Multi-mode unmanned aerial vehicle

• US 10,293,932 B2
• Filed: 12/08/2016
• Issued: 05/21/2019
• Est. Priority Date: 06/28/2016
• Status: Active Grant

• Current Assignee: Unmanned X
• Original Assignee: Saeid A. Alzahrani
• Inventors: Alzahrani, Saeid A.
• Primary Examiner(s): Benedik, Justin M
• Application Number:
  US15/372,667
• Publication Number:
  US 20170369162A1
• Time in Patent Office: 894 Days
• CPC Class Codes: B64C 25/22 fluid
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/96 using air
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/14 ducted or shrouded
• CPC Class Codes: B64U 60/50 with landing legs

Abstract

A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.

Claims

1. A multi-mode unmanned aerial vehicle, comprising:

an elongated fuselage having a front end, a rear end with a curved guide slot, a right side, a left side, and a wing-in-ground (WIG) effect bottom;

a right-fixed wing extending from the right side of the elongated fuselage;

a right tilt wing attached at a first side to a free end of the right fixed wing, the right tilt wing being rotatable in a range of 0-135 degrees about a lateral axis of the multi-mode unmanned aerial vehicle;

a right duct attached to a second side of the right tilt wing;

a right winglet attached to the right duct opposite to the right tilt wing;

a left-fixed wing extending from the left side of the elongated fuselage;

a left tilt wing attached at a first side to a free end of the left fixed wing, the left tilt wing being rotatable in a range of 0-135 degrees about the lateral axis of the multi-mode unmanned aerial vehicle;

a left duct attached to a second side of the left tilt wing;

a left winglet attached to the left duct opposite to the left tilt wing;

a tilt tail located within the curved guide slot at the rear end of the elongated fuselage, the tilt tail being rotatable in a range of 0-90 degrees about the lateral axis of the multi-mode unmanned aerial vehicle and within the curved guide slot, wherein the tilt tail includes a vertical stabilizer, a right horizontal stabilizer, and a left horizontal stabilizer;

a rear duct attached to the tilt tail;

a tilting mechanism including

a first set of servo actuators connected via a bevel gear group to a right and left set of horizontally-oriented shafts integrated with the right tilt wing and the left tilt wing, respectively,

a set of pulleys connected to the right and left set of horizontally-oriented shafts, and

a second set of servo actuators connected to a rear shaft integrated with the tilt tail; and

an integrated autonomous flight control system including processing circuitry configured to control flight and navigation of the multi-mode unmanned aerial vehicle and to control the tilting mechanism.

2. The multi-mode unmanned aerial vehicle of claim 1, further comprising:

a plurality of pivotal control surfaces positioned at a top entrance of the right duct,

dual counter-rotating rotors positioned at an underside of the right duct,

an engine centrally located within the right duct,

a plurality of cross stators positioned at a back entrance of the right duct, and

a plurality of stator pivotal control surfaces within each of the cross stators of the right duct.

3. The multi-mode unmanned aerial vehicle of claim 2, further comprising:

a plurality of pivotal control surfaces positioned at a top entrance of the left duct,

dual counter-rotating rotors positioned at an underside of the left duct,

an engine centrally located within the left duct,

a plurality of cross stators positioned at a back entrance of the left duct, and

a plurality of stator pivotal control surfaces within each of the cross stators of the left duct.

4. The multi-mode unmanned aerial vehicle of claim 3, further comprising:

a plurality of pivotal control surfaces positioned at a top entrance of the rear duct,

dual counter-rotating rotors positioned at an underside of the rear duct,

an engine centrally located within the rear duct,

a plurality of cross stators positioned at a back entrance of the rear duct, and

a plurality of stator pivotal control surfaces within each of the cross stators of the rear duct.

5. The multi-mode unmanned aerial vehicle of claim 1, wherein each of the right tilt wing, the left tilt wing, and the tilt tail are configured to rotate for vertical take-off and landing (VTOL), short take-off and landing (STOL), and horizontal take-off and landing (HTOL).

6. The multi-mode unmanned aerial vehicle of claim 1, wherein the WIG-effect bottom includes

a surrounding ring cavity,

at least one bottom stabilizer, and

at least one rear stabilizer.

7. The multi-mode unmanned aerial vehicle of claim 6, wherein the WIG-effect bottom facilitates water landings and cruises over a water surface.

8. The multi-mode unmanned aerial vehicle of claim 1, further comprising:

a slidable landing gear assembly.

9. The multi-mode unmanned aerial vehicle of claim 8, wherein the slidable landing gear assembly includes

a plurality of inner leg members adjustable and slidable within corresponding outer leg members attached to the WIG-effect bottom,

a loading force-sensitive contact sensor attached to a bottom end of each of the inner leg members, and

a foot attached to the bottom end of each of the inner leg members.

10. The multi-mode unmanned aerial vehicle of claim 8, wherein the slidable landing gear assembly includes one of an electric slidable landing gear assembly and a hydraulic slidable landing gear assembly.

11. The multi-mode unmanned aerial vehicle of claim 1, further comprising:

a front container hinged-door assembly configured to house the tilting mechanism and the integrated autonomous flight control system.

12. The multi-mode unmanned aerial vehicle of claim 11, wherein the front container hinged-door assembly includes

two locking pins,

two hinges,

a cooling fan configured to cool the tilting mechanism and the integrated autonomous flight control system, and

an air inlet with a filter.

13. The multi-mode unmanned aerial vehicle of claim 1, further comprising:

a front storage container for one or more of cargo and goods.

14. The multi-mode unmanned aerial vehicle of claim 1, wherein the multi-mode unmanned aerial vehicle includes an autonomously-controlled and gyroscopically-stabilized unmanned aerial vehicle.

15. A multi-mode unmanned aerial vehicle (UAV), comprising:

an elongated fuselage having a front end, a rear end with a curved guide slot, a right side, a left side, and a wing-in-ground (WIG) effect bottom;

a right-fixed wing extending from the right side of the elongated fuselage;

a right tilt wing attached at a first side to a free end of the right fixed wing, the right tilt wing being rotatable in a range of 0-135 degrees about a lateral axis of the multi-mode UAV;

a right duct attached to a second side of the right tilt wing;

a right winglet attached to the right duct opposite to the right tilt wing;

a left-fixed wing extending from the left side of the elongated fuselage;

a left tilt wing attached at a first side to a free end of the left fixed wing, the left tilt wing being rotatable in a range of 0-135 degrees about the lateral axis of the multi-mode UAV;

a left duct attached to a second side of the left tilt wing;

a left winglet attached to the left duct opposite to the left tilt wing;

a tilt tail located within the curved guide slot at the rear end of the elongated fuselage, the tilt tail being rotatable in a range of 0-90 degrees about the lateral axis of the multi-mode UAV and within the curved guide slot, wherein the tilt tail includes a vertical stabilizer, a right horizontal stabilizer, and a left horizontal stabilizer;

a rear duct attached to the tilt tail;

a tilting mechanism including

a first set of servo actuators connected via a bevel gear group to a right and left set of horizontally-oriented shafts integrated with the right tilt wing and the left tilt wing, respectively,

a set of pulleys connected to the right and left set of horizontally-oriented shafts, and

a second set of servo actuators connected to a rear shaft integrated with the tilt tail; and

processing circuitry configured to

control pitch, roll, yaw, speed, and cyclic flight of the multi-mode UAV,

control global navigation of the multi-mode UAV,

control respective engines of the right duct, the left duct, and the rear duct,

control the right tilt wing, the left tilt wing, and the rear tilt tail,

control the first set of servo actuators and the second set of servo actuators, and

control a plurality of onboard sensors of the multi-mode UAV.

16. The multi-mode UAV of claim 15, wherein the plurality of onboard sensors include at least one type of a speed sensor, an altimeter, an air pressure sensor, a static air pressure sensor, a differential air pressure sensor, a magnetometer, a light detection and ranging (LIDAR) sensor, and dual infrared/electro-optical IR/EO sensors.

17. The multi-mode UAV of claim 15, further comprising:

a front container hinged-door assembly configured to house the tilting mechanism and an integrated autonomous flight control system having the processing circuitry.

18. The multi-mode UAV of claim 17, wherein the front container hinged-door assembly includes

two locking pins,

two hinges,

a cooling fan configured to cool the tilting mechanism and the integrated autonomous flight control system, and

an air inlet with a filter.

19. The multi-mode UAV of claim 15, further comprising:

a front storage container configured to carry one or more of cargo, goods, and payloads.

20. The multi-mode unmanned aerial vehicle of claim 15, wherein each of the right duct, the left duct, and the rear duct includes

a plurality of pivotal control surfaces positioned at a top entrance of the respective right, left, and rear ducts,

dual counter-rotating rotors positioned at an underside of the respective right, left, and rear ducts,

an engine centrally located within the respective right, left, and rear ducts,

a plurality of cross stators positioned at a back entrance of the respective right, left, and rear ducts, and

a plurality of stator pivotal control surfaces within each of the cross stators of the respective right, left, and rear ducts.