Rotor drive systems for rotorcraft

Patent metadata

Field	Value
Publication number	US-9828089-B2
Application number	US-201615010970-A
Country	US
Kind code	B2
Filing date	Jan 29, 2016
Priority date	Jan 29, 2016
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

A rotor drive system includes a mast defining a rotation axis, an electric motor with a stator portion fixed to the stationary mast, a rotor portion rotatably relative to the stator portion, and a clutch disposed along the rotation axis and connected to the rotor portion of the electric motor. A rotor assembly is rotatable about the rotation axis and operably connected to clutch such that, when rotational speed of the rotor assembly exceeds rotational speed of the rotor portion of the electric motor, the clutch disengages the rotor assembly from the electric motor rotor portion.

First claim

What is claimed is:

1. A rotor drive system, comprising:
a stationary mast defining a rotation axis;
an electric motor with a stator portion fixed to the mast and a rotor portion rotatable relative to the stator portion about the rotation axis;
a clutch connected to the rotor portion of the electric motor; and
a rotor assembly rotatable about the rotation axis and operably connected to the clutch, wherein the clutch is coaxially arranged between the electric motor and the rotor assembly about the rotation axis to disengage the electric motor from the rotor assembly when rotational speed of the rotor assembly about the rotation axis exceeds rotational speed of the rotor portion of the electric motor.

2. A rotor drive system as recited in claim 1 , wherein the clutch includes a roller ramp clutch mechanism.

3. A rotor drive system as recited in claim 1 , wherein the clutch includes an inner hub fixed relative to the rotor portion of the electric motor and extending circumferentially about the rotation axis.

4. A rotor drive system as recited in claim 1 , wherein the clutch includes an outer hub fixed relative to the rotor assembly and axially overlapping an inner hub of the clutch.

5. A rotor drive system as recited in claim 1 , wherein the clutch includes a roller element radially interposed between an inner hub and an outer hub of the clutch.

6. A rotor drive system as recited in claim 5 , wherein the clutch includes a resilient member urging a roller member into contact with both the inner hub and the outer hub.

7. A rotor drive system as recited in any claim 1 , wherein the outer hub defines a wedge pocket radially opposing an inner hub and separated therefrom by a radial gap.

8. A rotor drive system as recited in claim 7 , wherein the wedge pocket is bounded by a planar segment oblique relative to a line tangent to the inner hub.

9. A rotor drive system as recited in claim 7 , wherein the wedge pocket has a radial depth on a trailing end that is greater than a radial depth on a leading end relative to a direction of rotation of rotor assembly about the rotation axis.

10. A rotor drive system as recited in claim 7 , wherein the wedge pocket is bounded by a radially extending first finger on a leading end and a radially extending second finger on a trailing end, the second finger having a greater radial length than the first finger.

11. A rotor drive system as recited in claim 7 , further including a roller element captive within the wedge pocket and movable therein between first and second positions, the second position trailing the first position relative to a rotation direction of the rotor assembly.

12. A rotor drive system as recited in claim 11 , wherein movement of the roller into the first position engages the clutch, wherein movement into the second position disengages the clutch.

13. A rotorcraft, comprising:
an airframe;
a stationary mast fixed to the airframe and defining a rotation axis;
an electric motor with a stator portion fixed to the stationary mast and a rotor portion rotatable relative to the stator portion about the rotation axis;
a clutch connected to the rotor portion of the electric motor and externally of the airframe; and
a rotor assembly rotatable about the rotation axis and operably connected to the clutch, wherein the clutch is coaxially arranged between the electric motor and the rotor assembly about the rotation axis such that, when engaged, the electric motor is coupled to the rotor assembly by the clutch for rotating the rotor assembly about the airframe, and when disengaged, the electric motor is separated from the rotor assembly for rotating about the airframe in an autorotation state.

14. A rotorcraft as recited in claim 13 , further including a clutch lock disposed axially between the rotor assembly and the electric motor.

15. A rotorcraft as recited in claim 14 , wherein the clutch lock has a locked position and an unlocked position, the clutch lock coupling the electric motor to the rotor assembly in the locked position, coupling of the electric motor and rotor assembly being determined by whether the clutch is engaged or disengaged when the clutch lock is in the unlocked position.

16. A rotorcraft as recited in claim 13 , wherein the clutch includes a roller ramp clutch mechanism.

17. A rotorcraft as recited in claim 13 , wherein the clutch comprises:
an inner hub splined to the rotor portion of the electric motor and extending circumferentially about the rotation axis;
an outer hub disposed radially outward of the inner hub and extending circumferentially about the inner hub; and
a roller element circumferentially captive relative to the outer hub and disposed radially between the inner hub and the outer hub.

18. A rotorcraft as recited in claim 17 , further including bearings disposed radially between the outer hub and the stationary mast.

19. A rotorcraft as recited in claim 17 , further including bearings disposed radially between the inner hub and the stationary mast.

20. A rotorcraft as recited in claim 19 , wherein the stator portion of the electric motor is disposed radially between the stationary mast and the bearings.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Lauder Timothy F
• Hartman Jonathan

Classifications

• B64D27/34

  All-electric aircraft · CPC title

• B64C27/14 Primary

  Direct drive between power plant and rotor hub · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D27/026

  comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33) · CPC title