Rotating wing assemblies for tailsitter aircraft

• US 10,293,933 B2
• Filed: 11/02/2017
• Issued: 05/21/2019
• 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:
  US15/801,833
• Publication Number:
  US 20180072413A1
• Time in Patent Office: 565 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 plurality of wing segments, each wing segment of the plurality of wing segments being rotatable relative to each other wing segment of the plurality of wing segments between a first arrangement in which a first wing segment is generally parallel to a second wing segment and a third wing segment is generally parallel to a fourth wing segment, wherein the plurality of wing segments forms a biplane, and a second arrangement in which the first wing segment is not parallel to the second wing segment and the third wing segment is not parallel to the fourth wing segment; and

a plurality of propulsion rotors, each propulsion rotor configured to provide vertical thrust and horizontal thrust;

wherein each wing segment of the plurality of wing segments is configured to rotate during flight.

2. The vertical take-off or landing aircraft of claim 1 wherein at least one propulsion rotor of the plurality of propulsion rotors is positioned at a rotation axis about which at least one of the wing segments rotates.

3. The vertical take-off or landing aircraft of claim 1 wherein at least one propulsion rotor of the plurality of propulsion rotors is attached to a first wing segment of the plurality of wing segments and spaced apart from a rotation axis about which the first wing segment rotates.

4. The vertical take-off or landing aircraft of claim 1 wherein each propulsion rotor is configured to provide vertical thrust when each wing segment is in the second arrangement.

5. The vertical take-off or landing aircraft of claim 1, further comprising a fuselage positioned between the first wing segment and the fourth wing segment.

6. The vertical take-off or landing aircraft of claim 1, further comprising a fuselage and a plurality of wing supports extending from the fuselage, wherein each wing support supports at least one of the wing segments.

7. The vertical take-off or landing aircraft of claim 1 wherein:

the first wing segment is rotatable about a first axis that is transverse to a spanwise direction of the first wing segment;

the second wing segment is rotatable about a second axis that is transverse to a spanwise direction of the second wing segment;

the third wing segment is rotatable about a third axis that is transverse to a spanwise direction of the third wing segment; and

the fourth wing segment is rotatable about a fourth axis that is transverse to a spanwise direction of the fourth wing segment.

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

a first wing having a first inboard portion proximate to an inboard region of the aircraft and a first outboard portion distal from the inboard region; and

a second wing having a second inboard portion proximate to the inboard region and a second outboard portion distal from the inboard region;

wherein the first wing and the second wing are configured to rotate between a first flight configuration in which the first inboard portion is positioned at a first distance from the second inboard portion, and a second flight configuration in which the first inboard portion is positioned at a second distance from the second inboard portion, wherein the second distance is greater than the first distance; and

wherein the aircraft is configured to take off or land in a tail-down orientation.

9. The vertical take-off or landing aircraft of claim 8, further comprising a third wing and a fourth wing, wherein each of the third wing and the fourth wing is rotatable relative to the inboard region, and wherein the first wing is positioned to rotate about a first axis, the second wing is positioned to rotate about a second axis, the third wing is positioned to rotate about a third axis, and the fourth wing is positioned to rotate about a fourth axis, and wherein the third and fourth axes are different from the first and second axes.

10. The vertical take-off or landing aircraft of claim 8, further comprising a fuselage.

11. The vertical take-off or landing aircraft of claim 8, further comprising a plurality of propulsion rotors configured to provide vertical thrust when the first wing and the second wing are in the second flight configuration.

12. The vertical take-off or landing aircraft of claim 8 wherein:

the first wing is rotatable about a first axis that is transverse to a span of the first wing; and

the second wing is rotatable about a second axis that is transverse to a span of the second wing.

13. The vertical take-off or landing aircraft of claim 12, further comprising a first propulsion system positioned at the first axis and a second propulsion system positioned at the second axis.

14. The vertical take-off or landing aircraft of claim 13 wherein the first propulsion system and the second propulsion system each comprise a propulsion rotor.

15. The vertical take-off or landing aircraft of claim 12, further comprising:

a third wing having a third inboard portion proximate to the inboard region and a third outboard portion distal from the inboard region, the third wing being rotatable about a third axis that is transverse to a span of the third wing; and

a fourth wing having a fourth inboard portion proximate to the inboard region and a fourth outboard portion distal from the inboard region, the fourth wing being rotatable about a fourth axis that is transverse to a span of the fourth wing.

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

a plurality of wing segments, each wing segment of the plurality of wing segments being rotatable relative to each other wing segment of the plurality of wing segments between a first arrangement in which a first wing segment is generally parallel to a second wing segment and a third wing segment is generally parallel to a fourth wing segment, and a second arrangement in which the first wing segment is not parallel to the second wing segment, and the third wing segment is not parallel to the fourth wing segment, and in which each wing segment of the plurality of wing segments is spaced apart from every other wing segment of the plurality of wing segments; and

a plurality of propulsion systems, each propulsion system configured to provide vertical thrust and horizontal thrust, wherein at least one propulsion system of the plurality of propulsion systems is configured to provide vertical thrust when at least one wing segment of the plurality of wing segments is in the second arrangement.

17. The vertical take-off or landing aircraft of claim 16 wherein at least one of the plurality of propulsion systems comprises a propulsion rotor.

18. The vertical take-off or landing aircraft of claim 17 wherein the propulsion rotor is positioned at a rotation axis about which at least one of the wing segments rotates.

19. The vertical take-off or landing aircraft of claim 17 wherein the propulsion rotor is configured to provide vertical thrust when each wing segment is in the second arrangement.

20. The vertical take-off or landing aircraft of claim 17 wherein the propulsion rotor is configured to provide horizontal thrust when each wing segment is in the first arrangement.

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

a plurality of wing segments, each wing segment of the plurality of wing segments being rotatable relative to each other wing segment of the plurality of wing segments between a first arrangement in which a first wing segment is generally parallel to a second wing segment and a third wing segment is generally parallel to a fourth wing segment, wherein the plurality of wing segments forms a biplane, and a second arrangement in which the first wing segment is not parallel to the second wing segment and the third wing segment is not parallel to the fourth wing segment; and

a plurality of propulsion rotors, each propulsion rotor configured to provide vertical thrust and horizontal thrust;

wherein each wing segment of the plurality of wing segments is rotatable about a pivot axis positioned away from free ends of the wing segment.