Tiltrotor Unmanned Aerial Vehicle

• US 20160272312A1
• Filed: 02/01/2015
• Published: 09/22/2016
• Est. Priority Date: 02/01/2014
• Status: Active Grant

• Current Assignee: Aero Machining LLC
• Original Assignee: Aero Machining LLC
• Inventors: Mallard, Brad
• Granted Patent: US 9,623,967 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 27/28 with forward-propulsion propellers pivotable to act as lifting rotors
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 2101/00 UAVs specially adapted for particular uses or applications
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/64 for parcel delivery or retrieval
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/24 Coaxial rotors
• CPC Class Codes: B64U 30/297 Tilting rotors
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 60/40 foldable or retractable
• CPC Class Codes: G01S 19/13 Receivers

Abstract

The invention is directed toward a UAV having a plurality of rotors position on axles extending longitudinally from a fuselage. The axles articulate the rotors from a vertical position, where the rotors provide lift, to a horizontal position, where the rotors provide thrust. The UAV is configured such that the voltage provided to each rotor may be varied to adjust rotor speed, and thus thrust, independently, giving the UAV enhanced maneuverability.

Claims

1. An unmanned aerial vehicle comprising

a. A fuselage

b. One or more pivotable arms

i. Wherein said one or more pivotable arms have a first end and a second end

ii. Wherein said first end of said one or more pivotable arms are coupled to said fuselage

iii. Wherein said one or more pivotable arms extend transversely from the longitudinal central axis of said fuselage

c. One or more rotor assemblies

i. Wherein each of said one or more rotor assemblies are respectively attached to said second end of said one or more pivotable arms

d. Wherein each of said one or more rotor assemblies are configured to independently pivot from a vertical position, generating a vertical thrust for vertical take-off and landing, to a horizontal position, generating a horizontal thrust for horizontal flight.

2. The unmanned aerial vehicle as in claim 1 further comprising

a. A processor unit

b. A power source

c. Wherein said power source is coupled with said one or more rotor assemblies

d. Wherein said processor unit is coupled with said power source and said one or more rotor assemblies

e. Wherein said processor unit is configured to regulate the voltage provided to each of said one or more rotor assemblies independently from each of said other one or more rotor assemblies.

3. The unmanned aerial vehicle as in claim 1 further comprising

a. A GPS unit

i. Wherein said GPS unit is coupled to said processor unit.

4. The unmanned aerial vehicle as in claim 1 further comprising

a. A transceiver

i. Wherein said transceiver is coupled to said processor unit.

5. The unmanned aerial vehicle as in claim 1 further comprising

a. One or more fixed wings

b. Wherein said one or more fixed wings extend horizontally from said fuselage substantially in line with the longitudinal center line of said fuselage

c. Wherein said one or more fixed wings generate lift when said unmanned aerial vehicle is in horizontal flight.

6. The unmanned aerial vehicle as in claim 5 further comprising

a. One or more rear flaps.

7. The unmanned aerial vehicle as in claim 1 further comprising

a. One or more vertical stabilizers

b. Wherein said one or more vertical stabilizers extend vertically from the surface of said fuselage

c. Wherein said one or more vertical stabilizers are positioned substantially parallel with the longitudinal central axis of said fuselage.

8. The unmanned aerial vehicle as in claim 1 further comprising

a. One or more landing struts

i. Wherein said one or more landing struts are connected to said fuselage.

9. The unmanned aerial as in claim 8

a. Wherein said one or more landing struts are retractable into the fuselage.

10. The unmanned aerial vehicle as in claim 1

a. Wherein said rotor assembly comprises

i. An upper motor

ii. An upper rotor connected to said upper motor

iii. A lower motor

iv. A lower rotor connected to said lower motor

v. Wherein said upper rotor and said lower rotor are substantially parallel

vi. Wherein said upper rotor and said lower rotor are configured to rotate in opposite directions.

11. The unmanned aerial vehicle as in claim 2 further comprising

a. A GPS unit

i. Wherein said GPS unit is coupled to said processor unit.

12. The unmanned aerial vehicle as in claim 11 further comprising

a. A transceiver

i. Wherein said transceiver is coupled to said processor unit.

13. The unmanned aerial vehicle as in claim 12 further comprising

a. One or more landing struts

i. Wherein said one or more landing struts are connected to said fuselage.

14. The unmanned aerial as in claim 13

a. Wherein said one or more landing struts are retractable into the fuselage.

15. The unmanned aerial vehicle as in claim 13 further comprising

a. One or more fixed wings

b. Wherein said one or more fixed wings extend horizontally from said fuselage substantially in line with the longitudinal center line of said fuselage

c. Wherein said one or more fixed wings generate lift when said unmanned aerial vehicle is in horizontal flight.

16. The unmanned aerial vehicle as in claim 15 further comprising

a. One or more rear flaps.

17. The unmanned aerial vehicle as in claim 16 further comprising

a. One or more vertical stabilizers

b. Wherein said one or more vertical stabilizers extend vertically from the surface of said fuselage

c. Wherein said one or more vertical stabilizers are positioned substantially parallel with the longitudinal central axis of said fuselage.

18. The unmanned aerial vehicle as in claim 17

a. Wherein said rotor assembly comprises

i. An upper motor

ii. An upper rotor connected to said upper motor

iii. A lower motor

iv. A lower rotor connected to said lower motor

v. Wherein said upper rotor and said lower rotor are substantially parallel

vi. Wherein said upper rotor and said lower rotor are configured to rotate in opposite directions.

19. The unmanned aerial vehicle as in claim 2

a. Wherein said rotor assembly comprises

i. An upper motor

ii. An upper rotor connected to said upper motor

iii. A lower motor

iv. A lower rotor connected to said lower motor

v. Wherein said upper rotor and said lower rotor are substantially parallel

vi. Wherein said upper rotor and said lower rotor are configured to rotate in opposite directions.

20. The unmanned aerial vehicle as in claim 19 further comprising

a. One or more fixed wings

b. One or more rear flaps

c. Wherein said one or more fixed wings extend horizontally from said fuselage substantially in line with the longitudinal center line of said fuselage

d. Wherein said one or more fixed wings generate lift when said unmanned aerial vehicle is in horizontal flight.