Yaw moment supplement for directional control

Patent metadata

Field	Value
Publication number	US-10407166-B2
Application number	US-201815864702-A
Country	US
Kind code	B2
Filing date	Jan 8, 2018
Priority date	Jan 8, 2018
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

A rotor system of an aircraft includes a rotor hub rotatable about an axis of rotation, and a power generation system. The power generation system includes a generator stator and a generator rotor. The generator rotor is coupled to the rotor hub. At least one induction type magnet is mounted to at least one of the generator stator and the generator rotor. A control unit is operably coupled to the at least one induction type magnet to selectively deliver power to the at least one induction type magnet to alter a torque of the rotor hub without decreasing a rotational speed of the rotor hub.

First claim

What is claimed is:

1. A rotor system of an aircraft comprising:
a rotor hub rotatable about an axis of rotation;
a power generation system including:
a generator stator and a generator rotor, the generator rotor being coupled to the rotor hub;
at least one induction type magnet mounted to at least one of the generator stator and the generator rotor; and
a control unit operably coupled to at least one induction type magnet to selectively deliver power to the at least one induction type magnet to alter a torque of the rotor hub without decreasing a rotational speed of the rotor hub.

2. The rotor system of claim 1 , wherein the power generation system is driven by the rotor hub in a first mode of operation and the rotor hub is driven at least partly by the power generation system in a second mode of operation.

3. The rotor system of claim 2 , wherein the power generation system further comprises an energy storage device operably coupled to the at least one induction type magnet, and in the first mode, power is stored within the energy storage device.

4. The rotor system of claim 2 , wherein in the first mode, power is not provided to the at least one induction type magnet.

5. The rotor system of claim 2 , wherein in the second mode of operation, the control unit selectively delivers power from the energy storage device to the at least one induction type magnet to control the torque of the rotor hub.

6. The rotor system of claim 2 , wherein in the second mode of operation, the aircraft is in autorotation.

7. The rotor system of claim 1 , wherein control of the torque of the rotor hub provides yaw control to the aircraft.

8. The rotor system of claim 1 , wherein the rotor system is one of a plurality of rotor systems of the aircraft.

9. The rotor system of claim 8 , wherein the rotor system is one of an upper rotor system and a lower rotor system of a coaxial main rotor system.

10. The rotor system of claim 8 , wherein the aircraft is a distributed propulsion aircraft.

11. The rotor system of claim 1 , wherein the power generation system is disposed adjacent an outboard end of the rotor hub.

12. The method of claim 11 , wherein the rotor system is one of a plurality of rotor systems of the aircraft.

13. The method of claim 12 , wherein the rotor system is one of an upper rotor system and a lower rotor system of a coaxial main rotor system.

14. The method of claim 12 , wherein the aircraft is a distributed propulsion aircraft.

15. A method of operating an aircraft comprising:
rotating a rotor system of the aircraft about an axis of rotation;
applying power, via a control unit, to at least one induction type magnet of a power generation system coupled to the rotor system; and
adjusting a torque of the rotor hub without decreasing a rotational speed of the rotor hub.

16. The method of claim 15 , wherein adjusting the torque of the rotor hub provides directional control to the aircraft.

17. The method of claim 16 , wherein the directional control includes yaw control.

18. The method of claim 15 , wherein applying power through the control unit to at least one induction type magnet further comprises modulating the power applied to the at least one induction type magnet.

19. The method of claim 15 , wherein adjusting the torque of the rotor hub comprises increasing the torque of the rotor hub.

20. The method of claim 15 , wherein adjusting the torque of the rotor hub comprises decreasing the torque of the rotor hub.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Lauder Timothy F

Classifications

• B64C27/14 Primary

  Direct drive between power plant and rotor hub · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• H02K11/0094

  Structural association with other electrical or electronic devices · CPC title

• B64C27/32

  Rotors · CPC title

• H02K16/04

  Machines with one rotor and two stators · CPC title