Peak power use with pilot monitoring

Patent metadata

Field	Value
Publication number	US-10933980-B2
Application number	US-201816054027-A
Country	US
Kind code	B2
Filing date	Aug 3, 2018
Priority date	Aug 3, 2018
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

First claim

What is claimed is:

1. An aircraft, comprising:
an electric propulsion system comprising an electric power source and an electric motor coupled to a rotor, the electric motor comprising a motor temperature sensor arranged to measure a temperature of the electric motor;
an electric power monitoring system comprising a controller connected to the electric motor; and
an instrument electronically connected to the electric motor, the instrument configured to communicate a time available value before a motor temperature measured by the motor temperature sensor will reach a motor temperature limit.

2. The aircraft of claim 1 , wherein the instrument is configured to display the time available value on a countdown timer.

3. The aircraft of claim 1 , wherein the instrument is configured to audibly announce the time available value.

4. The aircraft of claim 1 , wherein the instrument is configured to communicate the time available value when the motor temperature reaches a motor temperature trigger limit.

5. The aircraft of claim 1 , wherein the instrument is configured to graphically display the motor temperature relative to the motor temperature limit.

6. The aircraft of claim 1 , wherein the motor temperature limit is a high temperature limit of the electric motor.

7. The aircraft of claim 1 , wherein the instrument is configured to display the time available value on a countdown timer and to audibly announce the time available value.

8. The aircraft of claim 1 , wherein the instrument is configured to display the time available value on a countdown timer when the motor temperature reaches a motor temperature trigger limit.

9. The aircraft of claim 1 , wherein the instrument is configured to display the time available value on a countdown timer; and
the instrument is configured to graphically display the motor temperature relative to the motor temperature limit.

10. The aircraft of claim 9 , wherein the rotor is an anti-torque rotor; and
further comprising an engine to drive a main rotor through a transmission.

11. The aircraft of claim 1 , wherein the instrument is configured to display the time available value on a countdown timer when the motor temperature reaches a motor temperature trigger limit; and
the instrument is configured to graphically display the motor temperature relative to the motor temperature limit.

12. The aircraft of claim 1 , wherein the aircraft is a helicopter and the rotor is a tail rotor and further comprising:
an engine driving a main rotor through a transmission; and
the electric power source coupled to the transmission.

13. A method, comprising:
measuring, during flight of an aircraft, a winding temperature of an electric motor that is driving a rotor;
communicating the measured winding temperature to a pilot during flight of the aircraft;
determining a time available value before the measured winding temperature reaches a motor temperature limit; and
communicating to the pilot the time available value.

14. The method of claim 13 , wherein the communicating the time available value occurs when the measured winding temperature reaches a trigger limit.

15. The method of claim 13 , wherein the communicating the time available value comprises displaying a countdown timer.

16. The method of claim 13 , wherein the communicating the measured winding temperature comprises graphically displaying the measured winding temperature relative to the motor temperature limit.

17. The method of claim 13 , wherein the communicating the measured winding temperature comprises graphically displaying the measured winding temperature relative to the motor temperature limit; and
the communicating the time available value comprises displaying a countdown timer.

18. The method of claim 17 , wherein the communicating the time available value occurs when the measured winding temperature reaches a trigger limit.

19. The method of claim 13 , wherein the aircraft is a helicopter and the rotor is an anti-torque rotor; and
the motor temperature limit is a high temperature limit, and further comprising:
an engine driving a main rotor.

20. The method of claim 19 , wherein the communicating the time available value occurs when the measured winding temperature reaches a trigger limit.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Sinusas Eric Albert
• Lambert Edward
• Lavallee Yann
• Acee Aaron Alexander
• Brand Albert G

Classifications

• B64U30/20

  Rotors; Rotor supports · CPC title

• B64D31/06

  actuated automatically · CPC title

• B64C19/02 Primary

  Conjoint controls · CPC title

• B64C27/006 Primary

  Safety devices · CPC title

• B64U10/17

  Helicopters (flying platforms B64U10/13) · CPC title