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1.发明公开公开(公告)号：US20240336367A1
公开(公告)日：2024-10-10
申请号：US18293659
申请日：2022-08-02
IPC分类号： B64D35/021 , B64D27/30 , B64D31/06
CPC分类号： B64D35/021 , B64D27/30 , B64D31/06
摘要： A turboprop includes a propeller, a propeller shaft carrying the propeller, the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine having at least a first configuration in which it is mechanically coupled to the propeller shaft and at least one oil pump configured to supply a hydraulic circuit for adjusting the pitch of the propeller. The oil pump is configured to be electrically operated. An aircraft can include such a turboprop and methods can control such a turboprop and such an aircraft.
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公开(公告)号：US12122525B2
公开(公告)日：2024-10-22
申请号：US18296062
申请日：2023-04-05
IPC分类号： B64C29/00 , B60L15/06 , B60L15/38 , B64C27/54 , B64D27/24 , B64D27/30 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K15/03 , H02M7/5395 , H02P21/00 , H02P25/16 , H02P27/06 , H02P27/08 , H02K7/00
CPC分类号： B64D27/24 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/0008 , B64C29/0033 , B64D27/30 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/203 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K15/03 , H02M7/5395 , H02P21/50 , H02P25/16 , H02P27/06 , H02P27/08 , B60L2200/10 , B60L2210/40 , H02K7/006
摘要： A system for an aircraft includes a tiltable proprotor that is tiltable between a lift position for providing lift for the aircraft and a forward flight position for providing forward propulsion for the aircraft is provided. The system includes at least one actuator for adjusting a tilt angle of the tiltable proprotor; and at least one passive damper connected to the tiltable proprotor and configured to limit a rate of change of the tilt angle of the tiltable proprotor.
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公开(公告)号：US20240280066A1
公开(公告)日：2024-08-22
申请号：US18639822
申请日：2024-04-18
申请人： Morteza Vadipour
发明人： Morteza Vadipour
CPC分类号： F02K1/78 , F02K5/00 , B64C29/0008 , B64D27/30
摘要： A peripheral propulsion system having a propulsion unit, an upper section, and a lower section. The propulsion unit has a motor, a motor engagement section, an extension coupled to the motor engagement section, and two or more blades coupled to the extension. The extension is located between the upper section and the lower section. The output section is located about at least a portion of the lower section, and the two or more blades are located outside a periphery of the vehicle. When the motor is running, the two or more blades are capable of drawing fluid from about the periphery of the vehicle and through the output section.
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公开(公告)号：US20240213825A1
公开(公告)日：2024-06-27
申请号：US18556259
申请日：2022-04-27
摘要： A stator for an electric machine comprises: —a body; —a plurality of stator teeth fixed on the body; and—a plurality of tooth windings, which each have a first electrical conductor, which runs from one end portion, via at least one winding portion around at least one stator tooth, to another end portion, and a second electrical conductor, which is electrically insulated from the first electrical conductor and which runs from one end portion, via the at least one winding portion around the same at least one stator tooth, to another end portion; wherein one end portion of each of the first and second electrical conductors of the tooth windings can be or is electrically connected to an inverter, and the other end portions of the first electrical conductors of the tooth windings are electrically interconnected at a star point.
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公开(公告)号：US20240317416A1
公开(公告)日：2024-09-26
申请号：US18679884
申请日：2024-05-31
申请人： DENSO CORPORATION
发明人： Yuichi TAKEMURA , Shun SUGITA , Shingo NAKATA
CPC分类号： B64D33/08 , G01K1/026 , G01K3/005 , B64C29/0008 , B64D27/30
摘要： A control device is configured to control an electric flight vehicle. The electric flight vehicle includes an electric drive device configured to drive and rotate a rotor blade and a cooling unit configured to cool the drive device. The control device includes a temperature acquisition unit and a cooling determination unit. The temperature acquisition unit is configured to acquire temperature of the drive device as a device temperature. The cooling determination unit is configured to determine, according to the device temperature, whether a cooling-related abnormality has occurred as an abnormality related to cooling of the drive device by the cooling unit.
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公开(公告)号：US20240317413A1
公开(公告)日：2024-09-26
申请号：US18612116
申请日：2024-03-21
发明人： Andreas REEH , Gunar REINICKE , Robert BARKER
摘要： An electrical machine for integration into a vehicle frame structure is provided. The vehicle frame structure includes a structural wall that at least partially encloses an inner volume. The electrical machine includes a rotor with a rotor shaft. The rotor shaft is rotatable around a rotational axis, and is connectable to a propulsor for transferring torque to or from a fluid. The electrical machine includes a first bearing unit configured to hold the rotor shaft in a rotatable manner and a second bearing unit configured to hold the rotor shaft in a rotatable manner. The first bearing unit is releasably attachable to a first wall region of the structural wall, and the second bearing unit is releasably attachable to a second wall region of the structural wall. The first wall region and the second wall region are spaced apart with respect to the rotational axis.
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公开(公告)号：US20240208659A1
公开(公告)日：2024-06-27
申请号：US18536416
申请日：2023-12-12
发明人： Kerry Gregg Manning
CPC分类号： B64D27/40 , B64C29/0008 , B64D27/30
摘要： An articulating motor mount assembly including a first frame segment attachable to an airframe of an aircraft. A second frame segment is rotatably coupled to the first frame segment in a plane oblique to a longitudinal axis of the first frame segment. A third frame segment is rotatably coupled to the second frame segment in a plane oblique to a longitudinal axis of the second frame segment and configured to carry a thrust device. A first actuator is positioned to rotate the second frame segment relative to the first frame segment and a second actuator is positioned to rotate the third frame segment relative to the second frame segment.
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公开(公告)号：US20240322640A1
公开(公告)日：2024-09-26
申请号：US18598963
申请日：2024-03-07
摘要： A cooling structure for a rotary electric machine, the structure comprising an annular radiator body defining an axis X between a first end and a second end, the annular body having a radially inner wall and a radially outer wall and a plurality of channels defined between the radially inner wall and the radially outer wall, each extending from the first end to the second end, each channel having an inner surface defining the channel through which a coolant flows, in use, and wherein surface features are provided on the inner surface of the channels.
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公开(公告)号：US20240250585A1
公开(公告)日：2024-07-25
申请号：US18292434
申请日：2022-07-15
摘要： Aircraft electric propulsion system including: a motor including a hollow rotor, and a power and control electronics device, in which the power and control electronics device includes at least two ring-shaped electrical tracks each including at least two inverters, the inverters being connected to each other in parallel, wherein the electrical tracks delimit a hollow circular part of the power and control electronics device, the hollow circular part being placed in the axis of the hollow rotor of the motor.
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公开(公告)号：US12030656B1
公开(公告)日：2024-07-09
申请号：US18599703
申请日：2024-03-08
申请人： Archer Aviation Inc.
发明人： Scott Graves , Alan D. Tepe , Robert Wayne Moore
CPC分类号： B64D27/24 , B64C29/0033 , B64D27/30 , B64D33/08
摘要： An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
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