Unmanned aerial vehicle wing pylon system

Patent metadata

Field	Value
Publication number	US-12286226-B2
Application number	US-202318312336-A
Country	US
Kind code	B2
Filing date	May 4, 2023
Priority date	May 4, 2023
Publication date	Apr 29, 2025
Grant date	Apr 29, 2025

Abstract

In one embodiment, systems and methods include an aircraft vehicle comprising a body, a first wing coupled to the body, and a second wing coupled to the body, wherein the second wing has a length greater than the first wing, wherein each of the first wing and the second wing comprises a plurality of segments, wherein the second wing comprises a wing pylon system. The wing pylon system comprises one of the plurality of segments of the second wing, a payload, and a pylon coupling the payload to the one of the plurality of segments, the pylon being disposed underneath the one of the plurality of segments, and the payload being disposed underneath the pylon. A center of lift and a center of gravity for the aircraft vehicle are aligned and each is offset from a central axis of the body.

First claim

What is claimed is:

1. An unmanned aerial vehicle, comprising:
a body;
a first wing coupled to the body; and
a second wing coupled to the body and disposed opposite to the first wing, wherein the second wing has a length greater than the first wing, wherein each of the first wing and the second wing comprises a plurality of segments, wherein the second wing comprises a wing pylon system, wherein the wing pylon system comprises:
a wing segment being one of the plurality of segments of the second wing, wherein the wing segment is disposed between the body and another one of the plurality of segments of the second wing located at a distal end of the second wing;
a tank configured to contain a fuel to be used to sufficiently power the unmanned aerial vehicle, wherein the fuel is propane; and
a pylon coupling the tank to the wing segment, wherein the pylon is disposed underneath the wing segment, and wherein the tank is disposed underneath the pylon,

wherein a center of lift and a center of gravity for the unmanned aerial vehicle are each offset from a central axis of the body, and wherein the center of lift and the center of gravity are aligned.

2. The unmanned aerial vehicle of claim 1 , further comprising:
at least one aileron disposed on the first wing configured to deflect upwards and downwards; and
at least one aileron disposed on the second wing configured to deflect upwards and downwards.

3. The unmanned aerial vehicle of claim 1 , wherein the tank is configured to contain a volume of about 8.6 liters of the fuel.

4. The unmanned aerial vehicle of claim 1 , further comprising:
a horizontal tail stabilizer disposed behind the body and securably coupled to the body; and
a vertical tail stabilizer disposed behind the body and securably coupled to the body, wherein the horizontal tail stabilizer is larger than the vertical tail stabilizer.

5. The unmanned aerial vehicle of claim 1 , wherein the second wing comprises a greater number of the plurality of segments than the first wing.

6. The unmanned aerial vehicle of claim 1 , wherein the wing pylon system consists of the wing segment, the tank, and the pylon.

7. The unmanned aerial vehicle of claim 1 , wherein the pylon is secured to an underside of the wing segment through welding, wherein the tank is secured to the pylon through welding.

8. The unmanned aerial vehicle of claim 1 , wherein the wing pylon system further comprises a tail cone coupled to the tank extending away from the tank.

9. An unmanned aerial vehicle, comprising: a body; a first wing coupled to the body; and a second wing coupled to the body and disposed opposite to the first wing, wherein the second wing comprises a plurality of segments and a wing pylon system, wherein the second wing has a length greater than the first wing, wherein the wing pylon system comprises: a wing segment being one of the plurality of segments of the second wing, wherein the wing segment is disposed between the body and another one of the plurality of segments of the second wing located at a distal end of the second wing; a tank configured to contain a fuel to be used to sufficiently power the unmanned aerial vehicle, wherein the fuel is propane; and a pylon coupling the tank to the wing segment, wherein the pylon is disposed underneath the wing segment, and wherein the tank is disposed underneath the pylon.

10. The unmanned aerial vehicle of claim 9 , further comprising at least one aileron disposed on the first wing configured to deflect upwards and downwards.

11. The unmanned aerial vehicle of claim 10 , further comprising at least one aileron disposed on the second wing configured to deflect upwards and downwards.

12. The unmanned aerial vehicle of claim 9 , wherein the wing pylon system consists of the wing segment, the tank, and the pylon.

13. The unmanned aerial vehicle of claim 9 , wherein the tank is configured to contain a volume of about 8.6 liters of the fuel.

14. The unmanned aerial vehicle of claim 9 , wherein the wing pylon system further comprises a tail cone coupled to the tank extending away from the tank.

15. An unmanned aerial vehicle comprising: a body; a first wing coupled to the body; and a second wing coupled to the body and disposed opposite to the first wing, wherein the second wing comprises a plurality of segments and a wing pylon system, wherein the wing pylon system comprises: a wing segment being one of the plurality of segments of the second wing, wherein the wing segment is disposed between the body and another one of the plurality of segments of the second wing located at a distal end of the second wing; a tank configured to contain a fuel to be used to sufficiently power the unmanned aerial vehicle, wherein the fuel is propane; and a pylon coupling the tank to the wing segment, wherein the pylon is disposed underneath the wing segment, wherein the tank is disposed underneath the pylon, and wherein a center of lift and a center of gravity for the unmanned aerial vehicle are each offset from a central axis of the body and are aligned.

16. The wing pylon system of claim 15 , wherein the pylon is secured to an underside of the segment through one or more fasteners or welding, wherein the tank is secured to the pylon through additional one or more fasteners or welding.

17. The wing pylon system of claim 15 , wherein the tank is configured to contain a volume of about 8.6 liters of the fuel.

18. The wing pylon system of claim 15 , wherein the wing pylon system consists of the segment of the wing, the tank, the pylon, and a tail cone coupled to the tank extending away from the tank.

Assignees

• Lockheed Corp

Inventors

• Gamble Dustin Eli

Classifications

• B64C3/28

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/187

  Ribs · CPC title

• B64C3/185

  Spars · CPC title

• B64U2101/60

  for transporting passengers; for transporting goods other than weapons · CPC title