Unmanned aerial vehicle with twin-engine fore/AFT configuration and associated systems and methods

• US 9,527,597 B1
• Filed: 01/13/2014
• Issued: 12/27/2016
• Est. Priority Date: 01/11/2013
• Status: Active Grant

• Current Assignee: DroneTech UAV Corporation
• Original Assignee: David Alejandro Arrellano Escarpita, Jaime Sada
• Inventors: Sada, Jaime, Arrellano Escarpita, David Alejandro
• Primary Examiner(s): Sanderson, Joseph W
• Application Number:
  US14/153,721
• Time in Patent Office: 1,079 Days
• US Class Current: 1/1
• CPC Class Codes: B64D 27/08 within, or attached to, fuselages
• CPC Class Codes: B64D 37/04 Arrangement thereof in or on aircraft
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/00 Constructional aspects of UAVs of lift-producing means B64U30/00
• CPC Class Codes: B64U 2101/00 UAVs specially adapted for particular uses or applications
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 60/00 Undercarriages
• CPC Class Codes: B64U 70/00 Launching, take-off or landing arrangements

Abstract

An Unmanned Aerial Vehicle (UAV) for use in military and civilian functions, including a UAV being optimized by utilizing a front and a rearmost engine positioning in addition to an engine operating system for maximum fuel efficiency and performance.

Claims

1. An unmanned aerial vehicle (UAV) comprising:

a fuselage having a longitudinal axis;

a payload bay in the fuselage;

a first engine positioned along the longitudinal axis forward of the payload bay and coupled to a first propeller to drive the first propeller; and

a second engine positioned along the longitudinal axis aft of the payload bay and the first engine, the second engine being coupled to a second propeller to drive the second propeller, wherein the first and second engines are of different types, and wherein one of the engines is a four-cycle engine and the other engine is a two-cycle engine.

2. The UAV of claim 1 wherein the first and second engines have different specific fuel consumption ratings.

3. The UAV of claim 1 wherein one of the engines is lighter than the other.

4. The UAV of claim 1 wherein the first and second engines form a twin-engine configuration.

5. The UAV of claim 1 wherein a center of gravity of the UAV is located within the payload bay.

6. The UAV of claim 1, further comprising a control system configured to shut down one of the first and second engines at cruise altitude.

7. The UAV of claim 6 wherein the other of the first and second engines has a better fuel efficiency than the shut down engine.

8. The UAV of claim 1 wherein the first engine is located at the front-most extreme of the fuselage.

9. The UAV of claim 1 wherein the second engine is located at the rear-most extreme of the fuselage.

10. The UAV of claim 1 wherein the first engine includes a first electrical generator and the second engine includes a second electrical generator.

11. The UAV of claim 1 wherein:

the first and second engines form a twin-engine configuration; and

one of the first engine and the second engine is located at the front-most extreme of the fuselage, and the other is located at the rear-most extreme of the fuselage.

12. An unmanned aerial vehicle (UAV) comprising:

a fuselage having a longitudinal axis;

a payload bay within the fuselage;

a first engine positioned along the longitudinal axis forward of the payload bay;

a second engine positioned along the longitudinal axis aft of the payload bay and the first engine;

a first fuel tank positioned between the first engine and the payload bay;

a second fuel tank positioned between the second engine and the payload bay;

a control system coupled to the first and second engines and configured to shut down one of the first and second engines at cruise altitude; and

wherein;

a center of gravity of the UAV is located within the payload bay;

one of the first engine and the second engine has a two-cycle configuration, a first power capability and a first specific fuel consumption; and

the other of the first engine and the second engine has a four-cycle configuration, a second power capability less than the first power capability, and a second specific fuel consumption lower than the first.

13. The UAV of claim 12 wherein the engine with the two-cycle configuration is lighter than the engine with the four-cycle configuration.

14. A method for operating a unmanned aerial vehicle (UAV), comprising:

directing the UAV to take off under the power of a first engine and a second engine, the UAV including a fuselage having a longitudinal axis, the first and second engines being located along the longitudinal axis, wherein one of the engines is a four-cycle engine and the other engine is a two-cycle engine;

after takeoff, shutting down one of the first and second engines; and

cruising or loitering under the power of the other of the first and second engines.

15. The method of claim 14 wherein shutting down one of the first and second engines includes shutting down the two-cycle engine.

16. The method of claim 14 wherein cruising or loitering includes cruising or loitering under the power of the four-cycle engine.

17. The method of claim 14 wherein the UAV includes a first and second fuel tanks positioned between the first and second engines along the longitudinal axis, and wherein the method further comprises shifting fuel from the first fuel tank to the second fuel tank to control a center of gravity of the UAV.

18. The method of claim 14, further comprising loading a payload bay of the UAV, and wherein a center of gravity of the UAV is located with the payload bay.

19. An unmanned aerial vehicle (UAV) comprising:

a fuselage having a longitudinal axis;

a payload bay in the fuselage;

a first engine positioned along the longitudinal axis forward of the payload bay; and

a second engine positioned along the longitudinal axis aft of the payload bay and the first engine, wherein one of the engines is a four-cycle engine and the other engine is a two-cycle engine.

20. An unmanned aerial vehicle (UAV) comprising:

a fuselage having a longitudinal axis;

a payload bay in the fuselage;

a first engine positioned along the longitudinal axis forward of the payload bay; and

a second engine positioned along the longitudinal axis aft of the payload bay and the first engine, wherein;

the first and second engines form a twin-engine configuration;

one of the first engine and the second engine is located at the front-most extreme of the fuselage, and the other is located at the rear-most extreme of the fuselage;

one of the first engine and the second engine is a two-cycle engine with a first specific fuel consumption; and

the other of the first engine and the second engine is a four-cycle engine with a second specific fuel consumption lower than the first.