FLIGHT CONTROLLER WITH GENERATOR CONTROL

• US 20160280386A1
• Filed: 03/24/2016
• Published: 09/29/2016
• Est. Priority Date: 03/25/2015
• Status: Active Grant

• Current Assignee: SkyFront Corp.
• Original Assignee: SkyFront Corp.
• Inventors: Mestler, Troy, Stepanov, Anton
• Granted Patent: US 10,144,527 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 31/06 actuated automatically
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/30 Supply or distribution of electrical power
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A flight controller system includes an electronic speed control throttle input from which an anticipated electrical power demand is determined. The flight controller system includes a controller that determines a throttle input for a generator in order to satisfy the anticipated electrical power demand. The flight controller system includes an electronic speed control throttle output providing a delayed electronic speed control throttle signal.

Claims

1. A flight controller system, comprising:

an electronic speed control throttle input from which an anticipated electrical power demand is determined;

a controller that determines a throttle input for a generator in order to satisfy the anticipated electrical power demand; and

an electronic speed control throttle output providing a delayed electronic speed control throttle signal.

2. The system of claim 1, wherein the delayed electronic speed control throttle signal corresponds to a power output delay of the generator in response to the throttle input for the generator.

3. The system of claim 1, wherein the flight controller system is included in a multirotor aircraft.

4. The system of claim 1, wherein the throttle input for the generator is an engine throttle is input.

5. The system of claim 1, wherein the delayed electronic speed control throttle signal is delayed with respect to setting of the generator to the determined throttle input.

6. The system of claim 1, wherein a rate of change of an electronic speed control throttle signal setting in the delayed electronic speed control throttle signal has been altered to be limited by a maximum rate of change.

7. The system of claim 1, wherein the electronic speed control throttle input was determined based at least in part on a pilot control command indicating a desired flight control.

8. The system of claim 1, wherein the anticipated electrical power demand was determined based at least in part using a power prediction model for an aircraft that takes into account detected states of the aircraft.

9. The system of claim 1, wherein the throttle input was determined based at least in part on current engine RPM and one or more fuel system measurements of an engine of the generator.

10. The system of claim 1, wherein the throttle input is limited by a maximum limit that is less than a maximum throttle of the generator.

11. The system of claim 1, wherein the throttle input has been determined to be greater than a minimum throttle input required to satisfy the anticipated electrical power demand. s 12. The system of claim 1, wherein a motor of the delayed electronic speed control throttle signal is powered without a use of a battery.

13. The system of claim 1, further comprising a backup battery configured to be utilized in the event the generator becomes not functional.

14. The system of claim 1, wherein engine RPM of an engine of the generator is increased and the throttle input for the generator is decreased while maintaining a substantially constant generator power output.

15. The system of claim 1, wherein the throttle input for the generator is adjusted based on detected electrical output feedback.

16. The system of claim 1, wherein the delayed electronic speed control throttle signal was is generated in response to a determination that the anticipated electrical power demand is greater than a current electrical power demand by at least a threshold amount.

17. The system of claim 1, wherein the delayed electronic speed control throttle signal was delayed in response to a determination that a battery is not fully functional.

18. The system of claim 1, wherein in response to a determination that additional power is not available, an altitude control power budget is reduced and an attitude control power budget is increased within a constant total power budget of power provided by the generator.

19. A method, comprising:

determining using an electronic speed control throttle input, an anticipated electrical power demand;

determining using a flight controller a throttle input for a generator in order to satisfy the anticipated electrical power demand; and

providing via the flight controller a delayed electronic speed control throttle signal.

20. A flight controller system, comprising:

an electronic speed control throttle input from which an anticipated electrical power demand is determined;

a controller that determines a throttle input for a generator in order to satisfy the anticipated electrical power demand; and

an electronic speed control throttle output providing a modified electronic speed control throttle signal, wherein a rate of change of an electronic speed control throttle signal setting in the modified electronic speed control throttle signal has been limited by a maximum rate of change.