ELEVON CONTROL SYSTEM

• US 20150203201A1
• Filed: 01/08/2015
• Published: 07/23/2015
• Est. Priority Date: 09/09/2009
• Status: Abandoned Application

• Current Assignee: Aerovironment
• Original Assignee: Aerovironment
• Inventors: TAO, TONY SHUO, OLSON, NATHAN, MIRALLES, CARLOS THOMAS, PLUMB, ROBERT NICKERSON
• Application Number:
  US14/592,362
• Publication Number:
  US 20150203201A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 11/00 Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
• CPC Class Codes: B64C 13/18 using automatic pilot
• CPC Class Codes: B64C 13/34 using toothed gearing
• CPC Class Codes: B64C 2009/005 Ailerons
• CPC Class Codes: B64C 3/44 Varying camber
• CPC Class Codes: B64C 3/50 by leading or trailing edge flaps
• 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 5/12 for retraction against or within fuselage or nacelle
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64C 9/08 bodily displaceable
• CPC Class Codes: B64C 9/18 by single flaps
• CPC Class Codes: B64C 9/36 the members being fuselages or nacelles
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/50 Foldable or collapsible UAVs with frangible components B64U20/30
• CPC Class Codes: B64U 2101/15 for conventional or electronic warfare
• CPC Class Codes: B64U 2201/00 UAVs characterised by their flight controls
• CPC Class Codes: B64U 2201/104 using satellite radio beacon positioning systems, e.g. GPS
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/293 : Foldable or collapsible rotors or rotor supports
• CPC Class Codes: B64U 30/40 : Empennages, e.g. V-tails foldable or collapsible UAVs B64U20/50
• CPC Class Codes: B64U 40/10 : for adjusting control surfaces or rotors
• CPC Class Codes: B64U 70/00 : Launching, take-off or landing arrangements
• CPC Class Codes: Y02T 50/10 : Drag reduction

Abstract

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Claims

1. An aerial vehicle, comprising:

a fuselage having an exterior surface, wherein the exterior surface is tapered at an aft portion;

a first rudder surface rotatably disposed about a first hinge, wherein the first hinge extends along the aft portion of the exterior surface; and

a second rudder surface rotatably disposed about a second hinge, wherein the second hinge extends along the aft portion of the exterior surface.

2. The aerial vehicle of claim 1 wherein the first hinge has a canted angle relative to a longitudinal axis of the aerial vehicle between thirty degrees and sixty degrees, and wherein the second hinge has a canted angle relative to the longitudinal axis of the aerial vehicle between thirty degrees and sixty degrees.

3. The aerial vehicle of claim 1 wherein the first rudder surface has a first retracted position disposed along the exterior surface, and wherein the second rudder surface has a second retracted position disposed along the exterior surface.

4. The aerial vehicle of claim 3 wherein the first retracted position of the first rudder surface and the second retracted position of the second rudder surface are on opposite sides of the fuselage.

5. The aerial vehicle of claim 4 wherein the first rudder surface is configured to rotate about the first hinge and into a first deployed position by wind resistance, and wherein the second rudder surface is configured to rotate about the second hinge and into a second deployed position by wind resistance.

6. The aerial vehicle of claim 1 further comprising a guidance processor, wherein the guidance processor is configured to receive one or more inputs and output one or more rudder commands, and wherein the one or more rudder commands is a change in position of at least one of:

the first rudder surface and the second rudder surface.

7. The aerial vehicle of claim 6 wherein the first rudder surface is configured, by the guidance processor, to move independently from the second rudder surface.

8. The aerial vehicle of claim 1 further comprising a foldable propeller configured in a pusher-prop configuration.

9. The aerial vehicle of claim 8 wherein the foldable propeller has a folded position disposed along the exterior surface.

10. The aerial vehicle of claim 1 further comprising an actuator rod disposed in the aft portion of the fuselage.

11. The aerial vehicle of claim 10 further comprising a first aperture and a second aperture, wherein the first aperture and the second aperture are disposed on opposite sides of the fuselage, wherein the actuator rod is operable to extend through the first aperture to engage the first rudder surface, and wherein the actuator rod is operable to extend through the second aperture to engage the second rudder surface.

12. The aerial vehicle of claim 11 wherein the actuator rod is connectable to the first rudder surface by at least one or more of:

a magnet, a clasp, a clip, a flange, a peg, a pin, and a hook and loop fastener.

13. The aerial vehicle of claim 11 wherein the actuator rod is connectable to the second rudder surface by at least one or more of:

a magnet, a clasp, a clip, a flange, a peg, a pin, and a hook and loop fastener.

14. The aerial vehicle of claim 11 wherein each end of the actuator rod is bulbous.

15. The aerial vehicle of claim 11 wherein the length of the actuator rod is less than the distance between the first aperture and the second aperture.

16. The aerial vehicle of claim 11 further comprising an actuator, wherein the actuator is capable of extending the actuator rod about an axis perpendicular to a longitudinal axis of the aerial vehicle.

17. The aerial vehicle of claim 16 wherein the actuator further comprises at least one of:

an electro-mechanical linkage, a gear, a gear assembly, and a worm-gear.

18. The aerial vehicle of claim 11 further comprising a first spring and a second spring, wherein the first spring is configured to rotate the first rudder surface about the first hinge and into a first deployed position, and wherein the second spring is configured to rotate the first rudder surface about the second hinge and into a second deployed position.

19. The aerial vehicle of claim 18 wherein the first deployed position is proximate to the first aperture, and wherein the second deployed position is proximate to the second aperture.

20. A method of operating an aerial vehicle comprising:

rotating a first rudder surface from a first rotation position to a second rotation position about a canted first hinge on a tapered aft exterior surface of a fuselage; and

rotating a second rudder surface from a third rotation position to a fourth rotation position about a canted second hinge on the tapered aft exterior surface of the fuselage.

21. The method of claim 20 wherein rotating the first rudder surface from the first rotation position to the second rotation position further comprises rotating the first rudder surface from a retracted position disposed along the tapered aft exterior surface of the fuselage to a deployed position.

22. The method of claim 20 wherein rotating the second rudder surface from the third rotation position to the fourth rotation position further comprises rotating the first rudder surface from a retracted position disposed along the tapered aft exterior surface of the fuselage to a deployed position.

23. The method of claim 20 further comprising rotating a foldable propeller from a folded position disposed along the tapered aft exterior surface of the fuselage to an engaged position in a pusher-prop configuration.

24. The method of claim 20 further comprising:

extending an actuator rod through one or more actuator holes on the tapered aft exterior surface of the fuselage, wherein the extended actuator rod is configured to engage the first rudder surface; and

rotating, by the extended actuator rod, the first rudder surface from the second rotation position to a fifth rotation position, wherein rotation of the first rudder surface provides yaw control for the aerial vehicle.

25. The method of claim 20 further comprising:

extending an actuator rod through one or more actuator holes on the tapered aft exterior surface of the fuselage, wherein the extended actuator rod is configured to engage the second rudder surface; and

rotating, by the extended actuator rod, the second rudder surface from the fourth rotation position to a sixth rotation position, wherein rotation of the second rudder surface provides yaw control for the aerial vehicle.