander Lind ,  Todd Reichert

IPC分类号： B64C11/32 ,  B64C11/34 ,  B64C11/18 ,  B64C11/46 ,  B64C27/08 ,  B64C27/467 ,  B64C27/80 ,  B64C29/02

摘要： A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

公开(公告)号：US20210323661A1

公开(公告)日：2021-10-21

申请号：US17335085

申请日：2021-06-01

申请人： Suzhou Taoxun Aviation Technology Co., Ltd.

发明人： Xun GE ,  Yuan SHEN ,  Shuzhen GUO ,  Liangwei LI ,  Weidong LIU

IPC分类号： B64C27/80 ,  B64C27/10 ,  B64C27/605

摘要： The application discloses a coaxial helicopter, the cyclic pitch-changing mechanism simultaneously adjusts the pitches of the upper and the lower rotor systems, to make uniformity cyclic pitch-changing adjustment of the upper and lower rotors, and make independent collective pitch adjustment of the upper rotor system; the differential pitch-changing mechanism and the cyclic pitch-changing mechanism jointly act on the lower rotor system, to perform differential collective pitch adjustment of the upper and lower rotor systems. The synchronous rotating mechanism drives the swashplate members to synchronously rotate along with the drive shaft. The application achieves a simpler hybrid pitch-changing control system of the coaxial rotor pitch, a plurality of flight operations of the coaxial aircraft are performed synchronously, and a plurality of flight control modes, such as semi-differential and full-differential in a variable speed or a fixed speed mode, are supported, and thus the present application has wider application space.