公开(公告)号：US12107459B2

公开(公告)日：2024-10-01

申请号：US17704798

申请日：2022-03-25

Applicant: BETA AIR, LLC

Inventor： Manon Danielle Belzile ,  Kyle B. Clark ,  Stephen Widdis

IPC: H02K1/30 ,  B64C29/00 ,  B64D27/24 ,  B64D33/08 ,  H02K1/278 ,  H02K9/06 ,  H02K21/16

CPC classification number: H02K1/30 ,  B64D27/24 ,  B64D33/08 ,  H02K1/278 ,  H02K9/06 ,  H02K21/16 ,  B64C29/00

Abstract: A rotor for a motor of an electric aircraft is provided. The rotor may include a hub, which includes a plurality of magnets fixed to an inner surface of the hub that are configured to interact with a stator of the motor to rotate rotor. The rotor also includes redial spokes that extend from the hub and provide structural support to the rotor. The rotor may also include a hoop, which provides balance for rotor during operation of motor and may include an integrated fan that provides cooling to various components of the motor.

公开(公告)号：US20200307390A1

公开(公告)日：2020-10-01

申请号：US16363711

申请日：2019-03-25

Applicant: BETA AIR LLC

Inventor： Kyle B. Clark ,  Herman Wiegman

IPC: B60L15/20 ,  B64D31/00 ,  B64D27/24 ,  B60L58/12

Abstract: A system for maintaining attitude control under degraded or depleted energy source conditions using multiple electric propulsors includes a plurality of propulsors, at least an energy source providing electric power to the plurality of propulsors and a vehicle controller communicatively coupled to each propulsor and configured to calculate initial power levels for the plurality of propulsors, the initial power levels including an initial power level for each propulsor, determine an energy output capacity of the least an energy source under load, calculate, by the vehicle controller, an aggregate potential demand of the plurality of propulsors as a function of the initial power levels, determine that electric potential is insufficient to match the aggregate potential demand, and for each initial power level generate a reduced power level, the reduced power level less than the initial power level and direct a corresponding propulsor to consume electrical power at the reduced power level.

公开(公告)号：US20230356837A1

公开(公告)日：2023-11-09

申请号：US17736357

申请日：2022-05-04

Applicant: BETA AIR, LLC

Inventor： Kyle B. Clark

IPC: B64D45/04 ,  B64D27/24 ,  B64C29/00

CPC classification number: B64C29/0025 ,  B64D27/24 ,  B64D45/04

Abstract: In an aspect the present disclosure is directed to an electric aircraft. An electric aircraft may include a plurality of fixed wings, a tail, a first boom, and a second boom and a plurality of lift components. The aircraft also includes a tail affixed to the aft end of the fuselage, a first boom including a first rear end affixed to the tail and a first forward end proximal to the fore end of the fuselage, wherein the first boom is affixed to a first wing, a second boom including a second rear end affixed to the tail and a second forward end proximal to the fore end of the fuselage, wherein the second boom is affixed to the second wing. The aircraft may include a plurality of lift components which may be affixed to the booms.

公开(公告)号：US20230307972A1

公开(公告)日：2023-09-28

申请号：US17704798

申请日：2022-03-25

Applicant: BETA AIR, LLC

Inventor： Manon Danielle Belzile ,  Kyle B. Clark ,  Stephen Widdis

IPC: H02K1/30 ,  H02K1/278 ,  H02K9/06 ,  H02K21/16 ,  B64D27/24 ,  B64D33/08

CPC classification number: H02K1/30 ,  H02K1/278 ,  H02K9/06 ,  H02K21/16 ,  B64D27/24 ,  B64D33/08 ,  B64C29/00

Abstract: A rotor for a motor of an electric aircraft is provided. The rotor may include a hub, which includes a plurality of magnets fixed to an inner surface of the hub that are configured to interact with a stator of the motor to rotate rotor. The rotor also includes redial spokes that extend from the hub and provide structural support to the rotor. The rotor may also include a hoop, which provides balance for rotor during operation of motor and may include an integrated fan that provides cooling to various components of the motor.

公开(公告)号：US11753152B2

公开(公告)日：2023-09-12

申请号：US17552512

申请日：2021-12-16

Applicant: BETA AIR, LLC

Inventor： Riley Clinton Griffin ,  Kyle B. Clark ,  Raffaello Verna

IPC: B64C25/52 ,  B64C25/62 ,  B64C25/66

CPC classification number: B64C25/52 ,  B64C25/62 ,  B64C25/66

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

公开(公告)号：US11685533B2

公开(公告)日：2023-06-27

申请号：US17404886

申请日：2021-08-17

Applicant: BETA AIR, LLC

Inventor： Kyle B. Clark ,  Riley Griffin ,  Augustus Brightman ,  Steven Arms ,  Herman Wiegman

IPC: B64D15/02 ,  B64C29/00 ,  H02K1/22

CPC classification number: B64D15/02 ,  B64C29/0016 ,  H02K1/22

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

公开(公告)号：US20200031478A1

公开(公告)日：2020-01-30

申请号：US16427298

申请日：2019-05-30

Applicant: BETA AIR LLC

Inventor： Kyle B. Clark ,  Martine Rothblatt ,  Riley Griffin ,  Augustus Brightman ,  Steven Arms ,  Herman Wiegman

IPC: B64D15/02 ,  H02K1/22 ,  B64C29/00

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

公开(公告)号：US12054239B2

公开(公告)日：2024-08-06

申请号：US17404809

申请日：2021-08-17

Applicant: BETA AIR, LLC

Inventor： Kyle B. Clark

IPC: B64C13/16 ,  B64C13/04 ,  B64D27/24 ,  G05D1/00 ,  G06N20/00

CPC classification number: B64C13/16 ,  B64C13/04 ,  B64D27/24 ,  G05D1/0016 ,  G06N20/00

Abstract: A system for in-flight stabilization including a plurality if flight components mechanically coupled to an aircraft. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure datum of the flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of a flight component of the aircraft from the sensor, generate a mitigating response to be performed by at least a flight component of the plurality of flight components, and initiate the at least a flight component of the plurality of flight components. Initiating the flight component of the plurality of flight components further includes performing the mitigating response.

公开(公告)号：US20230143459A1

公开(公告)日：2023-05-11

申请号：US17736341

申请日：2022-05-04

Applicant: BETA AIR, LLC

Inventor： Kyle B. Clark

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

CPC classification number: B64C29/0025 ,  B64D27/24 ,  B64D27/26

Abstract: In an aspect the current disclosure is directed to an electric aircraft, wherein the electric aircraft is comprised of a plurality of flight components and a flight controller. A plurality of flight components is comprised of a plurality of control surfaces, a plurality of lift propulsors, at least a thrust propulsor, and a plurality of electric motors configured to power the plurality of propulsors. The flight controller is communicatively connected to a pilot input and flight components. The flight controller is configured to receive control datum from a pilot input and generate an output datum as a function of the control datum.

公开(公告)号：US20230002034A1

公开(公告)日：2023-01-05

申请号：US17365419

申请日：2021-07-01

Applicant: BETA AIR, LLC

Inventor： Kyle B. Clark

IPC: B64C13/04 ,  B64D27/24 ,  B64C11/00 ,  B64C29/00 ,  B60L50/60 ,  B64C5/06 ,  G05D1/10

Abstract: In an aspect, a system for fixed-pitch lift configured for use in an electric aircraft includes a plurality of flight components mechanically coupled thereto, each configured to provide lift to the electric aircraft. The electric aircraft also includes a first pusher mechanically coupled to a first owing of the electric aircraft, wherein the first pusher is configured to provide forward flight to the electric aircraft, a second pusher mechanically coupled to a second wing of the electric aircraft, wherein the second pusher is configured to provide forward flight to the electric aircraft as well, a sensor that is configured to detect vertical lift and forward flight from a pilot control and generate a command datum, as a function of the pilot control, a flight controller which may include a computing device configured to receive the command datum and direct the electric aircraft, as a function of the command datum.