Vertical takeoff and landing vehicle with increased cruise efficiency

Patent metadata

Field	Value
Publication number	US-9896200-B2
Application number	US-201615332391-A
Country	US
Kind code	B2
Filing date	Oct 24, 2016
Priority date	Aug 13, 2013
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

First claim

What is claimed is:

1. A vehicle, comprising:
a wing configured to tilt through a range of motion;
a plurality of wing electric motors coupled to the wing, wherein each wing electric motor is configured to drive an associated wing propeller;
a tail comprising at least one tail electric motor, wherein each tail electric motor is configured to drive an associated tail propeller, wherein the tail is configured to tilt through a range of motion;
an electric propulsion system connected to the wing electric motors and the tail electric motors; and
wherein the associated wing propellers comprise at least one variable pitch propeller and at least one fixed pitch propeller.

2. The vehicle of claim 1 , wherein the at least one variable pitch propeller is located at a wing tip of the wing.

3. The vehicle of claim 1 , wherein each associated tail propeller comprises a variable pitch tail propeller.

4. The vehicle of claim 1 , wherein the at least one variable pitch propeller is configured to fold back during a wing born flight phase.

5. The vehicle of claim 1 , wherein the wing and the tail are arranged in a semi-tandem configuration.

6. The vehicle of claim 1 , further comprising reflexed flaperons on the wing and tail.

7. The vehicle of claim 1 , wherein each tail and wing electric motor are mounted on a motor pylon which is shaped to reduce drag at high lift coefficients.

8. The vehicle of claim 7 , wherein each motor pylon has a cross sectional area that is less in a middle portion than in a forward section or an aft section.

9. The vehicle of claim 1 , wherein the vehicle is an unmanned aerial vehicle.

10. The vehicle of claim 1 , further comprising retractable landing skids and wherein the tail is configured to act as a rear landing skid.

11. The vehicle of claim 1 , wherein the range of motion is ninety degrees and the wing and tail are configured to transition between a wing born flight phase and a vertical takeoff and landing flight phase by tilting through the range of motion.

12. The vehicle of claim 11 , wherein the wing is swept.

13. The vehicle of claim 1 , wherein the wing propellers and the tail propellers are synchronized to each hold specific phase angles to provide destructive interference of propeller noise.

14. The vehicle of claim 1 , wherein the wing propellers and the tail propellers alternate rotation directions and turn at a low tip speed.

15. The vehicle of claim 1 , wherein tail is configured in a dihedral angle.

16. A vehicle, comprising:
a wing configured to tilt through a range of motion of 90 degrees;
a plurality of wing electric motors coupled to the wing, wherein each wing electric motor is configured to drive an associated wing propeller;
a tail comprising at least one tail electric motor, wherein each tail electric motor is configured to drive an associated tail propeller, wherein the tail is configured to tilt through a range of motion;
an electric propulsion system connected to the wing electric motors and the tail electric motors;
wherein each tail and wing electric motor are mounted on a motor pylon which has a cross sectional area that is less in a middle portion than in a forward section or an aft section; and
wherein the associated wing propellers comprise at least one variable pitch propeller and at least one fixed pitch propeller.

17. The vehicle of claim 16 , wherein the vehicle is an unmanned aerial vehicle.

18. The vehicle of claim 17 , wherein the at least one variable pitch propeller is configured to fold back during a wing born flight phase.

19. The vehicle of claim 16 , wherein each associated tail propeller comprises a variable pitch tail propeller.

20. The vehicle of claim 19 , wherein the at least one variable pitch propeller is located at a wing tip of the wing.

Assignees

• Nasa
• Nasa

Inventors

• Fredericks William J
• Moore Mark D
• Busan Ronald C
• Rothhaar Paul M
• North David D
• Langford William M
• Laws Christopher T
• Hodges William T
• Johns Zachary R
• Webb Sandy R

Classifications

• Y10S903/903

  having energy storing means, e.g. battery, capacitor · CPC title

• B64C11/28

  Collapsible or foldable blades · CPC title

• B64C5/02

  Tailplanes · CPC title

• B64C25/52

  Skis or runners · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title