Unmanned aerial vehicle hybrid rotor drive

Patent metadata

Field	Value
Publication number	US-9637227-B2
Application number	US-201514855448-A
Country	US
Kind code	B2
Filing date	Sep 16, 2015
Priority date	Sep 16, 2015
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

Devices, methods, and systems of various embodiments are disclosed including an unmanned aerial vehicle (UAV) having a hybrid rotor drive system. The UAV may include a frame, a primary rotor, a plurality of auxiliary rotors, a battery, and a processor coupled to the battery and the auxiliary rotors. The primary rotor may be configured to generate thrust with a downwash of air. The plurality of auxiliary rotors may each be at least partially disposed in the downwash of air generated by the primary rotor. The plurality of auxiliary rotors may be configured to be able to harvest energy from the downwash of air. The battery may be configured to store at least some of the energy harvested from the downwash of air by the plurality of auxiliary rotors. The processor may be configured with processor-executable instructions to utilize the plurality of auxiliary rotors to provide flight control for the UAV.

First claim

What is claimed is:

1. An unmanned aerial vehicle (UAV), comprising:
a frame;
a primary rotor supported by the frame and configured to generate thrust with a downwash of air;
a plurality of auxiliary rotors supported by the frame to each at least partially be disposed in the downwash of air generated by the primary rotor, wherein the plurality of auxiliary rotors are configured to harvest energy from the downwash of air;
a battery configured to store at least some of the energy harvested from the downwash of air by the plurality of auxiliary rotors; and
a processor coupled to the plurality of auxiliary rotors and the battery, wherein the processor is configured with processor-executable instructions to utilize the plurality of auxiliary rotors to provide flight control for the UAV.

2. The UAV of claim 1 , wherein the processor is further configured with the processor-executable instructions to:
control an amount of energy harvested by selected ones of the plurality of auxiliary rotors as part of implementing flight control parameters that provide the flight control for the UAV.

3. The UAV of claim 2 , wherein the processor is further configured with the processor-executable instructions to:
receive a flight control input;
determine the flight control parameters for the UAV based on the flight control input.

4. The UAV of claim 2 , wherein the processor is further configured with the processor-executable instructions such that the control of the amount of energy harvested by the selected ones of the plurality of auxiliary rotors includes harvesting different amounts of energy from at least two of the plurality of auxiliary rotors.

5. The UAV of claim 1 , further comprising:
a plurality of auxiliary motors each coupled to a respective auxiliary rotor of the plurality of auxiliary rotors, wherein each of the plurality of auxiliary motors includes a pulse width modulation circuit configured to selectively couple windings of a respective auxiliary motor of the plurality of auxiliary motors to the battery in order to adjust an amount of energy harvested by the respective auxiliary rotor or an amount of power drawn from the battery to generate auxiliary thrust by the respective auxiliary rotor.

6. The UAV of claim 1 further comprising:
a plurality of auxiliary motors each coupled to a respective auxiliary rotor of the plurality of auxiliary rotors, wherein each of the plurality of auxiliary motors includes a first set of metal-oxide semiconductor field-effect transistors (MOSFETs) and a second set of MOSFETs,
wherein the processor is further configured with the processor-executable instructions to:
control the first and second sets of MOSFETS differently in order to adjust an amount of energy harvested by the respective auxiliary rotor or an amount of power drawn from the battery to generate auxiliary thrust by the respective auxiliary rotor.

7. The UAV of claim 1 , wherein the processor is further configured with the processor-executable instructions to:
connect the battery to selected ones of the plurality of auxiliary rotors in order to generate auxiliary thrust to provide at least part of the flight control for the UAV.

8. The UAV of claim 1 , wherein the processor is further configured with the processor-executable instructions to:
connect the battery selectively to each of the plurality of auxiliary rotors to generate sufficient auxiliary thrust to land the UAV without propulsion from the primary rotor.

9. The UAV of claim 1 , wherein the processor is further configured with the processor-executable instructions to:
connect the battery selectively to each of the plurality of auxiliary rotors to generate sufficient auxiliary thrust to enable take off without propulsion from the primary rotor.

10. The UAV of claim 1 , wherein the processor is further configured with the processor-executable instructions to:
implement flight control parameters that provide the flight control by:
controlling an amount of energy harvested by a first one of the plurality of auxiliary rotors; and
connecting the battery to a second one of the plurality of auxiliary rotors to generate auxiliary thrust for propulsion of the UAV.

11. The UAV of claim 1 , further comprising:
a dump resistor electrically coupled to the plurality of auxiliary rotors via a switch coupled to the processor and configured to dissipate energy harvested by one or more auxiliary rotors in response to a signal received from the processor.

12. The UAV of claim 1 , wherein each of the plurality of auxiliary rotors are movable along a separate radially extending track secured to the frame, wherein movement of each of the plurality of auxiliary rotors along the separate radially extending track varies how much of each of the plurality of auxiliary rotors is disposed in the downwash of air.

13. The UAV of claim 1 , wherein the processor is further configured with the processor-executable instructions to:
adjust an adjustable throttle setting that controls the primary rotor.

14. The UAV of claim 1 , wherein the primary rotor is powered by an internal combustion engine.

15. The UAV of claim 1 , wherein the plurality of auxiliary rotors are equally spaced away from a rotational axis of the primary rotor.

16. The UAV of claim 1 , wherein the plurality of auxiliary rotors includes at least four auxiliary rotors.

17. A method of operating an unmanned aerial vehicle (UAV) comprising a primary rotor, a plurality of auxiliary rotors configured to be able to harvest energy from a downwash of air generated by the primary rotor, and a battery configured to store at least some of the energy harvested by the plurality of auxiliary rotors, the method comprising:
receiving a flight control input;
determining flight control parameters that provide flight control for the UAV based on the flight control input; and
controlling an amount of energy harvested by selected ones of the plurality of auxiliary rotors as part of implementing the determined flight control parameters.

18. The method of claim 17 , wherein controlling the amount of energy harvested by selected ones of the plurality of auxiliary rotors includes harvesting different amounts of energy from at least two of the plurality of auxiliary rotors.

19. The method of claim 17 , wherein each of the plurality of auxiliary rotors is coupled to a respective auxiliary motor of a plurality of auxiliary motors, wherein controlling the amount of energy harvested by selected ones of the plurality of auxiliary rotors comprises:
selectively coupling windings of the respective auxiliary motor to the battery in order to adjust the amount of energy harvested by selected ones of the plurality of auxiliary rotors or an amount of power drawn from the battery to generate auxiliary thrust by a select one of the plurality of auxiliary rotors.

20. The method of claim 17 , wherein controlling the amount of energy harvested by selected ones of the plurality of auxiliary rotors comprises:
controlling first and second sets of metal-oxide semiconductor field-effect transistors (MOSFETs) differently in order to adjust the amount of energy harvested by an individual one of the plurality of auxiliary rotors or an amount of power drawn from the battery to generate auxiliary thrust by the individual one of the plurality of auxiliary rotors.

21. The method of claim 17 , further comprising:
connecting the battery to selected ones of the plurality of auxiliary rotors in order to generate auxiliary thrust to provi

Assignees

• Qualcomm Inc

Inventors

• Von Novak William Henry
• Irish Linda Stacey

Classifications

• B64C19/00 Primary

  Aircraft control not otherwise provided for · CPC title

• H02P3/12

  by short-circuit or resistive braking · CPC title

• H02K7/1823 Primary

  structurally associated with turbines or similar engines · CPC title

• B64U2201/00

  UAVs characterised by their flight controls · CPC title

• B64U50/19

  using electrically powered motors · CPC title