VERTICAL TAKE-OFF AND LANDING VEHICLE WITH INCREASED CRUISE EFFICIENCY

• US 20160244158A1
• Filed: 08/13/2014
• Published: 08/25/2016
• Est. Priority Date: 08/13/2013
• Status: Active Grant

• Current Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Original Assignee: The United States of America As Represented By The Secretary of Agriculture
• Inventors: FREDERICKS, WILLIAM J., Busan, Ronald C., Langford, William M., Laws, Christopher T., Hodges, William T., Webb, Sandy R., Moore, Mark D., Rothhaar, Paul M., North, David D., Johns, Zachary R.
• Granted Patent: US 9,475,579 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 11/28 Collapsible or foldable blades
• CPC Class Codes: B64C 11/50 Phase synchronisation between multiple propellers
• CPC Class Codes: B64C 25/32 characterised by elements which contact the ground or similar surface arrester hooks B64C25/68
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/385 Variable incidence wings
• CPC Class Codes: B64C 3/40 Varying angle of sweep
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 5/02 Tailplanes
• CPC Class Codes: B64C 9/14 forming slots
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20
• CPC Class Codes: Y02T 50/40 : Weight reduction
• CPC Class Codes: Y02T 50/60 : Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 903/903 : having energy storing means, e.g. battery, capacitor

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.

Claims

1-6. -6. (canceled)

7. A vehicle, comprising:

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,

wherein the first series of electric motors comprises eight electric motors and the second series of electric motors comprises two electric motors,

wherein the associated wing propellers of two of the electric motors of the first series of electric motors are variable pitch propellers each located at a wing tip of the wings, and

wherein the associated wing propellers of the remaining six of the electric motors of the first series of electric motors are fixed pitch propellers.

8. The vehicle of claim 7, wherein the associated tail propellers of the second series of electric motors are variable pitch propellers.

9. The vehicle of claim 8, wherein the associated wing propellers of the remaining six of the electric motors of the first series of electric motors and the associated tail propellers of the second series of electric motors are configured to fold back during a wing born flight phase.

10. The vehicle of claim 7, wherein the wing and the tail are arranged in a semi-tandem configuration.

11. The vehicle of claim 7, further comprising reflexed flaperons on the wing and tail.

14. The vehicle of claim 7, wherein the motor pylons are shaped to reduce drag at high lift coefficients.

15. The vehicle of claim 14, wherein each motor pylon of the first and second series of motor pylons has a cross sectional area that is comparatively less in a middle portion than in a forward section or an aft section.

19. The vehicle of claim 7, wherein the vehicle is an unmanned aerial vehicle.

20. The vehicle of claim 7, further comprising retractable landing skids and wherein the tail is configured to act as a rear landing skid.

12-13. -13. (canceled)

16-18. -18. (canceled)

21. A vehicle, comprising:

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,

wherein the first series of electric motors comprises at least three electric motors,

wherein the associated wing propellers of at least two of the electric motors of the first series of electric motors are variable pitch propellers each located at a wing tip of the wings, and

wherein the associated wing propeller of at least one of the electric motors of the first series of electric motors is a fixed pitch propeller.

22. The vehicle of claim 21, wherein the associated tail propellers of the second series of electric motors are variable pitch propellers.

23. The vehicle of claim 21, wherein the wing and the tail are arranged in a semi-tandem configuration.

24. The vehicle of claim 21, further comprising reflexed flaperons on the wing and tail.

25. The vehicle of claim 21, wherein the motor pylons are shaped to reduce drag at high lift coefficients.

26. The vehicle of claim 25, wherein each motor pylon of the first and second series of motor pylons has a cross sectional area that is comparatively less in a middle portion than in a forward section or an aft section.

27. The vehicle of claim 21, wherein the vehicle is an unmanned aerial vehicle.