METHODS AND APPARATUS FOR TRANSFORMING UNMANNED AERIAL VEHICLE

• US 20100025543A1
• Filed: 10/31/2008
• Published: 02/04/2010
• Est. Priority Date: 11/02/2007
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: KINSEY, LLOYD E., Kranking, Patrick
• Granted Patent: US 8,157,203 B2
• Time in Patent Office: Days
• US Class Current: 244/7.A
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 50/10 Propulsion rotors specially adapted for rotorcraft or VTOL B64U30/20
• 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 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20

Abstract

Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Claims

1. An aircraft, comprising:

a fuselage comprising a forward end and an aft end;

a first lifting surface with a first leading edge, wherein the first lifting surface is rotatably connected to the fuselage;

a second lifting surface with a second leading edge, wherein the second lifting surface is rotatably connected to the fuselage;

wherein

the first and second lifting surfaces are configured to;

rotate prior to at least one of takeoff and landing such that each of the first and second leading edges forms an angle of between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage when the fuselage is disposed in a substantially vertical position; and

rotate after takeoff such that each of the first and second leading edges is positioned toward the forward end of the fuselage.

2. An aircraft according to claim 1, wherein the first lifting surface and the second lifting surface form a delta wing when the first and second leading edges are positioned toward the forward end of the fuselage.

3. An aircraft according to claim 1, wherein the first lifting surface and the second lifting surface rotate in opposite directions relative to each other.

4. An aircraft according to claim 1, wherein the first leading edge and the second leading edge face substantially opposite directions during at least one of takeoff and landing.

5. An aircraft according to claim 1, wherein the fuselage is configured to engage a launch system adapted to rotate the fuselage about its longitudinal axis prior to launch.

6. An aircraft according to claim 5, wherein the launch system is mounted on a mobile entity.

7. An aircraft according to claim 1, further comprising a propulsion system, wherein the propulsion system comprises at least one propulsive element connected to each of the first lifting and second lifting surfaces.

11. An unmanned aircraft according to claim 7, wherein the at least two wings are configured to rotate in opposite directions relative to each other.

8. An unmanned aircraft, comprising:

a fuselage comprising a forward end and an aft end; and

at least two wings rotatably connected to the fuselage, wherein;

each of the at least two wings comprises a leading edge; and

each of the at least two wings is configured to;

rotate prior to takeoff such that each of the first and second leading edges forms an angle between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage when the fuselage is disposed in a substantially vertical position; and

rotate after takeoff such that each of the first and second leading edges is positioned toward the forward end of the fuselage.

9. An unmanned aircraft according to claim 8, wherein the at least two wings are configured to rotate prior to landing such that each of the leading edges forms an angle of between thirty and one hundred fifty degrees relative to the longitudinal axis of the fuselage.

10. An unmanned aircraft according to claim 8, wherein the at least two wings form a delta wing aircraft when the two leading edges are positioned toward the forward end of the fuselage.

12. An unmanned aircraft according to claim 8, wherein the two leading edges face substantially opposite directions from each other during at least one of takeoff and landing

13. An unmanned aircraft according to claim 8, wherein the fuselage is configured to engage a launch system adapted to rotate the fuselage about its longitudinal axis prior to launch.

14. An unmanned aircraft according to claim 13, wherein the launch system is mounted on a mobile entity.

15. An unmanned aircraft according to claim 8, further comprising a propulsion system, wherein the propulsion system comprises at least one propulsive element connected to each of the first lifting and second lifting surfaces.

16. A method of flying an unmanned aircraft, comprising:

placing a fuselage comprising a forward end and an aft end in a substantially vertical position;

rotating at least two wings rotatably connected to the fuselage to an angle of between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage, wherein each of the at least two wings comprise a leading edge;

spinning the fuselage about its longitudinal axis such that the at least two wings produce enough lift to result in a substantially vertical flight of the unmanned aircraft;

rotating the at least two wings such that each of the leading edges is positioned towards the forward end of the fuselage; and

transitioning the unmanned aircraft into fixed-wing forward flight.

17. A method of flying an unmanned aircraft according to claim 16, further comprising:

pitching the unmanned aircraft upwards during forward flight to a stall position resulting in a tail slide;

rolling the aircraft during the upward pitch;

rotating the at least two wings to an angle of between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage after the roll is initiated; and

controlling the rate of descent of the unmanned aircraft during the tail slide by repositioning the at least two wings in order to continuously produce a lifting force until the unmanned aircraft lands.

18. A method of flying an unmanned aircraft according to claim 16, further comprising:

placing the unmanned aircraft into a dive;

rolling the aircraft during the dive;

rotating the at least two wings to an angle of between thirty and one hundred fifty degrees relative to a longitudinal axis of the fuselage after the roll is initiated; and

controlling the rate of descent of the unmanned aircraft during the dive by repositioning the at least two wings in order to continuously produce a lifting force until the unmanned aircraft lands.

19. A method of flying an unmanned aircraft according to claim 16, wherein the at least two wings are configured to rotate in opposite directions relative to each other.

20. A method of flying an unmanned aircraft according to claim 16, wherein placing the fuselage in a substantially vertical position comprises positioning a portion of the fuselage in a launch system configured to rotate the fuselage about its longitudinal axis.

21. A method of flying an unmanned aircraft according to claim 20, wherein the launch system is configured for installation in a mobile entity.

22. A method of flying an unmanned aircraft according to claim 16, wherein the spinning of the fuselage is controlled by a propulsion system attached to each of the at least two wings.