Annular airborne vehicle

• US 8,328,131 B2
• Filed: 05/08/2012
• Issued: 12/11/2012
• 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:
  US13/466,343
• Publication Number:
  US 20120256043A1
• Time in Patent Office: 217 Days
• Field of Search: 244/34.A, 244/12.6, 244/12.2, 244/45.R
• US Class Current: 244/34.A
• 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.

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, wherein the wing-body carries two or more rudders on its left side and two or more rudders on its right side and wherein the wing-body is formed with a slot between each adjacent pair of rudders.

2. The vehicle of claim 1 wherein the wing body carries three or more rudders on its left side and three or more rudders on its right side.

3. The vehicle of claim 1 wherein each slot is flared.

4. The vehicle of claim 1 wherein the wing-body has a projected planform 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.

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

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

7. The vehicle of claim 1 wherein each rudder houses a secure linkage that bonds with upper and lower sections of said wing-body to ensure structural integrity, and to allow for rotation within a prescribed arc about a vertical axis, where the arc is constrained to less than ±

30°

.

8. The vehicle of claim 1 wherein the wing-body has upper and lower sections, and wherein the vehicle further comprises two elevator elements and two aileron elements on each of the upper and lower sections.

9. 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.

10. The vehicle of claim 9 wherein the wing-body appears swept forward when viewed in plan, and swept backward when viewed in elevation.

11. The vehicle of claim 9 wherein the wing-body has a leading edge with two or more noses, and a trailing edge with two or more tails.

12. The vehicle of claim 11 wherein the noses are rotationally offset in relation to the tails.

13. The vehicle of claim 9 wherein at least part of the leading and/or trailing edge of the wing-body follows a substantially helical curve.

14. The vehicle of claim 1 wherein the wing-body is evolved from an aerofoil profile as a body of revolution around the wing-body axis.

15. The vehicle of claim 14 wherein the aerofoil profile has symmetrical upper and lower surfaces.

16. The vehicle of claim 1 wherein the two or more rudders on its left side are spaced apart from each other in a fore-and-aft direction parallel with the wing-body axis, and wherein the two or more rudders on its right side are spaced apart from each other in the fore-and-aft direction parallel with the wing-body axis.