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公开(公告)号：US11584534B2
公开(公告)日：2023-02-21
申请号：US17673031
申请日：2022-02-16
申请人： BETA AIR, LLC
发明人： Nicholas Moy , Riley Griffin , Lochie Ferrier , Collin Freiheit
摘要： Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.
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公开(公告)号：US20220411089A1
公开(公告)日：2022-12-29
申请号：US17361497
申请日：2021-06-29
申请人： BETA AIR, LLC
发明人： Nicholas Moy , Riley Griffin , Lochie Ferrier , Collin Freiheit
摘要： An electric aircraft for generating a yaw force includes a fuselage, a plurality of laterally extending elements secured to the fuselage, a plurality of lift components attached to the plurality of laterally extending elements, and at least a longitudinal thrust component attached to the plurality of laterally extending elements, wherein the longitudinal thrust component is configured to generate a yaw force.
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3.发明申请公开(公告)号：US20210229826A1
公开(公告)日：2021-07-29
申请号：US16950044
申请日：2020-11-17
申请人： AIRBUS HELICOPTERS
摘要： The present invention relates to an aircraft provided with a rotary airfoil, a power plant and an assistance system having an electric motor. The power plant comprises a power transmission box and at least one heat engine. The aircraft includes at least one accessory which is set in motion by a secondary output shaft of the power transmission box. The assistance system is provided with a mechanical connection module having a connection shaft which is connected to the secondary output shaft. A first connection member is connected to said at least one accessory and is connected by a first mechanical link internal to the connection shaft, a second connection member being connected to the electric motor and connected by a second mechanical link internal to the connection shaft.
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4.发明授权公开(公告)号：US11027854B2
公开(公告)日：2021-06-08
申请号：US16983347
申请日：2020-08-03
IPC分类号： G01C23/00 , B64D31/10 , B64D43/00 , G08G5/04 , F02C7/26 , F02C9/26 , F02C9/54 , G05D1/00 , G05D1/08 , G05D3/12 , G08G5/00
摘要： Aircraft autothrottle system, having a motor to impart rotational movement to a shaft extending from the motor. An actuator is connected to the shaft and to an attachment end of a throttle lever having a control end, opposite the attachment end. The actuator has bearings to apply thrust to a longitudinal surface of the shaft such that the actuator is translated longitudinally along the shaft surface in response to motor-imparted rotation of the shaft. The shaft surface being smoothly continuous and longitudinally unbroken along its elongation to allow the actuator to longitudinally slip along the shaft irrespective of any shaft rotation by the motor when the thrust force exceeds a linear force manually applied at the throttle lever. An electronic controller for the motor to move the throttle lever so the motor moves the actuator assembly along the shaft based on an engine parameter monitored by the controller.
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公开(公告)号：US20210122483A1
公开(公告)日：2021-04-29
申请号：US17024211
申请日：2020-09-17
申请人： MYBITCHBOOK, INC.
摘要： Methods and systems are configured to store user data and control access to the user data, wherein the data is stored remotely from the user (such as external to a user's computing device) and the user's data is maintained anonymously. Content is stored in association with a user identifier and access by third parties is controlled by linked third party identifiers.
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公开(公告)号：US20210101692A1
公开(公告)日：2021-04-08
申请号：US16591040
申请日：2019-10-02
申请人： The Boeing Company
发明人： Michael Thomas Fox
IPC分类号： B64D31/10 , B64D27/24 , B64D27/04 , B64D27/10 , B64D29/00 , B64D31/14 , B64D33/02 , B64D33/04 , B64D35/04 , B64D41/00 , B60L50/60 , B60L53/00
摘要： A propulsion system for an aircraft is disclosed, and includes a first propeller, a second propeller, a first hybrid propulsion system, a second hybrid propulsion system, and across-connecting clutch. The first hybrid propulsion system includes a first motor coupled to a first engine by a first overrunning clutch, where the first hybrid propulsion system is operably coupled to drive the first propeller. The second hybrid propulsion system includes a second motor coupled to a second engine by a second overrunning clutch, where the second hybrid propulsion system is operably coupled to drive the second propeller. The cross-connecting clutch is operably coupled to both the first hybrid propulsion system and the second hybrid propulsion system and configured to actuate into an engaged position.
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公开(公告)号：US10800537B2
公开(公告)日：2020-10-13
申请号：US15846664
申请日：2017-12-19
发明人： Philip A. Schmidt
摘要： An aircraft controller includes a memory for storing instructions. The instructions are operable to cause the controller to perform a thrust balancing method and ensure a balanced thrust output from the aircraft.
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公开(公告)号：US10597164B2
公开(公告)日：2020-03-24
申请号：US15972431
申请日：2018-05-07
IPC分类号： B64D31/10 , B64C29/02 , B64C39/02 , B64C27/52 , G05D1/00 , B64D27/26 , G05D3/00 , B64D27/24 , G05D1/10
摘要： An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. 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. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.
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公开(公告)号：US10232950B2
公开(公告)日：2019-03-19
申请号：US15200273
申请日：2016-07-01
摘要： In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.
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公开(公告)号：US10220953B2
公开(公告)日：2019-03-05
申请号：US15367247
申请日：2016-12-02
发明人： Hiroki Ishii , Koji Kawasaki , Takenori Matsue , Shinji Andou , Hiroyasu Baba
摘要： In an aerial vehicle, a malfunction determiner determines whether there is a malfunction in one of thrusters of the aerial vehicle. A flight controller activates the thrusters, and controls the output of each of the thrusters. The flight controller deactivates, when it is determined that there is a malfunction in one of the thrusters as a malfunctioned thruster, the malfunctioned thruster. The flight controller deactivates a selected thruster in the thrusters; the selected thruster being paired to the malfunctioned thruster, and controls the active thrusters except for the deactivated thrusters in all the thrusters to make the flight attitude of the aerial vehicle stable. The flight controller controls the active thrusters to cause the aerial vehicle to land while maintaining the flight attitude of the aerial vehicle being stable.
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