Vertical takeoff and landing unmanned aerial vehicle

Patent metadata

Field	Value
Publication number	US-9694906-B1
Application number	US-201615132107-A
Country	US
Kind code	B1
Filing date	Apr 18, 2016
Priority date	Apr 18, 2016
Publication date	Jul 4, 2017
Grant date	Jul 4, 2017

Abstract

The vertical takeoff and landing unmanned aerial vehicle includes a pair of selectively rotatable ducted fans and a selectively rotatable thrust vectoring nozzle providing vertical takeoff and landing for an unmanned aerial vehicle or a similar type of aircraft. A pair of fixed forward-swept wings are mounted on a rear portion of a fuselage, and a pair of canards are mounted on a top end of a forward portion of the fuselage. The pair of ducted fans are respectively mounted on free ends of the pair of canards, and are selectively rotatable about an axis parallel to a pitch axis of the fuselage. An engine is mounted in the rear portion of the fuselage, and a thrust vectoring nozzle is mounted on the rear portion of the fuselage for directing thrust exhaust from the engine. The thrust vectoring nozzle is selectively rotatable about an axis parallel to the pitch axis.

First claim

I claim:

1. A vertical takeoff and landing unmanned aerial vehicle, comprising:
a fuselage having a top end, a bottom end, and opposed forward and rear portions, the fuselage being elongated along a roll axis thereof;
a pair of fixed forward-swept wings mounted on the rear portion of the fuselage;
a pair of canards mounted on the top end of the forward portion of the fuselage, each canard extending from the forward portion, parallel to the pitch axis, and terminating with a free end;
wherein the canards are positioned above the pair of fixed forward-swept wings with respect to the fuselage;
a nose positioned forward of the pair of canards;
a pair of ducted fans mounted on the free ends of the pair of canards, the ducted fans being selectively rotatable about an axis parallel to a pitch axis of the fuselage;
an engine mounted in the rear portion of the fuselage; and
a thrust vectoring nozzle mounted on the rear portion of the fuselage for directing thrust exhaust from the engine, the thrust vectoring nozzle being selectively rotatable about an axis parallel to the pitch axis of the fuselage,
whereby the ducted fans and the thrust vectoring nozzle may be selectively rotated about an axis parallel to the pitch axis of the fuselage to direct fan exhaust from the ducted fans and the thrust exhaust from the engine downward along a yaw axis of the fuselage for vertical takeoff and landing, and the ducted fans and the thrust vectoring nozzle may be selectively rotated about the pitch axis of the fuselage to direct the fan exhaust from the ducted fans and the thrust exhaust from the engine rearward along the roll axis of the fuselage for horizontal flight.

2. The vertical takeoff and landing unmanned aerial vehicle as recited in claim 1 , further comprising a V-shaped stabilizer mounted on the top end of the rear portion of the fuselage.

3. The vertical takeoff and landing unmanned aerial vehicle as recited in claim 2 , further comprising an air intake duct mounted on the top end of the rear portion of the fuselage for directing air into the engine.

4. The vertical takeoff and landing unmanned aerial vehicle as recited in claim 1 , further comprising forward and rear retractable landing gear mounted on the respective bottom ends of the forward and rear portions of the fuselage.

5. The vertical takeoff and landing unmanned aerial vehicle as recited in claim 1 , wherein the pair of ducted fans are powered by the engine.

6. The vertical takeoff and landing unmanned aerial vehicle as recited in claim 5 , wherein the engine comprises an electric motor.

7. The vertical takeoff and landing unmanned aerial vehicle as recited in claim 1 , wherein the pair of ducted fans are powered by at least one electric motor.

Assignees

• Univ King Saud

Inventors

• Sadek Shereef Aly

Classifications

• B64U50/12

  using turbine engines, e.g. turbojets or turbofans · CPC title

• B64U70/60

  Take-off or landing of UAVs from a runway using their own power · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64U50/14

  ducted or shrouded · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title