Rotating wing assemblies for tailsitter aircraft

• US 9,821,909 B2
• Filed: 04/05/2016
• Issued: 11/21/2017
• Est. Priority Date: 04/05/2016
• Status: Active Grant

• Current Assignee: Swift Engineering, Inc.
• Original Assignee: Swift Engineering, Inc.
• Inventors: Moshe, Jonathan
• Primary Examiner(s): Bonzell, Philip J
• Application Number:
  US15/091,456
• Publication Number:
  US 20170283052A1
• Time in Patent Office: 595 Days
• CPC Class Codes: B64C 27/22 Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 3/38 Adjustment of complete wings or parts thereof
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A tailsitter aircraft includes one or more rotatable wings. The tailsitter aircraft optionally includes a fuselage from which wing supports extend. Each rotatable wing optionally includes a rotatable wing section having an inboard portion proximate to the fuselage, and an outboard portion distal from the fuselage. The rotatable wing section may be rotatably attached to the wing support and configured to rotate between a vertical flight configuration in which the inboard portion is positioned on an opposing side of the wing support relative to the outboard portion, and a horizontal flight configuration different from the vertical flight configuration. The wings may be rotated during flight to transition between horizontal and vertical flight configurations, and they may be rotated about multiple axes.

Claims

1. A vertical take-off or landing aircraft comprising:

a wing support extending from an inboard region of the aircraft;

a wing mounted on the wing support;

a first propulsion system attached to the wing; and

a second propulsion system attached to the wing;

wherein

the wing is positioned to rotate about an axis between a horizontal flight configuration in which the wing is generally aligned with the wing support and a vertical flight configuration in which the wing is oriented at an angle relative to the wing support, wherein the axis is positioned between the first propulsion system and the second propulsion system, and wherein the axis is oriented along a chordwise direction of the wing.

2. The vertical take-off or landing aircraft of claim 1, further comprising a landing leg attached to the wing and extending toward a tail end of the aircraft, the landing leg positioned to at least partially support the aircraft when the aircraft is on a landing surface in the vertical flight configuration.

3. The vertical take-off or landing aircraft of claim 1 wherein when the aircraft is in the horizontal flight configuration, the wing has an inboard portion positioned proximate to the inboard region and a tip portion positioned distal to the inboard region, and wherein when the aircraft is in the vertical flight configuration, the inboard portion and the tip portion are positioned on opposing sides of a center of gravity of the aircraft.

4. The vertical take-off or landing aircraft of claim 1 wherein the angle is between 20 degrees and 160 degrees.

5. The vertical take-off or landing aircraft of claim 1, further comprising one or more additional wing supports, wherein the wing is rotatably attached to the additional wing supports.

6. The vertical take-off or landing aircraft of claim 1, further comprising an elongated recess in the wing positioned to receive the wing support.

7. The vertical take-off or landing aircraft of claim 1 wherein the axis is positioned at an angle relative to a longitudinal axis of the aircraft.

8. The vertical take-off or landing aircraft of claim 1 wherein the axis is a first axis, and wherein the wing is further positioned to rotate about a second axis different from the first axis.

9. The vertical take-off or landing aircraft of claim 1 wherein when the aircraft is in the horizontal flight configuration, the wing has an inboard portion positioned proximate to the inboard region and a tip portion positioned distal to the inboard region, and wherein when the aircraft is in the vertical flight configuration, the inboard portion and the tip portion are positioned on opposing sides of the wing support.

10. The vertical take-off or landing aircraft of claim 9, further comprising a fuselage, wherein the inboard portion is a root portion, and wherein when the aircraft is in the horizontal flight configuration, the root portion is positioned adjacent to the fuselage.

11. The vertical take-off or landing aircraft of claim 9 wherein when the aircraft is in the horizontal flight configuration, the inboard portion is positioned adjacent to a fixed wing segment.

12. A vertical take-off or landing aircraft comprising:

a fuselage;

a wing support attached to the fuselage; and

a rotatable wing section having an inboard portion proximate to the fuselage and an outboard portion distal from the fuselage, the rotatable wing section being rotatably attached to the wing support at a wing rotation joint and configured to rotate about an axis between a vertical flight configuration in which the inboard portion is positioned on an opposing side of the wing rotation joint relative to the outboard portion, and a horizontal flight configuration different from the vertical flight configuration;

wherein the axis is oriented along a chordwise direction of the wing section.

13. The vertical take-off or landing aircraft of claim 12 wherein when the rotatable wing section is in the vertical flight configuration, the outboard portion and the inboard portion are located on opposite sides of a center of gravity of the aircraft.

14. The vertical take-off or landing aircraft of claim 12 wherein when the rotatable wing section is in the vertical flight configuration, the outboard portion and the inboard portion are located on opposite sides of the wing support.

15. The vertical take-off or landing aircraft of claim 12, further comprising a landing gear unit attached to the rotatable wing section, the landing gear unit positioned to at least partially support the aircraft on a surface when the rotatable wing section is in the vertical flight configuration.

16. The vertical take-off or landing aircraft of claim 12 wherein the wing support comprises a first wing support and the rotatable wing section comprises a first rotatable wing section, the aircraft further comprising a second wing support attached to the fuselage and a second rotatable wing section rotatably attached to the second wing support, wherein the first and second rotatable wing sections are configured to rotate between the horizontal flight configuration and the vertical flight configuration during flight.

17. The vertical take-off or landing aircraft of claim 12 wherein the rotatable wing section is configured to rotate to an angle between 20 degrees and 160 degrees relative to the wing support.

18. The vertical take-off or landing aircraft of claim 12 wherein the axis is positioned at a distance from an end of the rotatable wing section that is between 10 percent and 90 percent of a length of the rotatable wing section.

19. A vertical take-off or landing aircraft comprising:

a wing support extending from a main body of the aircraft; and

a wing attached to the wing support, the wing comprising a root portion and a tip portion, the wing configured to rotate about an axis between a horizontal flight configuration in which the wing is generally aligned with the wing support and a vertical flight configuration in which the wing is oriented at an angle relative to the wing support;

wherein

the axis is oriented along a chordwise direction of the wing, and wherein the root portion and the tip portion are positioned on opposite sides of a center of gravity of the aircraft in the vertical flight configuration.

20. The vertical take-off or landing aircraft of claim 19, further comprising a first propulsion rotor connected to the wing and a second propulsion rotor connected to the wing, wherein the axis is positioned between the first propulsion rotor and the second propulsion rotor.

21. The vertical take-off or landing aircraft of claim 19, further comprising a landing leg attached to the wing and extending toward a tail end of the aircraft, the landing leg positioned to at least partially support the aircraft on a landing surface in the vertical flight configuration.