Motor wear metric generator

Patent metadata

Field	Value
Publication number	US-2021394933-A1
Application number	US-202117376902-A
Country	US
Kind code	A1
Filing date	Jul 15, 2021
Priority date	Jun 15, 2020
Publication date	Dec 23, 2021
Grant date	—

Abstract

A signal associated with a motor is obtained where the motor is included in a aircraft that has flight capabilities. A motor wear metric that represents an amount of wear experienced by the motor is determined based at least in part on the signal. It is determined, at a flight computer that is included in the aircraft, whether to restrict the flight capabilities of the aircraft based at least in part on the motor wear metric. The flight capabilities of the aircraft are restricted in the event it is so determined.

First claim

What is claimed is:

1 . An aircraft that has flight capabilities, including:
a motor; and a flight computer that is configured to:
obtain a signal associated with the motor;
determine a motor wear metric that represents an amount of wear experienced by the motor based at least in part on the signal;
determine whether to restrict the flight capabilities of the aircraft based at least in part on the motor wear metric; and
restrict the flight capabilities of the aircraft in the event it is determined to restrict the flight capabilities of the aircraft.

2 . The aircraft recited in claim 1 , wherein the signal includes a thrust value generated by the flight computer.

3 . The aircraft recited in claim 1 , wherein the motor wear metric is determined based at least is in part on one or more of the following: a rotational speed associated with the motor, a torque associated with the motor, load information associated with the motor, a temperature associated with the motor, an operational time associated with the motor, an airspeed, an air density, a humidity, an acceleration, or position information associated with the aircraft.

4 . The aircraft recited in claim 1 , wherein the motor wear metric is determined based at least in part on a rotational speed associated with the motor and load information associated with the motor.

5 . The aircraft recited in claim 1 , wherein the motor wear metric is determined based at least in part on a rotational speed associated with the motor and load information associated with the motor, wherein load information includes a direction of load.

6 . The aircraft recited in claim 1 , wherein determining whether to restrict the flight capabilities of the aircraft is further based at least in part on a specified risk tolerance.

7 . The aircraft recited in claim 1 , wherein the flight computer is further configured to: in response to the motor being replaced by a new replacement motor, reset the motor wear metric to an initial value.

8 . The aircraft recited in claim 1 , wherein the flight computer is further configured to: in response to the motor being replaced by a refurbished replacement motor:
generate a new motor wear metric for the refurbished replacement motor, including by performing a health check on the refurbished replacement motor; and reset the motor wear metric to the new motor wear metric.

9 . The aircraft recited in claim 1 further including a numeric display that is configured to display the motor wear metric and that is disposed on an external surface of the aircraft.

10 . The aircraft recited in claim 1 further including a numeric display that is configured to display the motor wear metric and that is disposed on an external surface of the aircraft, including an external surface of a boom that includes the motor.

11 . A method, including:
obtaining a signal associated with a motor, wherein the motor is included in a aircraft that has flight capabilities; determining a motor wear metric that represents an amount of wear experienced by the motor based at least in part on the signal; determining, at a flight computer that is included in the aircraft, whether to restrict the flight capabilities of the aircraft based at least in part on the motor wear metric; and restrict the flight capabilities of the aircraft in the event it is determined to restrict the flight capabilities of the aircraft.

12 . The method recited in claim 11 , wherein the signal includes a thrust value generated by the flight computer.

13 . The method recited in claim 11 , wherein the motor wear metric is determined based at least in part on one or more of the following: a rotational speed associated with the motor, a torque associated with the motor, load information associated with the motor, a temperature associated with the motor, an operational time associated with the motor, an airspeed, an air density, a humidity, an acceleration, or position information associated with the aircraft.

14 . The method recited in claim 11 , wherein the motor wear metric is determined based at least in part on a rotational speed associated with the motor and load information associated with the motor.

15 . The method recited in claim 11 , wherein the motor wear metric is determined based at least in part on a rotational speed associated with the motor and load information associated with the motor, wherein load information includes a direction of load.

16 . The method recited in claim 11 , wherein determining whether to restrict the flight capabilities of the aircraft is further based at least in part on a specified risk tolerance.

17 . The method recited in claim 11 , further including: in response to the motor being replaced by a new replacement motor, resetting the motor wear metric to an initial value.

18 . The method recited in claim 11 , further including: in response to the motor being replaced by a refurbished replacement motor:
generating a new motor wear metric for the refurbished replacement motor, including by performing a health check on the refurbished replacement motor; and resetting the motor wear metric to the new motor wear metric.

19 . The method recited in claim 11 , further including: displaying, via a numeric display included in the aircraft, the motor wear metric, wherein the numeric display is disposed on an external surface of the aircraft.

20 . The method recited in claim 11 , further including: displaying, via a numeric display included in the aircraft, the motor wear metric, wherein the numeric display is disposed on an external surface of the aircraft, including an external surface of a boom that includes the motor.

Assignees

• Kitty Hawk Corp

Inventors

• Kwon Dennis Young
• Selwa Alexander David

Classifications

• B64U50/19

  using electrically powered motors · CPC title

• B64F5/60 Primary

  Testing or inspecting aircraft components or systems · CPC title

• G07C5/0808 Primary

  Diagnosing performance data (testing of vehicles G01M17/00; testing of electrical installation on vehicles G01R31/005) · CPC title

• G07C5/0816

  Indicating performance data, e.g. occurrence of a malfunction · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title