Patents Assigned to Archer Aviation, Inc.
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Patent number: 11975853Abstract: 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.Type: GrantFiled: April 18, 2023Date of Patent: May 7, 2024Assignee: ARCHER AVIATION, INC.Inventors: Scott Graves, Alan D. Tepe
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Patent number: 11975854Abstract: 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.Type: GrantFiled: April 25, 2023Date of Patent: May 7, 2024Assignee: ARCHER AVIATION, INC.Inventors: Alan D. Tepe, Stephen Michael Spiteri, Scott Graves, Alan Baldwin, Wei Wu, Robert Wayne Moore, Michael Zwiers, Diederik Marius
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Publication number: 20240140590Abstract: Disclosed are electric vertical take-off and landing (eVTOL) aircraft gaming apparatuses and methods. In one embodiment, a video game apparatus comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft in a video game using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.Type: ApplicationFiled: October 31, 2023Publication date: May 2, 2024Applicant: Archer Aviation, Inc.Inventors: Nathan Thomas DEPENBUSCH, Jeffery Scott Greenwood
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Publication number: 20240132224Abstract: A method of controlling an electric aircraft that has a plurality of actuators that includes a plurality of electric propulsion units includes: receiving force and moment commands for the electric aircraft; determining control commands for the plurality of actuators based on the desired force and moment commands by solving an optimization problem that comprises a noise minimization term for minimizing noise generated by the electric propulsion units; and controlling the plurality of actuators according to the determined control commands to meet the force and moment commands for the electric aircraft.Type: ApplicationFiled: December 28, 2023Publication date: April 25, 2024Applicant: Archer Aviation Inc.Inventors: Geoffrey C. BOWER, Nansi XUE, Alan CHEN, Benjamin GOLDMAN, Nathan DEPENBUSCH
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Publication number: 20240132222Abstract: In an embodiment, a system may comprise at least two power supplies which may comprise a first power source, a first step-down converter, a first switching device, a first bus, a second power source, a second step-down converter, a second switching device, and a second bus, the first and second buses being electrically separate. An exemplary system may further comprise an alternate power supply comprising a third power source and an alternate step-down converter connected to at least the first and second buses via at least a third switching device, the alternate power supply acting as a backup power supply configured to be used after a failure of one or more of the at least two power supplies. In some embodiments, the first and second switching devices may be controlled by at least a first controller and the at least third switching device may be controlled by an alternate controller.Type: ApplicationFiled: May 3, 2023Publication date: April 25, 2024Applicant: Archer Aviation Inc.Inventors: Pedro Roberto Paterson CARLEIAL, Marco Da Silva, Daniel Kenji Nishimaru, Denesh Jain
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Publication number: 20240136887Abstract: A rotor assembly has a sleeve, a rotor hub, a lamination core, and a plurality of tapered magnets disposed circumferentially around an inner diameter of the sleeve. The plurality of tapered magnets are configured to abut on one another. The plurality of tapered magnets includes a first set of tapered magnets and a second set of tapered magnets. Insertion of the first set of tapered magnets axially relative to the second set of tapered magnets is configured to increase a diameter of the sleeve. The rotor hub is configured to retain at least one of the lamination core, the plurality of tapered magnets, or the sleeve.Type: ApplicationFiled: December 27, 2023Publication date: April 25, 2024Applicant: Archer Aviation Inc.Inventors: Scott GRAVES, Diego SILVA
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Patent number: 11958621Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.Type: GrantFiled: December 6, 2023Date of Patent: April 16, 2024Assignee: ARCHER AVIATION, INC.Inventor: Scott Graves
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Publication number: 20240116627Abstract: A VTOL aircraft includes a plurality of lift propellers configured to rotated by lift motors to provide vertical thrust during takeoff, landing and hovering operations. The lift propellers are configured to generate a cooling airflow to cool the lift motors during use. During a cruise operation when the VTOL aircraft is in forward motion, the lift propellers may be stowed in a stationary position. Therefore, the cooling airflow may be reduced or eliminated when it is not needed.Type: ApplicationFiled: February 2, 2023Publication date: April 11, 2024Applicant: Archer Aviation, Inc.Inventors: Karthik Kumar BODLA, Bharat TULSYAN, Christopher M. HEATH, Kerry MANNING, Alan D. TEPE
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Publication number: 20240116629Abstract: A tilt propeller for a vertical takeoff and landing (VTOL) aircraft includes a linked low pitch stop (LLPS). The LLPS serves as a secondary pitch control system that is activated when a primary pitch control system fails. The LLPS may include a pitch rod coupled to a propeller blade yoke, and a mechanical coupling that correlates the tilt angle of the propeller with a pitch angle setting of the LLPS. The pitch rod may be separated by a gap from the mechanical coupling during normal operation. If the primary pitch control fails, the pitch rod is forced into contact with the mechanical coupling to close the gap and form a load-bearing path to control the pitch angle.Type: ApplicationFiled: September 29, 2023Publication date: April 11, 2024Applicant: Archer Aviation, Inc.Inventors: Nathan STORRS, Jonathan BENO
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Publication number: 20240116628Abstract: 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.Type: ApplicationFiled: April 5, 2023Publication date: April 11, 2024Applicant: Archer Aviation, Inc.Inventors: Jonathan Anthony BENO, Benjamin Scott DYER, Nathan Daniel STORRS
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Publication number: 20240116643Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.Type: ApplicationFiled: December 6, 2023Publication date: April 11, 2024Applicant: Archer Aviation Inc.Inventor: Scott GRAVES
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Publication number: 20240116639Abstract: 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.Type: ApplicationFiled: April 12, 2023Publication date: April 11, 2024Applicant: Archer Aviation Inc.Inventors: Scott GRAVES, Robert Wayne MOORE
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Publication number: 20240116641Abstract: 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.Type: ApplicationFiled: April 25, 2023Publication date: April 11, 2024Applicant: Archer Aviation, Inc.Inventors: Alan D. TEPE, Stephen Michael SPITERI, Scott GRAVES, Alan BALDWIN, Wei WU, Robert Wayne MOORE, Michael ZWIERS, Diederik MARIUS
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Publication number: 20240116642Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.Type: ApplicationFiled: September 28, 2023Publication date: April 11, 2024Applicant: Archer Aviation Inc.Inventor: Scott GRAVES
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Publication number: 20240120590Abstract: This disclosure relates generally to an apparatus for organizing battery cells. The apparatus includes a block including: sleeves forming chambers, a first sheet configured to locate the sleeves, and a foam structure surrounding the sleeves. Each chamber is configured to accommodate a battery cell. The block is configured to: organize the battery cells into battery cell groups, separate each battery cell group from its adjacent battery cell groups using a thermally insulating material, and prevent gas from entering into each battery cell group from its adjacent battery cell groups. Each battery cell group includes a plurality of the battery cells, each of the battery cells in the battery cell group is adjacent to at least another of the battery cells in the battery cell group. Each battery cell group is adjacent to at least another battery cell group.Type: ApplicationFiled: April 7, 2023Publication date: April 11, 2024Applicant: Archer Aviation, Inc.Inventors: Alex CLARABUT, Likhith MADAMANCHI, Alex Ho YANG, Ryan Joseph CHERNIAK, Kerry MANNING
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Publication number: 20240120869Abstract: 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.Type: ApplicationFiled: August 1, 2023Publication date: April 11, 2024Applicant: Archer Aviation, Inc.Inventors: Alan TEPE, Stephen SPITERI, Wei WU, Diederik MARIUS
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Publication number: 20240116640Abstract: 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.Type: ApplicationFiled: April 18, 2023Publication date: April 11, 2024Applicant: Archer Aviation Inc.Inventors: Scott GRAVES, Alan D. TEPE
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Publication number: 20240117829Abstract: A joint assembly for an aircraft comprising: a joint comprising a first portion rotatably coupled to a second portion so that the first portion can rotate relative to the second portion; an actuator for rotating the first portion of the joint and comprising a connecting portion that connects to the first portion of the joint; and a latch moveable to a latched arrangement in which the latch prevents rotation of the first portion of the joint in at least one rotational direction, the latch being biased toward the latched arrangement and operatively connected to the connecting portion such that if the connecting portion becomes separated from the rest of the actuator, the latch moves to the latched arrangement, thereby preventing rotation of the first portion of the joint in the at least one rotational direction.Type: ApplicationFiled: March 24, 2023Publication date: April 11, 2024Applicant: Archer Aviation, Inc.Inventor: Guy BERNARD
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Patent number: 11945597Abstract: A method of controlling an electric aircraft that has a plurality of actuators that includes a plurality of electric propulsion units includes: receiving force and moment commands for the electric aircraft; determining control commands for the plurality of actuators based on the desired force and moment commands by solving an optimization problem that comprises a noise minimization term for minimizing noise generated by the electric propulsion units; and controlling the plurality of actuators according to the determined control commands to meet the force and moment commands for the electric aircraft.Type: GrantFiled: January 25, 2021Date of Patent: April 2, 2024Assignee: ARCHER AVIATION, INC.Inventors: Geoffrey C. Bower, Nansi Xue, Alan Chen, Benjamin Goldman, Nathan Depenbusch
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Patent number: 11945594Abstract: A electric aircraft power distribution system includes a first battery pack connected to at least a first load and to a common bus that connects the first battery pack in parallel to at least a second battery pack; a first electrical component electrically connected between the first battery pack and the first load and configured to disconnect the first load from the first battery pack in response to current above a first threshold current, wherein the first electrical component has a first disconnection time at the first threshold current; and a second electrical component electrically connected between the first battery pack and the common bus and configured to disconnect the first battery pack from the common bus in response to current above a second threshold current, wherein the second electrical component has a second disconnection time at the second threshold current that is higher than the first disconnection time.Type: GrantFiled: July 21, 2023Date of Patent: April 2, 2024Assignee: ARCHER AVIATION, INC.Inventor: John Melack