Peak power use with pilot monitoring
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.
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.