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公开(公告)号:US20250019082A1
公开(公告)日:2025-01-16
申请号:US18401316
申请日:2023-12-29
Applicant: Joby Aero, Inc.
Inventor: Joeben BEVIRT , Alex STOLL
Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The deployment mechanisms deploy the rotor forward and up as they deploy from a forward flight configuration to a vertical thrust configuration. A single motor may drive two co-axial propellers, with a first propeller driven when the motor spins in a first direction, and a second propeller driven when the motor spins in a second direction.
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公开(公告)号:US11919652B2
公开(公告)日:2024-03-05
申请号:US18097497
申请日:2023-01-17
Applicant: JOBY AERO, INC.
Inventor: JoeBen Bevirt , Alex Stoll
CPC classification number: B64D27/24 , B64C11/28 , B64C29/0033 , B64C39/068 , Y02T50/60
Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The deployment mechanisms deploy the rotor forward and up as they deploy from a forward flight configuration to a vertical thrust configuration.
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公开(公告)号:US11884388B2
公开(公告)日:2024-01-30
申请号:US18149550
申请日:2023-01-03
Applicant: Anduril Industries, Inc.
Inventor: Nicholas Robert Alley , Joshua Lemming Steele , Jesse Owen Williams , Daniel Kuehme , Jonathan Caleb Phillips
IPC: B64C39/02 , B64C3/56 , B64U10/25 , B64U30/12 , B64U101/00 , B64C3/40 , B64C5/12 , B64C5/16 , B64C3/54 , B64C13/24 , B64C1/36 , B64C11/28 , B64C13/30 , B64C5/02 , B64U101/30
CPC classification number: B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2211/00 , B64U10/25 , B64U30/12 , B64U2101/00 , B64U2101/30 , Y02T50/10 , Y02T50/40
Abstract: An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.
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公开(公告)号:US11814153B2
公开(公告)日:2023-11-14
申请号:US17552052
申请日:2021-12-15
Applicant: Bell Textron Inc.
Inventor: Kyle Thomas Cravener , Andrew Maresh , Jonathan Andrew Knoll
CPC classification number: B64C11/28 , B64C11/04 , B64C27/28 , B64C29/0033
Abstract: A system for retaining a folded proprotor blade in flight. The system includes a mounting plate, a first arm coupled to the mounting plate at an acute angle relative to the mounting plate, and a first deformable pad affixed to the first arm and adapted to contact the folded proprotor blade.
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公开(公告)号:US11745853B2
公开(公告)日:2023-09-05
申请号:US16821266
申请日:2020-03-17
Applicant: Bell Textron Inc.
Inventor: Andrew Ryan Maresh , Kyle Thomas Cravener
CPC classification number: B64C11/02 , B64C11/28 , B64C27/35 , B64C29/0033 , F16D3/26
Abstract: Embodiments are directed to a rotor hub assembly comprising a yoke configured to attach rotor blades thereto, a single Hooke's joint configured to attach to, and transmit forces between, a mast and the yoke, and a spherical bearing coupled between the yoke and the mast. Two pillow blocks couple the single Hooke's joint to the yoke. An adapter sleeve is attached to the pillow blocks and is positioned to surround the spherical bearing. The adapter sleeve extends between the single Hooke's joint and the mast. A hub lock extension is attached to the yoke. The hub lock extension is configured to receive a hub lock that prevents gimballing of the yoke when engaged.
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公开(公告)号:US11713687B1
公开(公告)日:2023-08-01
申请号:US17696995
申请日:2022-03-17
Applicant: General Electric Company
Inventor: Gregory L. Detweiler
CPC classification number: F01D7/00 , B64C11/28 , B64C11/30 , F01D5/021 , F05D2220/36 , F05D2260/70
Abstract: An engine defining a longitudinal axis includes: a turbomachine; a fan drivingly coupled with the turbomachine, the fan being a forward thrust fan and having: a hub; a plurality of fan blades, the plurality of fan blades comprising a first fan blade; and a flapping hinge integrated into the first fan blade or coupled to the fan blade, at least a portion of the first fan blade moveable about the flapping hinge to define a variable angle with the longitudinal axis.
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公开(公告)号:US11618550B2
公开(公告)日:2023-04-04
申请号:US17220097
申请日:2021-04-01
Applicant: The Boeing Company
Inventor: Michael J. Duffy , Matthew S. Stauffer
IPC: B64C11/28 , B64C39/02 , B64C11/04 , B64C27/30 , B64C29/00 , B64C27/26 , B64C27/473 , B64U30/10 , B64U30/20 , B64U70/80
Abstract: A rotor assembly for a fixed-wing VTOL aircraft. The rotor assembly is configured to provide vertical flight for the fixed-wing VTOL aircraft. In one embodiment, the rotor assembly includes a hub assembly, a first rotor blade affixed to the hub assembly, and a second rotor blade affixed to the hub assembly. The hub assembly orients the second rotor blade in relation to the first rotor blade about an axis of rotation of the hub assembly with the first rotor blade and the second rotor blade vertically stacked when the hub assembly is stopped for wing-borne flight.
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公开(公告)号:US11613355B2
公开(公告)日:2023-03-28
申请号:US16920017
申请日:2020-07-02
Applicant: Bell Textron Inc.
Inventor: Carlos Alexander Fenny , Rohn Lee Olson , Andrew James Zahasky
IPC: B64C39/06 , B64D27/24 , B64C29/02 , B64C11/28 , B64C27/50 , B64C3/16 , B64C3/10 , B64C27/08 , B64C29/00 , B64C27/12 , B64D31/00 , B64C1/06 , B64C39/02 , B64C39/00 , B64C1/00 , B64D27/02
Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.
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公开(公告)号:US11603203B2
公开(公告)日:2023-03-14
申请号:US16717524
申请日:2019-12-17
Applicant: TEXTRON INNOVATIONS INC.
Inventor: Carlos Alexander Fenny , Rohn Lee Olson
IPC: B64D27/24 , B64D27/02 , B64C39/06 , B64C11/28 , B64C27/50 , B64C3/16 , B64C3/10 , B64C27/08 , B64C29/00 , B64C27/12 , B64D31/00 , B64C29/02 , B64C1/06 , B64C39/02 , B64C39/00 , B64C1/00
Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.
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公开(公告)号:US11603192B2
公开(公告)日:2023-03-14
申请号:US17144437
申请日:2021-01-08
Applicant: Hyundai Motor Company , Kia Motors Corporation
Inventor: Sang Hyun Jung , Jae Young Choi
Abstract: A foldable blade assembly may include a first blade, a motor configured to rotate the first blade, a second blade of which a rotation center coincides with a rotation center of the first blade, and an actuator configured to move the second blade upward or downward to selectively couple the second blade to the first blade so that the second blade and the first blade are rotated together or configured to release the coupling between the second blade and the first blade.
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