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公开(公告)号：US12227300B2
公开(公告)日：2025-02-18
申请号：US18620917
申请日：2024-03-28
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Robert Wayne Moore
IPC: H02K11/33 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/00 , B64D27/24 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K15/03 , H02M7/5395 , H02P21/00 , H02P25/16 , H02P27/06 , H02P27/08 , H02K7/00
Abstract: An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main shaft connected to the rotor via a gear reduction, wherein the main shaft extends through the rotor. The electric motor assembly may include a collar connected to the main shaft, wherein the collar encircles the main shaft, and at least a portion of the collar is configured to direct a fluid away from the main shaft and toward the stator ring.
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公开(公告)号：US12208908B2
公开(公告)日：2025-01-28
申请号：US18620493
申请日：2024-03-28
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Alan D. Tepe
IPC: 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
Abstract: 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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3.发明授权
公开(公告)号：US12199541B2
公开(公告)日：2025-01-14
申请号：US18401446
申请日：2023-12-30
Applicant: Archer Aviation, Inc.
Inventor： Guy Bernard , Geoffrey Bower , Diederik Marius , Kurt Wagner , Stephen Spiteri
Abstract: An aircraft system for damping movement of a structural flight element. The aircraft system including a moveable aircraft structure, a power source, a controller, a resistor, and a first transistor connected in series to the resistor. When the power source of the aircraft is providing power, the controller controls the first transistor to prevent current flow through its terminals and through the resistor. Further, when the power source of the aircraft is not providing power, the first transistor allows current generated by a back EMF (electromotive force) voltage to flow through its terminals and through the resistor, the back EMF voltage being created by movement of the moveable aircraft structure.
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公开(公告)号：US20240379275A1
公开(公告)日：2024-11-14
申请号：US18656699
申请日：2024-05-07
Applicant: Archer Aviation Inc.
Inventor： Harshit SONI , Stephen SPITERI
Abstract: The embodiments of the present disclosure provide systems and methods of forming a transformer with enhanced leakage inductance for power conversion. The transformer may include a toroidal core, a primary winding around a first portion of the toroidal core, a secondary winding around a second portion of the toroidal core different from the first portion, and a magnetic material disposed within a cavity formed by the toroidal core. The magnetic material may comprise a ferrite. The method of forming a transformer may include the steps of providing a toroidal core, winding a primary coil around a first portion of the toroidal core, winding a secondary coil around a second portion of the toroidal core, and disposing a magnetic material within the cavity formed by the toroidal core to enhance the leakage inductance of the transformer.
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公开(公告)号：US12122528B2
公开(公告)日：2024-10-22
申请号：US18622656
申请日：2024-03-29
Applicant: Archer Aviation Inc.
Inventor： Alan D. Tepe
CPC classification number: B64D27/24 , B64C29/0033 , H02P25/16 , H02P27/06
Abstract: An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
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公开(公告)号：US12122527B2
公开(公告)日：2024-10-22
申请号：US18622647
申请日：2024-03-29
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Alan Baldwin , Stephen Michael Spiteri , Wei Wu , Alan D. Tepe
CPC classification number: B64D27/24 , B64C29/0033 , H02P25/16 , H02P27/06
Abstract: An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
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公开(公告)号：US20240326629A1
公开(公告)日：2024-10-03
申请号：US18740189
申请日：2024-06-11
Applicant: Archer Aviation, Inc.
Inventor： Alex CLARABUT , Paul FRIHAUF , Yalan BI , Holger TEICHGRAEBER , Mamdouh MUBARAK ALTAYEB , Jon David PETERSON
CPC classification number: B60L53/62 , B60L53/14 , B60L58/26 , B64F1/35 , H02J7/0047 , H02J7/00714 , B60L2200/10
Abstract: Aspects of the present disclosure generally relate to systems and methods for the configuration and control of charging and cooling systems for aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a method of charging an aircraft is disclosed comprising: receiving a mode of operation indicating whether battery packs of the aircraft are connected in parallel prior to joining a charging bus, receiving charging protocol information, and controlling charging operations of the battery packs based on the mode of operation and the charging protocol information.
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公开(公告)号：US20240300659A1
公开(公告)日：2024-09-12
申请号：US18663960
申请日：2024-05-14
Applicant: Archer Aviation, Inc.
Inventor： Alan TEPE , Stephen SPITERI , Wei WU , Diederik MARIUS
IPC: B64D27/24 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/00 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/20 , H02K7/00 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K15/03 , H02M7/5395 , H02P21/00 , H02P25/16 , H02P27/06 , H02P27/08
CPC classification number: B64D27/24 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/0008 , B64C29/0033 , 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
Abstract: An electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to alternate current (AC) voltages to drive a first set of stator windings of the electrical motor, in response to a first pulse width modulation (PWM) vector, and a second inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to AC voltages to drive a second set of stator windings of the electrical motor, in response to a second PWM vector. The first PWM vector and the second PWM vector are substantially equal and opposite vectors.
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公开(公告)号：US20240253796A1
公开(公告)日：2024-08-01
申请号：US18622656
申请日：2024-03-29
Applicant: Archer Aviation Inc.
Inventor： Alan D. TEPE
CPC classification number: B64D27/24 , B64C29/0033 , H02P25/16 , H02P27/06
Abstract: An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
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公开(公告)号：US12024304B2
公开(公告)日：2024-07-02
申请号：US18299276
申请日：2023-04-12
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Robert Wayne Moore
IPC: H02K11/33 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/00 , B64D27/24 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K15/03 , H02M7/5395 , H02P21/00 , H02P25/16 , H02P27/06 , H02P27/08 , H02K7/00
CPC classification number: B64D27/24 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/0008 , B64C29/0033 , 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
Abstract: An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main shaft connected to the rotor via a gear reduction, wherein the main shaft extends through the rotor. The electric motor assembly may include a collar connected to the main shaft, wherein the collar encircles the main shaft, and at least a portion of the collar is configured to direct a fluid away from the main shaft and toward the stator ring.
