UN-MANNED AERIAL VEHICLE

• US 20160009363A1
• Filed: 02/04/2014
• Published: 01/14/2016
• Est. Priority Date: 02/04/2013
• Status: Active Grant

• Current Assignee: Texas A&M University System
• Original Assignee: Texas A&M University System
• Inventors: Valasek, John, May, James Franklin, Beckett, Andrew, Rhodes, Cecil C. Jr.
• Granted Patent: US 9,957,035 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 1/22 Other structures integral with fuselages to facilitate loading , e.g. cargo bays, cranes
• CPC Class Codes: B64C 2211/00 Modular constructions of airplanes or helicopters
• CPC Class Codes: B64C 39/04 having multiple fuselages or tail booms
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/60 UAVs characterised by the material
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

The present invention relates to an aircraft. The aircraft includes a fuselage module for receiving a payload. The fuselage module includes a plurality of internal connections. The aircraft includes a wing module adjustably coupled to the fuselage module and a tail module coupled to the wing module. The wing module may be adjusted relative to the fuselage module to adjust a location of an aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft. A main landing gear may be adjusted relative to the fuselage module to adjust the location of the aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft.

Claims

1. An aircraft comprising:

a fuselage module for receiving a payload, the fuselage module comprising a plurality of internal connections;

a main landing gear adjustably coupled to the fuselage module;

a wing module adjustably coupled to the fuselage module;

a tail module adjustably coupled to the wing module;

wherein the wing module may be adjusted relative to the fuselage module to maintain a pre-determined distance between a location of an aerodynamic center of the aircraft and a location of a center of gravity of the aircraft; and

wherein a location of main landing gear relative to the fuselage module may be adjusted to maintain the pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft.

2. The aircraft of claim 1, comprising a nose landing gear adjustably coupled to the fuselage module;

3. The aircraft of claim 1, comprising a drive motor disposed within a rear aspect of the fuselage module.

4. The aircraft of claim 1, comprising:

a first adjustable coupling disposed on an upper aspect of the fuselage module; and

a second adjustable coupling disposed on an underside of the wing module.

5. The aircraft of claim 4, wherein the first adjustable coupling is intermeshed with the second adjustable coupling.

6. The aircraft of claim 5, comprising a pin securing the first adjustable coupling and the second adjustable coupling.

7. The aircraft of claim 5, wherein the first adjustable coupling and the second adjustable coupling facilitates selective movement of the wing module relative to the fuselage module.

8. The aircraft of claim 1, wherein the tail module comprises a first boom and a second boom.

9. The aircraft of claim 8, wherein the wing module comprises a first aperture and a second aperture.

10. The aircraft of claim 9, wherein the first boom is inserted into the first aperture and the second boom is inserted into the second aperture.

11. The aircraft of claim 1, wherein the tail module is adjustable relative to the wing module.

12. The aircraft of claim 1, wherein the plurality of internal connections comprise a plurality of slot rails disposed generally parallel to an aircraft long axis.

13. The aircraft of claim 12, wherein the plurality of slog rails are T-slot rails.

14. A method of configuring an aircraft, the method comprising:

positioning a payload within a fuselage module;

determining a location of a center of gravity of the aircraft with the payload;

determined a first desired location of a wing module relative to the fuselage module;

connecting the wing module to the fuselage module at the desired location;

adjusting a location of a main landing gear to a second desired location; and

connecting a tail module to the wing module.

15. The method of claim 14, wherein the connecting the wing module comprises intermeshing a first adjustable coupling, disposed on the fuselage module, with a second adjustable coupling, disposed on the wing module.

16. The method of claim 15, wherein the connecting the wing module comprises inserting a pin through the first adjustable coupling and the second adjustable coupling.

17. The method of claim 14, comprising adjusting a location of the wing module relative to the fuselage module.

18. The method of claim 14, wherein the connecting the tail module comprises inserting a first boom into a first aperture located on the wing module and inserting a second boom into a second aperture located on the wing module.

19. The method of claim 14, wherein the positioning comprises securing the payload to a plurality of slot rails.

20. The method of claim 19, wherein the plurality of slot rails are oriented generally parallel to an aircraft long axis.