公开(公告)号：USD1062878S1

公开(公告)日：2025-02-18

申请号：US29936150

申请日：2024-04-05

Applicant: Archer Aviation, Inc.

Designer： Julien Montousse ,  Niki James Smart ,  Nicolas Rousseau ,  Young-Joon Suh ,  Erik Saetre ,  Julien Thiebaud ,  Geoffrey Christien Bower ,  Giovanni Droandi ,  Spencer Robert Fugal ,  Alexander Oliver Haas ,  Dev Gorur Rajnarayan ,  Nischint Rajmohan ,  Jenner Grey Richards ,  Bernardo Augusto de Oliveira Vieira

公开(公告)号：US12195193B2

公开(公告)日：2025-01-14

申请号：US18622643

申请日：2024-03-29

Applicant: Archer Aviation Inc.

Inventor： Alan D. Tepe ,  Alan Baldwin

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 ,  H02K7/08 ,  H02K7/116 ,  H02K9/19 ,  H02K11/33 ,  H02K15/03 ,  H02M7/5395 ,  H02P21/00 ,  H02P25/16 ,  H02P27/06 ,  H02P27/08 ,  H02K7/00

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.

公开(公告)号：US12122525B2

公开(公告)日：2024-10-22

申请号：US18296062

申请日：2023-04-05

Applicant: Archer Aviation, Inc.

Inventor： Jonathan Anthony Beno ,  Benjamin Scott Dyer ,  Nathan Daniel Storrs

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

CPC classification number: 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

Abstract: 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.

公开(公告)号：US12122504B1

公开(公告)日：2024-10-22

申请号：US18542479

申请日：2023-12-15

Applicant: Archer Aviation Inc.

Inventor： Eric S. Loos ,  Danny L. Ball ,  Jacob P. Virkler ,  Matthew J. Morgan

IPC: B64C11/04 ,  F01D5/30

CPC classification number: B64C11/04 ,  F01D5/30

Abstract: Apparatus, systems, and methods for a propeller blade retention system. The retention system may include a hub including a socket formed by an inner surface of the hub, a blade extending into the socket and a retention sleeve having a first portion and a second portion. The retention system may include a filler sleeve disposed between the blade and the second portion of the retention sleeve, a first bearing disposed between the second portion of the retention sleeve and the inner surface of the hub, the first bearing having a first race, and a second bearing disposed between the first portion of the retention sleeve and the inner surface of the hub, the second bearing having a second race. The retention system may include a cap comprising a body portion and a flange portion. The retention system may include a shim carrier.

公开(公告)号：US20240326599A1

公开(公告)日：2024-10-03

申请号：US18737373

申请日：2024-06-07

Applicant: Archer Aviation Inc.

Inventor： Saienath POOPALARAJAH ,  Pedro Roberto Paterson CARLEIAL ,  Paul FRIHAUF

IPC: B60L3/04 ,  B60L50/60 ,  B64C29/00 ,  H01M50/583 ,  H02H7/20

CPC classification number: B60L3/04 ,  B60L50/60 ,  H01M50/583 ,  H02H7/20 ,  B60L2200/10 ,  B64C29/0008 ,  H01M2200/103 ,  H01M2220/20

Abstract: An electrical system for an aircraft, comprising at least one processor configured to: receive aircraft movement information, detect that the movement information indicates a potential crash, detect a loss of continuity in at least one low voltage wire, and blow a battery pack fuse to disconnect supply of the high voltage power to the aircraft.

公开(公告)号：US12100850B2

公开(公告)日：2024-09-24

申请号：US18297138

申请日：2023-04-07

Applicant: Archer Aviation, Inc.

Inventor： Alex Clarabut ,  Likhith Madamanchi ,  Alex Ho Yang ,  Ryan Joseph Cherniak ,  Kerry Manning

IPC: H01M50/24 ,  B60L50/60 ,  B64D27/24 ,  H01M50/209 ,  H01M50/213 ,  H01M50/229 ,  H01M50/242 ,  H01M50/291 ,  H01M50/383 ,  B64C29/00

CPC classification number: H01M50/209 ,  B60L50/66 ,  B64D27/24 ,  H01M50/213 ,  H01M50/229 ,  H01M50/24 ,  H01M50/242 ,  H01M50/291 ,  H01M50/383 ,  B60L2200/10 ,  B64C29/0008 ,  H01M2220/20

Abstract: 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.

公开(公告)号：US20240297397A1

公开(公告)日：2024-09-05

申请号：US18662741

申请日：2024-05-13

Applicant: Archer Aviation Inc.

Inventor： Likith MADAMANCHI

IPC: H01M50/342 ,  H01M50/24 ,  H01M50/367 ,  H01M50/509

CPC classification number: H01M50/3425 ,  H01M50/24 ,  H01M50/367 ,  H01M50/509

Abstract: This disclosure relates generally to high voltage power supply (HVPS) systems and battery assemblies for aircraft that use electrical propulsion systems. In one embodiment, an apparatus for safely venting battery cells in thermal runaway is provided. The apparatus includes: a mechanical support layer, the mechanical support layer configured to be attached to a battery assembly; and a vent flap layer attached to the mechanical support layer, the vent flap layer including vent flaps corresponding to battery cells in the battery assembly. Each vent flap includes one or more portions configured to deform to permit flow of gas from the battery cell corresponding to the vent flap.

公开(公告)号：US20240208658A1

公开(公告)日：2024-06-27

申请号：US18599703

申请日：2024-03-08

Applicant: Archer Aviation Inc.

Inventor： Scott GRAVES ,  Alan D. TEPE ,  Robert Wayne MOORE

IPC: B64D27/24 ,  B64C29/00 ,  B64D33/08

CPC classification number: B64D27/24 ,  B64C29/0033 ,  B64D33/08

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.

公开(公告)号：US20240162520A1

公开(公告)日：2024-05-16

申请号：US18460463

申请日：2023-09-01

Applicant: Archer Aviation, Inc.

Inventor： Bharat TULSYAN ,  Weiyu CAO ,  Pablo RAMASWAMY ,  Ryan CHERNIAK ,  Alex CLARABUT

IPC: B64D33/08 ,  B60L50/60 ,  B60L58/26 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6554 ,  H01M10/6556 ,  H01M10/6568 ,  H01M50/204 ,  H01M50/249

CPC classification number: B64D33/08 ,  B60L50/60 ,  B60L58/26 ,  H01M10/613 ,  H01M10/625 ,  H01M10/6554 ,  H01M10/6556 ,  H01M10/6568 ,  H01M50/204 ,  H01M50/249 ,  B60L2200/10 ,  B64C29/0008

Abstract: A cooling system includes a plurality of heat exchanger assemblies corresponding to a plurality of battery packs and a fluid conveyance assembly. Each heat exchanger assembly includes a first heat exchanger inlet-outlet and a second heat exchanger inlet-outlet configured to receive a heat transfer fluid or discharge the heat transfer fluid. The fluid conveyance assembly is coupled to the heat exchanger assemblies and configured to circulate the heat transfer fluid in parallel to the heat exchanger assemblies in a U-flow scheme with an inlet and an outlet of the heat transfer fluid arranged at the same location. The fluid conveyance assembly includes a plurality of flow restrictors configured to balance the heat transfer fluid flowing into the heat exchanger assemblies. The heat transfer fluid flows through the corresponding flow restrictor before flowing into the corresponding heat exchanger assembly of the battery pack.

公开(公告)号：US11975853B2

公开(公告)日：2024-05-07

申请号：US18302285

申请日：2023-04-18

Applicant: Archer Aviation Inc.

Inventor： Scott Graves ,  Alan D. Tepe

IPC: B64D27/24 ,  B64C29/00 ,  B64D33/08

CPC classification number: B64D27/24 ,  B64C29/0033 ,  B64D33/08

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.