公开(公告)号：US11945594B2

公开(公告)日：2024-04-02

申请号：US18357055

申请日：2023-07-21

Applicant: Archer Aviation, Inc.

Inventor： John Melack

IPC: B64D27/24 ,  B64C29/00

CPC classification number: B64D27/24 ,  B64C29/0033 ,  B64D2221/00

Abstract: 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.

公开(公告)号：US11901795B1

公开(公告)日：2024-02-13

申请号：US18316931

申请日：2023-05-12

Applicant: ARCHER AVIATION, INC.

Inventor： Scott Graves ,  Diego Silva

IPC: H02K7/00 ,  H02K1/27 ,  B64D27/24 ,  H02K1/32 ,  H02K15/03 ,  B64C29/00

CPC classification number: H02K7/006 ,  B64C29/0033 ,  B64D27/24 ,  H02K1/27 ,  H02K1/32 ,  H02K15/03

Abstract: 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.

公开(公告)号：US11827349B1

公开(公告)日：2023-11-28

申请号：US18324702

申请日：2023-05-26

Applicant: ARCHER AVIATION, INC.

Inventor： Kerry Manning ,  Nathan Storrs ,  Scott Graves

IPC: B64C29/00 ,  B64D27/26 ,  B64D27/24 ,  B64C11/02

CPC classification number: B64C29/0033 ,  B64C11/02 ,  B64D27/24 ,  B64D27/26

Abstract: A VTOL aircraft includes a lift propeller configured to provide lift during takeoff, landing and hover operations. The lift propeller is configured to be stowed close to a boom surface when not in use during, e.g., cruise flight, to minimize drag around propeller surfaces. The lift propeller may be displaced vertically with respect to the boom when switching to a lift configuration to provide greater separation from the boom to improve lift efficiency and reduce unwanted vibrations. The lift propeller may have a fail-safe configuration that allows the propeller to move passively between lift and stowed configurations, and to fully rotate even when fully retracted.

公开(公告)号：US11820523B1

公开(公告)日：2023-11-21

申请号：US18298548

申请日：2023-04-11

Applicant: Archer Aviation Inc.

Inventor： Scott Graves

IPC: B64D27/24 ,  B64D35/00 ,  B64C29/00 ,  B64C11/00 ,  B64D35/02 ,  H02K7/00

CPC classification number: B64D27/24 ,  B64C29/0033 ,  B64D35/02 ,  H02K7/006

Abstract: 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.

公开(公告)号：US11465532B2

公开(公告)日：2022-10-11

申请号：US17156047

申请日：2021-01-22

Applicant: Archer Aviation, Inc.

Inventor： Diederik Marius

IPC: B60L58/18 ,  B60L50/60 ,  B60L58/12 ,  B64C27/52 ,  B64C27/32 ,  B64C27/24 ,  B64D31/00 ,  H02J4/00 ,  H02J7/00 ,  H02J7/34 ,  B64D27/24

Abstract: A power distribution system for an electric aircraft includes a first electric propulsion unit comprising at least two power stages; a first battery pack electrically connected to a first power stage of the at least two power stages; a second battery pack electrically connected to a second power stage of the at least two power stages; and a control system configured to control the first battery pack, the second battery pack, the first power stage, and the second power stage to transfer power from the first battery pack to the second battery pack through the first power stage and the second power stage.

公开(公告)号：US20220234470A1

公开(公告)日：2022-07-28

申请号：US17156047

申请日：2021-01-22

Applicant: Archer Aviation, Inc.

Inventor： Diederik MARIUS

IPC: B60L58/18 ,  H02J4/00 ,  H02J7/00 ,  H02J7/34 ,  B64D27/24 ,  B64D31/00 ,  B60L50/60 ,  B64C27/52 ,  B64C27/32 ,  B60L58/12

Abstract: A power distribution system for an electric aircraft includes a first electric propulsion unit comprising at least two power stages; a first battery pack electrically connected to a first power stage of the at least two power stages; a second battery pack electrically connected to a second power stage of the at least two power stages; and a control system configured to control the first battery pack, the second battery pack, the first power stage, and the second power stage to transfer power from the first battery pack to the second battery pack through the first power stage and the second power stage.

公开(公告)号：US20250042544A1

公开(公告)日：2025-02-06

申请号：US18477220

申请日：2023-09-28

Applicant: Archer Aviation Inc.

Inventor： Kerry MANNING ,  Nathan STORRS ,  Scott GRAVES

IPC: B64C29/00 ,  B64C11/02 ,  B64D27/24 ,  B64D27/40

Abstract: A VTOL aircraft includes a lift propeller configured to provide lift during takeoff, landing and hover operations. The lift propeller is configured to be stowed close to a boom surface when not in use during, e.g., cruise flight, to minimize drag around propeller surfaces. The lift propeller may be displaced vertically with respect to the boom when switching to a lift configuration to provide greater separation from the boom to improve lift efficiency and reduce unwanted vibrations. The lift propeller may have a fail-safe configuration that allows the propeller to move passively between lift and stowed configurations, and to fully rotate even when fully retracted.

公开(公告)号：US12214894B1

公开(公告)日：2025-02-04

申请号：US18667065

申请日：2024-05-17

Applicant: Archer Aviation Inc.

Inventor： Scott Graves

IPC: F16H3/091 ,  B64C29/00 ,  B64D27/33 ,  B64D35/021

Abstract: A motor gearbox assembly for an aircraft may comprise a layshaft configured to transmit torque from a rotor to a main power output shaft. The motor gearbox assembly may comprise a gearbox housing, a stator mounted inside the gearbox housing, a rotor rotatably mounted inside the stator on a main power output shaft and a layshaft rotatably mounted in the gearbox housing outside of the stator. The motor gearbox assembly may comprise a first ear reduction between the rotor and the layshaft, and a second gear reduction between the layshaft and the main power output shaft.

公开(公告)号：US12205484B1

公开(公告)日：2025-01-21

申请号：US18451055

申请日：2023-08-16

Applicant: Archer Aviation, Inc.

Inventor： Anthony Hunter ,  Timothy Mclain ,  Joshua Mangelson ,  Gary Long ,  Pablo Hopman ,  Siddhartha Kumar ,  David Christopher Akagi ,  Kalliyan Velasco

IPC: G08G5/02 ,  G06V10/10 ,  G08G5/00

Abstract: Systems and methods of providing guidance to assist eVTOL aerial vehicles in performing landing and takeoff operations at landing locations in GPS-denied environments are disclosed. An exemplary system includes an aerial vehicle comprising a camera configured to generate images based on information transmitted by a plurality of light sources located adjacent a landing surface for the aerial vehicle and a controller circuit configured to receive the generated images and determine a position and an orientation of the aerial vehicle based on the received images, wherein the light sources are arranged in a predetermined pattern on the landing surface, and wherein a characteristic of light emitted from each of the light sources is modulated with respect to time.

公开(公告)号：US12176697B2

公开(公告)日：2024-12-24

申请号：US18189537

申请日：2023-03-24

Applicant: ARCHER AVIATION, INC.

Inventor： Michael Mauger ,  Simon Saenz Llano ,  Naishadh Vasjaliya ,  Sonny Pilger ,  Adam Ziemba ,  Pedro Carleial ,  Andrija Bajovic

IPC: H02G3/22 ,  B64C3/18 ,  B64F5/10 ,  B64C29/00

Abstract: The embodiments of the present disclosure provide an aircraft assembly. The aircraft assembly includes an aircraft structure comprising a component with a plurality of wire openings. A plurality of high voltage wires are disposed in the wire openings in the component such that each wire opening receives one high voltage wire, and the each wire opening has an opening size larger than a size of the one high voltage wire, the opening size being smaller than a size of a connector attached to an end of the one high voltage wire. The high voltage wires are installed in the wire openings before curing the aircraft structure.