Aircraft propulsor and method for using said propulsor

Patent metadata

Field	Value
Publication number	US-12195191-B2
Application number	US-202117535200-A
Country	US
Kind code	B2
Filing date	Nov 24, 2021
Priority date	Nov 24, 2021
Publication date	Jan 14, 2025
Grant date	Jan 14, 2025

Abstract

A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.

First claim

What is claimed is:

1. A propulsor comprising:
a propulsor body;
a prop assembly in rotational communication with the propulsor body, the prop assembly comprising a hub and a plurality of prop blades, the hub and the plurality of prop blades are configured for rotation about an axial centerline of the propulsor, each prop blade of the plurality of prop blades is rotatably mounted to the hub and rotatable between a deployed position and a stowed position;
at least one linkage having a first linkage end and a second linkage end, the first linkage end of the at least one linkage rotatably mounted to the propulsor body and the second linkage end configured to be rotatably mounted to an aircraft body;
a first motor disposed within the propulsor body at the axial centerline, the first motor coupled to the at least one linkage, the first motor configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position; and
a first shaft extending along the axial centerline between and to the first motor and the hub, the first shaft configured for rotation about the axial centerline, the first shaft mounted to the hub and configured to apply a rotational force from the first motor to the hub.

2. The propulsor of claim 1 , wherein, in the deployed position, the plurality of prop blades extend in a first direction substantially radially outward from the axial centerline and wherein, in the stowed position, the plurality of prop blades extend in a second direction substantially axially with respect to the axial centerline.

3. The propulsor of claim 1 , further comprising a second shaft configured for rotation about the axial centerline, the second shaft configured to effect rotation of the plurality of prop blades between the deployed position and the stowed position.

4. The propulsor of claim 3 , wherein each of the first shaft and the second shaft are in rotational communication with the first motor and the first motor is configured to selectively effect rotation of the first shaft and the second shaft about the axial centerline.

5. The propulsor of claim 3 , wherein the second shaft is in rotational communication with a second motor, different than the first motor, the second motor configured to selectively effect rotation of the second shaft about the axial centerline.

6. The propulsor of claim 1 , wherein in the first rotational position the propulsor body is in a propulsor stowed position relative to the aircraft body, and in the second rotational position the propulsor body is in a propulsor deployed position relative to the aircraft body.

7. The propulsor of claim 1 , wherein a gearbox selectively engages the first motor using a clutch to rotate the at least one linkage relative to the propulsor body between the first rotational position and the second rotational position.

8. An aircraft comprising:
an aircraft body including an exterior surface and defining an interior cavity; and
at least one propulsor mounted to the aircraft body and moveable between a first propulsor position in which the at least one propulsor is located inside the interior cavity and a second propulsor position in which the at least one propulsor is at least partially disposed outside the interior cavity, the at least one propulsor comprising:
a propulsor body;
a prop assembly in rotational communication with the propulsor body, the prop assembly comprising a hub and a plurality of prop blades, the hub and the plurality of prop blades are configured for rotation about an axial centerline of the propulsor, each prop blade of the plurality of prop blades is rotatably mounted to the hub and rotatable between a deployed position and a stowed position;
at least one linkage having a first linkage end and a second linkage end, the first linkage end of the at least one linkage rotatably mounted to the propulsor body and the second linkage end rotatably mounted to the aircraft body; and
a first motor disposed within the propulsor body at the axial centerline, the first motor coupled to the at least one linkage, the first motor configured to rotate the at least one linkage relative to the propulsor body between a first rotational position corresponding with the first propulsor position and a second rotational position corresponding with the second propulsor position.

9. The aircraft of claim 8 , further comprising a gas turbine generator configured to provide electrical power for the at least one propulsor.

10. The aircraft of claim 9 , further comprising an energy storage device in electrical communication with the gas turbine generator, the energy storage device configured to provide electrical power for the at least one propulsor.

11. The aircraft of claim 8 , further comprising a main propulsor fixedly attached to the aircraft body.

12. The aircraft of claim 8 , further comprising an energy storage device configured to provide electrical power for the at least one propulsor.

13. The aircraft of claim 12 , wherein the energy storage device includes one or both of a battery and a capacitor.

14. The aircraft of claim 8 , wherein the at least one propulsor is configured as a pusher prop.

15. A method for providing thrust for an aircraft, the method comprising:
deploying a propulsor from a propulsor stowed position within an interior cavity of an aircraft body to a propulsor deployed position in which at least a portion of the propulsor is disposed outside of the interior cavity by rotating at least one linkage with a first motor, the at least one linkage rotatably mounted to the propulsor and the aircraft body, the first motor disposed within the propulsor;
rotating a plurality of prop blades of the propulsor, with the first motor, from a blade stowed position to a blade deployed position in which the plurality of prop blades extend in a substantially radial direction relative to an axial centerline of the propulsor; and
providing thrust for the aircraft by rotating the plurality of prop blades about the axial centerline with the first motor.

16. The method of claim 15 , wherein the step of deploying the propulsor is performed in response to a predetermined flight condition.

17. The method of claim 16 , wherein the predetermined flight condition includes one or both of a takeoff condition or a go-around condition.

18. The method of claim 15 , further comprising providing electrical power for the propulsor with an energy storage device.

19. The method of claim 18 , wherein the energy storage device includes one or both of a battery and a capacitor.

20. The method of claim 15 , wherein the propulsor is configured as a pusher prop.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Sobanski Jon E
• Hanrahan Paul R
• Staubach Joseph B
• Klinowski Jill

Classifications

• B64D27/359

  using capacitors · CPC title

• B64D27/357

  using batteries · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D27/406

  Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links · CPC title

• B64C11/28 Primary

  Collapsible or foldable blades · CPC title