Tandem electric rotorcraft

Patent metadata

Field	Value
Publication number	US-2022388640-A1
Application number	US-202117303642-A
Country	US
Kind code	A1
Filing date	Jun 3, 2021
Priority date	Jun 3, 2021
Publication date	Dec 8, 2022
Grant date	—

Abstract

An electric tandem rotorcraft is disclosed. The tandem rotorcraft can include a forward and an aft electric rotor assembly operably coupled to a fuselage of the rotor craft. The aft rotor assembly can be coupled to the fuselage via a tail structure. The rotorcraft can include a wing assembly that can be operably rotatable between a vertical lift configuration and a horizontal flight configuration. The wing assembly can be disposed between and/or below planes of rotation of the forward and aft rotor assemblies. The forward and aft rotor assemblies can have planes of rotation that overlap one another and may or may not intermesh. The forward and aft rotor assemblies can also be distanced such that their respective planes of rotation do not overlap.

First claim

What is claimed is:

1 . A tandem electric rotorcraft, comprising:
a fuselage having a forward end and an aft end; a wing assembly operably coupled to the fuselage between the forward end and the aft end and operably rotatable between a vertical lift configuration and a horizontal flight configuration; a forward electric rotor assembly having forward rotor blades and operably coupled to forward end of the fuselage via a forward pylon, wherein the forward electric rotor assembly is configured to rotate in a first plane of rotation; and an aft electric rotor assembly having aft rotor blades and operably coupled to the aft end of the fuselage via an aft pylon, wherein the aft electric rotor assembly is configured to rotate in a second plane of rotation, wherein the first plane of rotation and the second plane of rotation overlap.

2 . The tandem electric rotorcraft of claim 1 , wherein the second plane of rotation is disposed above the first plane of rotation.

3 . The tandem electric rotorcraft of claim 1 , wherein the vertical lift configuration is a position substantially perpendicular with a longitudinal axis of the fuselage.

4 . The tandem electric rotorcraft of claim 1 , wherein the horizontal flight configuration is a position substantially parallel with the longitudinal axis of the fuselage.

5 . The tandem electric rotorcraft of claim 1 , further comprising an actuator configured to transition the wing assembly between the vertical lift configuration and the horizontal flight configuration.

6 . The tandem electric rotorcraft of claim 5 , wherein the transition of the wing assembly is pilot controlled.

7 . The tandem electric rotorcraft of claim 5 , wherein the transition of the wing assembly is controlled via a flight control computer.

8 . The tandem electric rotorcraft of claim 1 , wherein the first plane of rotation and the second plane of rotation intermesh.

9 . The tandem electric rotorcraft of claim 1 , wherein the wing assembly is disposed below an area of overlap of the first plane of rotation and the second plane of rotation.

10 . The tandem electric rotorcraft of claim 1 , further comprising a tail structure disposed between the fuselage and the aft pylon.

11 . A non-overlapping tandem electric rotorcraft, comprising:
a fuselage having a forward end and an aft end; a wing assembly operably coupled to the fuselage between the forward end and the aft end and operably rotatable between a vertical lift configuration and a horizontal flight configuration; a forward electric rotor assembly having forward rotor blades and operably coupled to forward end of the fuselage via a forward pylon, wherein the forward electric rotor assembly is configured to rotate in a first plane of rotation; and an aft electric rotor assembly having aft rotor blades and operably coupled to the aft end of the fuselage via an aft pylon, wherein the aft electric rotor assembly is configured to rotate in a second plane of rotation, wherein the first plane of rotation and the second plane of rotation overlap.

12 . The non-overlapping tandem electric rotorcraft of claim 11 , wherein the second plane of rotation is disposed above the first plane of rotation.

13 . The non-overlapping tandem electric rotorcraft of claim 11 , wherein the first plane of rotation is equiplanar with the second plane of rotation.

14 . The non-overlapping tandem electric rotorcraft of claim 11 , further comprising an actuator configured to transition the wing assembly between the vertical lift configuration and the horizontal flight configuration.

15 . The non-overlapping tandem electric rotorcraft of claim 14 , wherein the transition of the wing assembly is pilot controlled.

16 . The non-overlapping tandem electric rotorcraft of claim 14 , wherein the transition of the wing assembly is controlled via a flight control computer.

17 . The non-overlapping tandem electric rotorcraft of claim 11 , wherein the first plane of rotation and the second plane of rotation intermesh.

18 . The non-overlapping tandem electric rotorcraft of claim 11 , wherein the wing assembly is disposed below an area of overlap of the first plane of rotation and the second plane of rotation.

19 . A method of transitioning a flight configuration of a tandem electric rotorcraft, the method comprising the steps of:
rotating a wing assembly about a longitudinal wing axis such that a lateral wing axis is substantially perpendicular to a fuselage longitudinal axis; and rotating the wing assembly about the longitudinal wing axis such that the lateral wing axis is substantially parallel with the fuselage longitudinal axis, wherein the wing assembly is operably coupled to a fuselage of the tandem electric rotorcraft, and wherein the tandem electric rotorcraft includes a forward electric rotor assembly and an aft electric rotor assembly.

20 . The electric tandem non-overlapping rotorcraft of claim 19 , further comprising an actuator configured to transition the wing assembly between the vertical lift configuration and the horizontal flight configuration.

21 . The electric tandem non-overlapping rotorcraft of claim 20 , wherein the transition of the wing assembly is pilot controlled.

22 . The electric tandem non-overlapping rotorcraft of claim 20 , wherein the transition of the wing assembly is controlled via a flight control computer.

23 . The electric tandem non-overlapping rotorcraft of claim 19 , wherein the first plane of rotation and the second plane of rotation intermesh.

24 . The electric tandem non-overlapping rotorcraft of claim 19 , wherein the wing assembly is disposed below an area of overlap of the first plane of rotation and the second plane of rotation.

Assignees

• Textron Innovations Inc
• Bell Textron Inc

Inventors

• Ivans Steven Ray
• Ross Brent Chadwick

Classifications

• B64C3/385

  Variable incidence wings · CPC title

• B64C27/26 Primary

  characterised by provision of fixed wings · CPC title

• B64C27/08 Primary

  with two or more rotors · CPC title

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title