Unmanned air vehicle

• US 8,146,855 B2
• Filed: 09/03/2008
• Issued: 04/03/2012
• Est. Priority Date: 09/03/2008
• Status: Expired due to Fees

• Current Assignee: Anvar Ismailov, Muhabbat Ismailova
• Original Assignee: Anvar Ismailov, Muhabbat Ismailova
• Inventors: Ismailov, Anvar
• Primary Examiner(s): Collins, Timothy D
• Assistant Examiner(s): Stehle, Jamie S
• Application Number:
  US12/230,638
• Publication Number:
  US 20100051741A1
• Time in Patent Office: 1,308 Days
• Field of Search: 244/63, 244/49, 244/45.R, 244/46, 244/218, 244/219, 244/3.27, 244/3.28, 244/3.29
• US Class Current: 244/49
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2101/15 for conventional or electronic warfare
• CPC Class Codes: B64U 2101/18 for dropping bombs; for firing ammunition
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 70/50 Launching from storage containers, e.g. from submarine missile tubes
• CPC Class Codes: B64U 70/70 Launching or landing using catapults, tracks or rails launching from storage containers B64U70/50
• CPC Class Codes: B64U 80/70 in containers B64U80/60 takes precedence
• CPC Class Codes: B64U 80/86 Land vehicles
• CPC Class Codes: F42B 10/14 using fins spread or deployed after launch, e.g. after leaving the barrel
• CPC Class Codes: F42B 10/64 of fins

Abstract

An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Claims

1. An unmanned air vehicle comprising a fuselage provided with a nose adapted for the incorporation of inter alia surveillance equipment or ordnance, the fuselage being provided with a tail plane with a rudder, to each side of the fuselage is attached a foldable wing adapted to carry further equipment, each wing having a root part affixed to the fuselage and a hinged part hingeably connected to the respective root part to allow the vehicle to form a substantially triangular shape when the hinged parts are folded, each said root part and said hinged part having at least one respective controllable aileron at its trailing edge, each aileron controllable for individual control during outbound flight including the launch phase with the vehicle in the folded triangular shape, a propulsive launch engine, and at least one flight power unit for flight.

2. An unmanned air vehicle according to claim 1 wherein each wing part has controllable flaps at its leading edge, and each flap being adapted in use for individual control during outbound flight including the launch phase.

3. An unmanned air vehicle according to claim 2 further including at least one return power unit for use during the return flight, and a pod for containing the vehicle with the wings folded in the triangular shape, the pod being so constructed as to provide a launch platform for the vehicle.

4. An unmanned air vehicle according to claim 1 wherein each hinged part of respective said wing includes two contiguous parts respective to one another and hinged together such as to give to the wing foldability and a tripartite configuration.

5. An unmanned air vehicle according to claim 4 wherein deployment mechanisms are provided for moving the hinged parts into the flight mode.

6. An unmanned air vehicle according to claim 1 wherein a clamp is provided to retain the wings in the folded position, the clamp being disposed on the tail plane.

7. An unmanned air vehicle according to claim 6 wherein the clamp is accommodated within the tail plane when not in use.

8. An unmanned air vehicle according to claim 1 wherein the wings are hollow, and fuel tanks are accommodated within the wings.

9. An unmanned air vehicle according to claim 1 wherein the propulsive launch engine is a jet engine to be jettisoned in use following launch.

10. An unmanned air vehicle according to claim 3 wherein the flight power unit for flight is a motor-driven propeller powered by a fuel-fired engine.

11. An unmanned air vehicle according to claim 10 wherein a standby electric motor is provided for the propeller.

12. An unmanned air vehicle according to claim 11 wherein a bank of batteries is provided within the fuselage to power the electric motor.

13. An unmanned air vehicle according to claim 10 wherein the propeller is mounted in a propeller guard structure to which the propulsive launch engine is releasably secured.

14. An unmanned air vehicle according to claim 3 wherein the flaps and ailerons are powered by motors actuable by remote control.

15. An unmanned air vehicle according to claim 3 wherein in use the vehicle is launched from within its pod with the wings in the folded condition and during launch the flaps and ailerons are so adapted as to effect flight control as they do during normal flight when the vehicle has reached operating altitude.

16. An unmanned air vehicle according to claim 1 wherein the ordnance mounted in the nose of the fuselage is a cannon provided with cartridge magazines.

17. An unmanned air vehicle according to claim 16 wherein the fuselage is provided with discharge apertures for the ejection of spent cartridges.

18. An unmanned air vehicle according to claim 1 wherein the further equipment located beneath the wings is comprised of missiles.

19. An unmanned air vehicle according to claim 1 wherein the tail end of the fuselage is provided with a hook deployable prior to land.

20. An unmanned aerial system including the unmanned air vehicle according to claim 19 wherein a landing deck is provided and incorporates a slideway in which is reciprocally mounted a detent adapted for interengagement with the hook upon landing, the detent being affixed to an arresting wire connected to a braking mechanism.

21. An unmanned aerial system according to claim 20 wherein the landing deck is angularly orientable.

22. An unmanned air vehicle according to claim 3 wherein the pod for containing the vehicle is provided with support and guide rollers adapted to retain the vehicle in a desired path in use upon launch.

23. An unmanned air vehicle according to claim 3 wherein the return power unit for return flight is at least one jet engine.