ELEVON CONTROL SYSTEM

• US 20120267473A1
• Filed: 09/09/2010
• Published: 10/25/2012
• Est. Priority Date: 09/09/2009
• Status: Active Grant

• Current Assignee: Aerovironment
• Original Assignee: Aerovironment
• Inventors: Miralles, Carlos Thomas, Tao, Tony Shuo, Olson, Nathan, Plumb, Robert Nickerson
• Granted Patent: US 9,108,713 B2
• Time in Patent Office: Days
• US Class Current: 244/38
• 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) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently mounted trailing edges opposed by fuselage-house house deflecting actuator horns (621,622). Embodiments include one or more rudder elements (1045, 1046,1145, 1146,1245, 1345, 1346,1445, 1446,1545, 1546) which may be rotatably attached and actuated by an effector member (1049,1149,1249,1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements.

Claims

1. An aerial vehicle comprising:

a fuselage housing a first fuselage-mounted effector;

a first airfoil comprising a first control surface resiliently mounted to the first airfoil,

wherein the first control surface is opposed by the first fuselage-mounted effector;

a second airfoil, rotatably attached to the fuselage housing; and

a second fuselage-mounted effector disposed within the fuselage housing and extendible in part to engage the second airfoil.

2. The aerial vehicle of claim 1 further comprising:

the fuselage housing a third fuselage-mounted effector; and

a third airfoil comprising a second control surface resiliently mounted to the third airfoil.

3. The aerial vehicle of claim 2 further comprising:

a fourth airfoil, rotatably attached to the fuselage housing.

4. The aerial vehicle of claim 2 further comprising:

a mid-body and wherein the first airfoil and the third airfoil are disposed along the fuselage mid-body.

5. The aerial vehicle of claim 3, the fuselage further comprising:

a tapered aft portion, and wherein the second airfoil and the fourth airfoil are disposed along the tapered aft portion of the fuselage.

6. The aerial vehicle of claim 1 wherein the first fuselage-mounted effector is a first actuator horn extendible via a first fuselage aperture.

7. The aerial vehicle of claim 2 wherein the third fuselage-mounted effector is a second actuator horn extendible via a second fuselage aperture.

8. The aerial vehicle of claim 1 wherein the first resiliently mounted control surface is a trailing edge of the first airfoil articulated at a lineal joint about the first airfoil.

9. The aerial vehicle of claim 1 wherein the aerial vehicle is unmanned during operation.

10. A method of aerial vehicle flight control comprising:

providing a first resiliently mounted control surface opposed by a first fuselage-mounted actuator horn; and

deflecting the first resiliently mounted control surface via the first fuselage-mounted actuator horn based on one or more command signals.

11. An aerial vehicle comprising:

a fuselage, comprising a housing tapering aftward;

a first airfoil, rotatably attached to the fuselage housing; and

an effector member disposed within the fuselage housing and extendible in part to engage the first airfoil.

12. The aerial vehicle of claim 11, wherein the aft portion of the fuselage tapers by an angle defined in part by the first airfoil.

13. The aerial vehicle of claim 12 wherein the first airfoil is resiliently mounted to the fuselage housing.

14. The aerial vehicle of claim 12 wherein the first airfoil is mounted to the fuselage housing via a hinge.

15. The aerial vehicle of claim 13 wherein the first airfoil rotates around an axis and the axis of rotation is canted relative to the longitudinal axis of the fuselage housing.

16. The aerial vehicle of claim 15 wherein the first airfoil is responsive to a translation of the effector member.

17. The aerial vehicle of claim 16 wherein the effector member is extendible laterally relative to the longitudinal axis of the fuselage housing.

18. The aerial vehicle of claim 17 wherein the effector member is engaged by an actuator to effect the angular rotation of the first airfoil.

19. The aerial vehicle of claim 18 wherein the effector member is further extendible from a fuselage aperture.

20. The aerial vehicle of claim 19 wherein the effector member translates in a single axis.

21. The aerial vehicle of claim 14 wherein the axis of rotation is about a hinge-line canted relative to the longitudinal axis of the fuselage housing.

22. The aerial vehicle of claim 21 wherein the first airfoil is responsive to the translation of the effector member.

23. The aerial vehicle of claim 22 wherein the effector member is extendible laterally relative to the longitudinal axis of the fuselage housing.

24. The aerial vehicle of claim 23 wherein the effector member is engaged by an actuator to effect the angular rotation of the first airfoil.

25. The aerial vehicle of claim 24 wherein the effector member is further extendible from a fuselage aperture.

26. The aerial vehicle of claim 25 wherein the effector member translates in a single axis.

27. The aerial vehicle of claim 11 further comprising:

a second airfoil, rotatably attached to the fuselage housing;

wherein the second airfoil opposes the first airfoil;

wherein the aft portion of the fuselage tapers by an angle defined further by the second airfoil;

wherein the first airfoil and the second airfoil abut the opposing ends of the effector member; and

wherein the effector member engages the first airfoil and the second airfoil.

28. The aerial vehicle of claim 27 wherein the first airfoil and the second airfoil move in cooperation with each other.

29. The aerial vehicle of claim 28 wherein the first airfoil and the second airfoil are resiliently mounted to the fuselage housing;

wherein the axis of rotation of the first airfoil and second airfoil are canted relative to a longitudinal axis of the fuselage housing;

wherein the first airfoil and the second airfoil are responsive to the translation of the effector member;

wherein the effector member is extendible laterally relative to the longitudinal axis of the fuselage housing;

wherein the effector member is engaged by an actuator to effect the angular rotation of the first airfoil and the second airfoil;

wherein the effector member is further extendible from a fuselage aperture; and

wherein the effector member translates in a single axis.

30. The aerial vehicle of claim 28 wherein the first airfoil is mounted to the fuselage housing via a hinge;

wherein the axis of rotation is about a hinge-line canted relative to a longitudinal axis of the fuselage housing;

wherein the first airfoil and the second airfoil are responsive to the translation of the effector member;

wherein the effector member is extendible laterally relative to the longitudinal axis of the fuselage housing;

wherein the effector member is engaged by an actuator to effect the angular rotation of the first airfoil and the second airfoil;

wherein the effector member is further extendible from a fuselage aperture; and

wherein the effector member translates in a single axis.