Devices, systems and methods for modular payload integration for unmanned aerial vehicles

• US 8,256,715 B2
• Filed: 11/18/2009
• Issued: 09/04/2012
• Est. Priority Date: 11/18/2008
• Status: Expired due to Fees

• Current Assignee: Mav6 LLC
• Original Assignee: MAVG LLC
• Inventors: Ballard, Brian Adams, Kluesener, Robert Daniel, Wowczuk, Zenovy Stephan, Watson, Alexander Cobb
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Dixon, Keith L
• Application Number:
  US12/621,257
• Publication Number:
  US 20100123042A1
• Time in Patent Office: 1,021 Days
• Field of Search: 244/123.1, 244/123.5, 244/124, 244/137.4, 244/36, 244/45.R, 244/139, 244/140
• US Class Current: 244/123.1
• CPC Class Codes: B33Y 80/00 Products made by additive manufacturing
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/40 Modular UAVs
• CPC Class Codes: B64U 20/92 of avionics
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 30/10 Wings

Abstract

Devices, systems and methods are disclosed which relate to providing wing designs with payload integration capabilities on existing modularly assembled unmanned aerial vehicles (UAVs). Exemplary embodiments of the present invention present a novel technique of adding payloads to existing UAVs while improving flight performance over existing techniques by maintaining a similar overall weight with improved aerodynamic properties. The technique includes using a reinforced foam core center wing with a fiberglass epoxy skin. A lightweight payload canopy cover integrates onto the center wing as an agnostic enclosure for payloads. The payload canopy cover may contain venting holes for the cooling of electronic payloads. The systems may also include common devices such as antennas, GPS, and batteries for use with a wide range of payloads.

Claims

1. A device for use on a small unmanned aerial vehicle (UAV), the device comprising:

a wing with a center wing portion extending over the UAV, the wing having an open cavity and a wing airfoil; and

a cover removably coupled to the open cavity having an aerodynamic shape such that the combination of the cover and the wing yields a payload airfoil of greater thickness than the wing airfoil;

wherein a payload cavity is created from the combination of the volume of the open cavity and from the volume added by the cover.

2. The device of claim 1, wherein the cover further comprises an air intake at the leading edge of the airfoil and an exhaust near the trailing edge of the airfoil.

3. The device of claim 1, wherein the center wing portion further comprises an internal structure.

4. The device of claim 3, wherein the internal structure is used for reinforcing the payload cavity.

5. The device of claim 1, wherein the center wing portion comprises a solid foam core.

6. The device of claim 1, wherein the center wing portion is removably coupled to the body of the UAV.

7. The device in claim 1, wherein the center wing portion further comprises an integrated internal antenna cavity.

8. The device in claim 7, wherein a cable harness electrically links an antenna in the integrated internal antenna cavity to a payload inside the payload cavity.

9. The device in claim 8, wherein the antenna includes a copper ground plane.

10. The device of claim 1, wherein the cover contains an integrated GPS receiver, which is located near the top of the canopy airfoil.

11. A payload cavity for use on an unmanned aerial vehicle (UAV), the payload cavity comprising:

a wing with a center wing portion extending over the UAV, the wing having an open cavity centered along the UAV'"'"'s line of symmetry and a wing airfoil; and

a rigid cover providing an open volume removably coupled to the open cavity such that the open volume and the open cavity are united;

wherein the union of the open volume and the open cavity creates a payload volume and a payload airfoil.

12. The payload cavity of claim 11, wherein the rigid cover further comprises an air intake at the leading edge of the payload airfoil and an exhaust near the trailing edge of the payload airfoil.

13. The payload cavity of claim 11, wherein the center wing portion further comprises an internal structure.

14. The payload cavity of claim 11, wherein the center wing portion comprises a solid foam core.

15. The payload cavity in claim 11, wherein the center wing portion further comprises an integrated internal antenna cavity.

16. The payload cavity in claim 15, wherein a cable harness electrically links an antenna in the integrated internal antenna cavity to a payload inside the open cavity.

17. The payload cavity in claim 16, wherein the antenna includes a copper ground plane.

18. The payload cavity of claim 11, wherein the rigid cover contains an integrated GPS receiver.