Annular airborne vehicle

• US 8,262,016 B2
• Filed: 04/16/2008
• Issued: 09/11/2012
• Est. Priority Date: 04/18/2007
• Status: Expired due to Fees

• Current Assignee: GO Science Group Ltd.
• Original Assignee: GO Science, Ltd. (Thalassa Holdings Ltd.)
• Inventors: Gosling, Harry George Dennis
• Primary Examiner(s): Ellis, Christopher P
• Application Number:
  US12/594,719
• Publication Number:
  US 20100044496A1
• Time in Patent Office: 1,609 Days
• Field of Search: 244/36, 244/45.R, 244/45.A, 244/199.1, 244/130, 244/52, 244/56, 244/55
• US Class Current: 244/12.2
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 39/062 having annular wings
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/14 ducted or shrouded
• CPC Class Codes: B64U 50/18 Thrust vectoring
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis. A direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device and/or a magnitude of thrust of the first propulsion device can be adjusted independently of the magnitude of thrust of the second propulsion device. In certain embodiments the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing position at right angles to the first viewing angle.

Claims

1. An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends;

and a propulsion system comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device which is mounted to the wing-body, positioned on a second side of the plane including the wing-body axis, and operable independently of the first propulsion device, wherein a direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device.

2. The vehicle of claim 1 wherein the direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device by rotating the propulsion device.

3. The vehicle of claim 1 wherein each propulsion device comprises a thrust generator and a plurality of ducts arranged to receive propulsion gas from thrust generator, and wherein the direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device by adjusting the flow of propulsion gas in the ducts.

4. The vehicle of claim 3 wherein each duct is contained within the wing-body.

5. The vehicle of claim 1 wherein a thrust vector of each propulsion device can be adjusted between a first configuration in which the thrust vectors are co-directed and a second configuration in which the thrust vectors are contra-directed.

6. The vehicle of claim 1 wherein at least part of the wing-body is swept with respect to the wing-body axis.

7. The vehicle of claim 6 wherein the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing position at right angles to the first viewing angle.

8. The vehicle of claim 7 wherein the outer wing-body appears swept forward when viewed in elevation, and swept backward when viewed in plan.

9. The vehicle of claim 1 wherein the first propulsion device is positioned on a first side of a vertical plane including the wing-body axis, and the second propulsion device is positioned on a second side of the vertical plane including the wing-body axis.

10. The vehicle of claim 1 further comprising a controller device which is configured to independently operate the propulsion devices by issuing respective control signals to the propulsion devices.

11. An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends, The vehicle of claim 1 wherein the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing angle at right angles to the first viewing angle.

12. The vehicle of claim 11 wherein the wing-body appears swept forward when viewed in plan, and swept backward when viewed in elevation.

13. The vehicle of claim 11 wherein the wing-body has a leading edge with two or more noses, and a trailing edge with two or more tails.

14. The vehicle of claim 13 wherein the noses are rotationally offset in relation to the tails.

15. The vehicle of claim 11 wherein at least part of the leading and/or trailing edge of the wing-body follows a substantially helical curve.

16. An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends, The vehicle of claim 1 wherein the wing-body carries at least one rudder on its left side and at least one rudder its right side.

17. The vehicle of claim 16 wherein the wing body carries two or more rudders on its left side and two or more rudders on its right side.

18. The vehicle of claim 17 wherein the wing-body is formed with a slot between each adjacent pair of rudders.

19. The vehicle claim 1 wherein the wing-body has a projected platform area S, and a maximum outer diameter B normal to the wing-body axis, and wherein the ratio B2/S is greater than 0.5.

20. The vehicle of claim 1 further comprising three or more undercarriage elements for providing stability during take-off and landing operations.

21. The vehicle of claim 1 further comprising an energy source housed at least partially inside the outer wing-body.