Vertical takeoff and landing unmanned aircraft system

• US 10,059,442 B2
• Filed: 05/25/2016
• Issued: 08/28/2018
• Est. Priority Date: 07/10/2015
• Status: Active Grant

• Current Assignee: Draganfly Innovations Inc. (Frontier Energy Corp.)
• Original Assignee: Zenon Dragan
• Inventors: Olm, Orville, Dragan, Zenon
• Primary Examiner(s): Green, Richard R
• Application Number:
  US15/164,718
• Publication Number:
  US 20170008625A1
• Time in Patent Office: 825 Days
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 39/12 Canard-type aircraft
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/30 for safety, e.g. with frangible components rotor guards B64U30/299
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• 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 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 40/20 for in-flight adjustment of the base configuration
• CPC Class Codes: B64U 50/14 ducted or shrouded
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20
• CPC Class Codes: B64U 80/00 Transport or storage specially adapted for UAVs
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.

Claims

1. A vertical takeoff and landing unmanned aircraft system (VTOL UAS), comprising:

a center wing including a fuselage, the fuselage configured for receiving and removably coupling with a removable payload pod;

a left power pod coupled to a left tip of the center wing, the left power pod having a left power pod stand;

a right power pod coupled to a right tip of the center wing, the right power pod having a right power pod stand;

a left foldable wing rotatably coupled to the left power pod, the left foldable wing having a left wing stand coupled with a left wing tip of the left foldable wing, the left foldable wing including a left aileron;

a right foldable wing rotatably coupled to the right power pod, the right foldable wing having a right wing stand coupled with a right wing tip of the right foldable wing, the right foldable wing including a right aileron;

the VTOL UAS having a lateral axis, a vertical axis and a longitudinal axis;

a trailing edge of each of the left wing stand, the right wing stand, the left power pod stand and the right power pod stand being longitudinally equal;

a canard boom removably coupled to a leading edge of the fuselage;

a control power pod coupled with a leading edge of the canard boom, the control power pod configured for vectoring a thrust produced by the control power pod;

the left power pod, the right power pod, and the control power pod configured for providing a combined thrust greater than the weight of the VTOL UAS;

the canard boom extending longitudinally from the fuselage to the control power pod;

a canard coupled with the control power pod;

the VTOL UAS configured for a powered flight regime in a powered flight configuration, the powered flight configuration a substantially linear lateral wing configuration including a substantially linear lateral alignment of the center wing, the left foldable wing and the right foldable wing along the lateral axis;

the VTOL UAS configured for a VTOL flight regime in a VTOL configuration, the VTOL configuration including a folded wing configuration wherein each of the left foldable wing and the right foldable wing is rotated in an equal clock direction about the longitudinal axis to an angle in which the left wing stand and the right wing stand substantially align with the fuselage along the vertical axis;

the VTOL UAS configured for maintaining;

a stationary nose up position on a landing surface while in the VTOL configuration;

a takeoff in the VTOL flight regime while in the VTOL configuration;

a steady state hover in the VTOL flight regime;

a transition from the VTOL configuration to the powered flight configuration during the takeoff;

a transition from the VTOL flight regime to the powered flight regime;

a steady state flight in the powered flight regime;

a transition from the powered flight regime to the VTOL flight regime;

a transition from the powered flight configuration to the VTOL configuration; and

a landing in the VTOL flight regime while in the VTOL configuration.

2. The VTOL UAS of claim 1, wherein each of the left power pod, the right power pod, and the control power pod are comprised of one of a ducted fan and a ducted propeller engine enclosed within a cylindrical duct, each cylindrical duct configured as a lifting airfoil during the powered flight regime.

3. The VTOL UAS of claim 1, wherein the left foldable wing and the right foldable wing have a mean aerodynamic chord (MAC) of approximately six inches, the center wing has a MAC of approximately eight inches, and each of the left and right foldable wings and the center wing is comprised of a an airfoil having a thickness of approximately 7.3% MAC at approximately 30% chord and a maximum camber of approximately 3.9% MAC at approximately 45% chord.

4. The VTOL UAS of claim 1, wherein the center wing, the left foldable wing, and the right foldable wing present a high aspect ratio of one of greater than 20 and approximately 24 while in the powered flight configuration.

5. The VTOL UAS of claim 1, wherein the powered flight regime includes lift produced by the left foldable wing, the right foldable wing, and the center wing and further includes thrust produced by each of the left power pod, the right power pod and the control power pod, and wherein the VTOL flight regime includes vertical thrust and lift produced by each of the left power pod, the right power pod and the control power pod.

6. The VTOL UAS of claim 1, further including at least four vectored thrust vanes coupled to a trailing edge of the control power pod and configured for powered displacement to vector the thrust from the control power pod, and further including at least one ducteron coupled to a trailing edge of each of the left power pod and the right power pod.

7. The VTOL UAS of claim 1, wherein the control power pod is articulatingly coupled with the leading edge of the canard boom and is configured for angular displacement from the longitudinal axis of the VTOL UAS.

8. The VTOL UAS of claim 7, wherein the control power pod articulatingly coupled with a leading edge of the canard boom further includes at least four vectored thrust vanes coupled to a trailing edge of the control power pod and configured for powered displacement to angularly displace the control power pod from the longitudinal axis to 1) vector the thrust from the control power pod, and 2) change an angle of attack of the canard.

9. The VTOL UAS of claim 7, wherein the control power pod articulatingly coupled with a leading edge of the canard boom further includes at least four servo tabs integrated with a trailing edge of the at least four vectored thrust vanes, the at least four servo tabs configured to displace the at least four vectored thrust vanes.

10. The VTOL UAS of claim 7, wherein the control power pod coupled with a leading edge of the canard boom further includes a powered articulating system configured for angularly displacing the control power pod from the longitudinal axis.

11. The VTOL UAS of claim 1, further including an autopilot configured for receiving an input from at least one of an offboard controller, an onboard memory and processor, an onboard pitot static system, an onboard positioning system, and an onboard accelerometer, the autopilot further configured for controlling the thrust of each of the power pods, displacing each of the ailerons and one or more ducterons, and displacing the control power pod and canard to maintain controlled flight in each of the powered flight regime and the VTOL flight regime.

12. The VTOL UAS of claim 1, wherein the VTOL UAS is further configured for an assisted takeoff in the powered flight configuration via at least one of a catapult device, a removable wheel configuration, a launch from a specific above ground level altitude, and a removable skid system.

13. The VTOL UAS of claim 1, further including a disassembled configuration wherein the left foldable wing and the right foldable wing are rotated about the longitudinal axis to a position proximal to the fuselage, and the canard boom removably coupled to the leading edge of the fuselage is removed.

14. A method for launching a vertical takeoff and landing (VTOL) unmanned aircraft system (UAS), comprising:

maintaining a stationary nose up position on a landing surface while in a VTOL configuration, the VTOL configuration including a folded wing configuration wherein each of a left foldable wing and a right foldable wing is rotated in an equal clock direction about a longitudinal axis to an angle in which a left wing stand and a right wing stand substantially align with a fuselage along a vertical axis;

launching in a VTOL flight regime while in the VTOL configuration;

hovering while in the VTOL flight regime;

transitioning from the VTOL configuration to a powered flight configuration during the launching, the powered flight configuration a substantially linear lateral wing configuration including a substantially linear lateral alignment of a center wing, the left foldable wing and the right foldable wing along a lateral axis;

transitioning from the VTOL flight regime to a powered flight regime;

maintaining a steady state flight in the powered flight regime;

transitioning from the powered flight regime to the VTOL flight regime;

transitioning from the powered flight configuration to the VTOL configuration; and

landing in the VTOL flight regime while in the VTOL configuration.

15. The method for launching a VTOL UAS of claim 14, wherein the launching in a VTOL flight regime further comprises a controlled vertical takeoff using a constant thrust from a left power pod and a right power pod, and vectored thrust from a control power pod, the left power pod coupled to a left tip of the center wing, the left power pod having a left power pod stand, the right power pod coupled to a right tip of the center wing, the right power pod having a right power pod stand, and a control power pod is coupled with a leading edge of a canard boom, the control power pod configured for vectoring a thrust produced by the control power pod.

16. The method for launching a VTOL UAS of claim 14, wherein transitioning from the VTOL configuration to a powered flight configuration during the launching further comprises rotating the left foldable wing and the right foldable wing from the VTOL configuration to the powered flight configuration.

17. The method for launching a VTOL UAS of claim 15, wherein transitioning from the VTOL flight regime to a powered flight regime further comprises a nose down moment of a vectored thrust from the control power pod and an increase in airspeed from approximately zero to above a stall speed of the VTOL UAS.

18. The method for launching a VTOL UAS of claim 14, wherein transitioning from the powered flight regime to the VTOL flight regime further comprises a deep stall of the VTOL UAS and a decrease in airspeed from above the stall speed of the VTOL UAS to approximately zero.

19. The method for launching a VTOL UAS of claim 14, wherein transitioning from the powered flight configuration to the VTOL configuration further comprises rotating each of the left foldable wing and the right foldable wing from the powered flight configuration to the VTOL configuration.

20. The method for launching a VTOL UAS of claim 14, wherein landing in the VTOL flight regime while in the VTOL configuration further comprises a nose up attitude of the VTOL UAS and a nose up descent to the stationary nose up position on the landing surface.