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US 11,691,744 B1Granted
Dual-motor propulsion assembly
AssigneeBeta Air, LLC
InventorJeffrey K. Petter
Life of this patent
Estimating the term…
Abstract
Provided in this disclosure is a dual-motor propulsion assembly, and corresponding methods of operation, that is configured for use in an electric aircraft. Dual-motor propulsion assembly provides redundant systems by including vertically stack motors, where one motor powers a propulsor of the assembly if the other motor malfunctions or becomes inoperative.
Claims19
A dual-motor propulsion system of an electric aircraft, the system comprising:
- a flight component attached to an electric aircraft, wherein the flight component is configured to maneuver the electric aircraft through a fluid medium;
- a first motor and a second motor arranged in a vertically stacked configuration, wherein:
- each of the first motor and the second motor is selectively mechanically connected to the flight component via a shaft and configured to provide motive power to the flight component;
- and
- the second motor is configured to provide motive power to the flight component if the first motor is inoperative;
- a shaft extending through each of the first motor and the second motor in the vertically stacked configuration;
- a plurality of sensors comprising a redundant sensor arrangement, wherein the redundant sensor arrangement is communicatively connected to the first motor and the second motor, wherein the redundant sensor arrangement comprises a first sensor and a second sensor, respectively, wherein the first sensor and the second sensor are configured to measure a same characteristic of the first motor and second motor, respectively, and wherein the redundant sensor arrangement is configured to:
- detect that the first motor is inoperative;
- and
- generate a failure datum corresponding to the inoperativeness of the first motor;
- and
- a controller communicatively connected to at least the redundant sensor arrangement and each of the first motor and the second motor, wherein the controller is configured to:
- receive the failure datum from the redundant sensor arrangement;
- and
- generate at least a command to the first motor and the second motor as a function of the failure datum.
12 more elements
A method of use of a dual-motor propulsion system in an electric aircraft, the method comprising:
- providing, using a first motor and a second motor arranged in a vertically stacked configuration and a shaft extending through each of the first motor and the second motor in the vertically stacked configuration, motive power to a flight component attached to an electric aircraft, wherein each of the first motor and the second motor is selectively mechanically connected to the flight component via a shaft;
- maneuvering, using the flight component, the electric aircraft;
- providing, using the second motor, motive power to the flight component if the first motor is inoperative;
- detecting, by a redundant sensor arrangement of a plurality of sensors, that the first motor is inoperative, wherein the redundant sensor arrangement is communicatively connected to the first motor and the second motor and comprises a first sensor and a second sensor, wherein both the first sensor and the sensor are configured to measure a same characteristic of the first motor and the second motor, respectively;
- generating, by the redundant sensor arrangement, a failure datum corresponding to the inoperativeness of the first motor;
- receiving, by a controller communicatively connected to at least the redundant sensor arrangement and each of the first motor and the second motor, the failure datum from the redundant sensor arrangement;
- and
- generating, by the controller, at least a command to the first motor and the second motor as a function of the failure datum.
5 more elements
Dependencies are inferred from the claim text.