System, apparatus and method for long endurance vertical takeoff and landing vehicle

Patent metadata

Field	Value
Publication number	US-9682774-B2
Application number	US-201414507313-A
Country	US
Kind code	B2
Filing date	Oct 6, 2014
Priority date	Feb 15, 2012
Publication date	Jun 20, 2017
Grant date	Jun 20, 2017

Abstract

A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

First claim

What is claimed is:

1. A vertical take-off and landing (VTOL) aircraft, comprising:
a fuselage having a nose end and a tail end;
an empennage located at the tail end of the fuselage;
a canted wing having first and second wing tips,
wherein the fuselage is positioned approximately halfway between the first and second wing tips of the canted wing, the canted wing having (1) a first integrated hinge disposed between the fuselage and the first wing tip of the canted wing, and (2) a second integrated hinge disposed between the fuselage and the second wing tip,
wherein the first and second integrated hinges are configured to reject wind gust by maintaining a constant moment at the first integrated hinge or the second integrated hinge,
wherein the canted wing includes a trailing edge control surface positioned on the canted wing between each of: (1) the fuselage and the first integrated hinge; (2) the fuselage and the second integrated hinge; (3) the first integrated hinge and the first wing tip; and (4) the second integrated hinge and the second wing tip; and

a plurality of engines, said plurality of engines comprising (1) a first tiltrotor positioned between the fuselage and the first wing tip of the canted wing, (2) a second tiltrotor positioned between the fuselage and the second wing tip of the canted wing, and (3) a fixed engine positioned on the fuselage aft of the canted wing in a vertical configuration, the first tiltrotor, the second tiltrotor, and the plurality of engines configured such that:
during a first phase of takeoff, (i) said fixed engine generates thrust, thereby causing the tail end of the fuselage to become airborne, and (ii) said first tiltrotor and said second tiltrotor transition from a vertical configuration to a horizontal configuration until the fuselage achieves a predetermined angle, and
during a second phase of takeoff, said first tiltrotor and said second tiltrotor are in the horizontal configuration and the aircraft is capable of wing borne flight.

2. The VTOL aircraft of claim 1 , wherein the fixed engine is disabled during wing borne flight.

3. The VTOL aircraft of claim 1 , wherein the empennage employs a stabilizer configuration.

4. The VTOL aircraft of claim 3 , wherein the stabilizer configuration comprises a vertical stabilizer and an all-moving horizontal stabilizer.

5. The VTOL aircraft of claim 1 , wherein the canted wing has an aspect ratio of at least 10.

6. The VTOL aircraft of claim 1 , further comprising an intelligence, surveillance, and reconnaissance payload.

7. The VTOL aircraft of claim 1 , wherein the canted wing is configured to provide substantially constant lift to the VTOL aircraft by reducing an angle of attack of the outboard wing panel starting at the hinge of the canted wing, thereby rejecting wind gusts.

8. The VTOL aircraft of claim 1 , wherein said first tiltrotor and said second tiltrotor are counter-rotating.

9. The VTOL aircraft of claim 1 , wherein the VTOL aircraft is an unmanned VTOL aircraft.

10. The VTOL aircraft of claim 1 , further comprising a vehicle computer coupled with a sensor to measure wind gusts, wherein the vehicle computer is configured to control a bend angle of said first and/or second integrated hinges based at least in part on measurements from said sensor.

11. A vertical take-off and landing (VTOL) aircraft, comprising:
a fuselage having a nose end, and a tail end;
an empennage located at the tail end of the fuselage;
a canted wing having a first wing tip and a second wing tip, the fuselage positioned halfway between the first and second wing tips, the canted wing comprising:
first and second wing panels coupled by a first hinge, the first wing panel attached to the fuselage and the second wing panel comprising the first wing tip; and
third and fourth wing panels coupled by a second hinge, the third wing panel attached to the fuselage opposite the first wing panel and the fourth wing panel comprising the second wing tip, the first hinge and the second hinge to enable the canted wing to reject wind gusts by maintaining constant moments at the locations of the integrated hinges, wherein each of the first, second, third, and fourth wing panels includes a control surface at its trailing edge;

a first tiltrotor positioned left of the fuselage on the canted wing;
a second tiltrotor positioned right of the fuselage on the canted wing; and
a fixed engine positioned on the fuselage aft of the canted wing in a vertical configuration, the first tiltrotor, the second tiltrotor, and the fixed engine configured such that:
during a first phase of takeoff, (i) the fixed engine generates thrust, thereby causing the tail end of the fuselage to become airborne, and (ii) the first tiltrotor and the second tiltrotor transition from a vertical orientation to a horizontal orientation until the fuselage achieves a transition angle; and
during a second phase of takeoff, the first tiltrotor and the second tiltrotor are in the horizontal configuration to provide thrust to the aircraft for wing borne flight.

12. The VTOL aircraft of claim 11 , further comprising a vehicle computer to control bend angles of the first and second hinges to control wind gust rejection by the canted wing.

13. The VTOL aircraft of claim 12 , further comprising a sensor to measure a wind gust, the vehicle computer to control the bend angles using the measurement of the wind gust.

14. The VTOL aircraft of claim 12 , wherein the vehicle computer controls the canted wing to provide substantially constant lift to the VTOL aircraft by controlling the canted wing to reject wind gusts by reducing an angle of attack of at least one of (1) the second wing panel starting at the first hinge or (2)the fourth wing panel starting at the second hinge.

15. The VTOL aircraft of claim 11 , wherein the first tiltrotor and the second tiltrotor are counter-rotating.

16. The VTOL aircraft of claim 11 , wherein the fixed engine is disabled during wing borne flight.

17. A vertical take-off and landing (VTOL) aircraft, comprising:
a fuselage having a nose end, and a tail end;
an empennage located at the tail end of the fuselage;
a canted wing having a first wing tip and a second wing tip, the fuselage positioned halfway between the first and second wing tips, the canted wing comprising:
first and second wing panels coupled by a first hinge, the first wing panel attached to the fuselage and the second wing panel comprising the first wing tip; and
third and fourth wing panels coupled by a second hinge, the third wing panel attached to the fuselage opposite the first wing panel and the fourth wing panel comprising the second wing tip, wherein each of the first wing panel and the third wing panel includes a control surface at its trailing edge;

a vehicle computer coupled with a sensor to measure wind gusts, wherein the vehicle computer is configured to control a bend angle of said first hinge and/or second hinge based at least in part on measurements from said sensor;
a first tiltrotor positioned left of the fuselage on the canted wing; and
a second tiltrotor positioned right of the fuselage on the canted wing, the first tiltrotor and the second tiltrotor configured such that:
during a first phase of takeoff, the first tiltrotor and the second tiltrotor transition from a vertical orientation to a horizontal orientation until the fuselage achieves a transition angle; and
during a second phase of takeoff, the first tiltrotor and the second tiltrotor are in the horizontal configuration to provide thrust to the aircraft for wing borne flight.

Assignees

• Aurora Flight Sciences Corp

Inventors

• Paduano James Donald
• Dahlstrand Paul Nils
• Wissler John Brooke
• Woodworth Adam

Classifications

• B64U50/14

  ducted or shrouded · CPC title

• B64U70/60

  Take-off or landing of UAVs from a runway using their own power · CPC title

• B64C27/52 Primary

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title