ELEVON CONTROL SYSTEM

• US 20160185445A1
• Filed: 07/10/2015
• Published: 06/30/2016
• Est. Priority Date: 09/09/2009
• Status: Active Grant

• Current Assignee: Aerovironment
• Original Assignee: Aerovironment
• Inventors: PLUMB, ROBERT NICKERSON, OLSON, NATHAN, MIRALLES, CARLOS THOMAS, TAO, TONY SHUO
• Granted Patent: US 10,696,375 B2
• 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 system, comprising:

a fuselage;

a first pair of airfoils rotatably attached to the fuselage at a forward pivot point;

a second pair of airfoils rotatably attached to the fuselage at an aft pivot point; and

an aft positioned forward-folding propeller coupled to the fuselage;

wherein the first pair of airfoils and second pair of airfoils are rotatable to a retracted position that is aligned with a longitudinal axis of the fuselage.

2. The aerial vehicle of claim 1, wherein the fuselage and aft positioned forward-folding propeller coupled to the fuselage are disposed within a launcher tube.

3. The system of claim 1, wherein the first pair of airfoils are rotatably attached to the fuselage at a forward coaxial pivot point.

4. The system of claim 1, wherein the second pair of airfoils are rotatably attached to the fuselage at an aft coaxial pivot point.

5. The system of claim 1, wherein at least one of the first and second pair of airfoils have port and starboard airfoils having constant chords.

6. The system of claim 5, wherein the constant chords have a length that approximates the maximum width of the fuselage.

7. The system of claim 1, wherein each airfoil of the first pair of airfoils further comprises a respective resiliently mounted control surface, wherein each of the respective control surfaces is articulated at a respective lineal joint about its respective airfoil.

8. The system of claim 7, wherein each respective resiliently mounted control surface is a trailing edge control surface.

9. The system of claim 8, further comprising:

a first actuator horn disposed in the fuselage, the first actuator horn extendible via a first fuselage aperture, wherein the first actuator horn is extendible to oppose one of the resiliently mounted control surfaces.

10. The system of claim 9, wherein the first fuselage housing aperture is located on a bottom of the fuselage, and wherein the first actuator horn is extendible through the first fuselage housing aperture to contact a top surface of one of the respective resiliently mounted control surfaces.

11. An aerial vehicle system, comprising:

a fuselage;

a first pair of airfoils rotatably attached to the fuselage at a forward pivot point; and

a second pair of airfoils rotatably attached to the fuselage at an aft pivot point;

wherein at least one of the first and second pair of airfoils have port and starboard airfoils having constant chords.

12. The system of claim 11, wherein the constant chords have a length that approximates the maximum width of the fuselage.

13. The system of claim 11, further comprising:

an aft positioned forward-folding propeller coupled to the fuselage.

14. The system of claim 13, wherein the first pair of airfoils and second pair of airfoils and aft positioned forward-folding propeller are rotatable to a retracted position that is approximately aligned along a longitudinal axis of the fuselage.

15. The system of claim 11, wherein each airfoil of the first pair of airfoils further comprises a respective resiliently mounted control surface, wherein each of the respective control surfaces is articulated at a respective lineal joint about its respective airfoil.

16. The system of claim 15, wherein each respective resiliently mounted control surface is a trailing edge control surface.

17. The system of claim 16, further comprising:

a first actuator horn disposed in the fuselage, the first actuator horn extendible via a first fuselage aperture, wherein the first actuator horn is extendible to oppose one of the resiliently mounted control surfaces.

18. The system of claim 17, wherein the first fuselage housing aperture is located on a bottom of the fuselage, and wherein the first actuator horn is extendible through the first fuselage housing aperture to contact a top surface of one of the respective resiliently mounted control surfaces.

19. The system of claim 11, wherein the first pair of airfoils is operable to rotate aft into a deployed position.

20. The system of claim 19, wherein the second pair of airfoils is operable to rotate forward into a deployed position.

21. An aerial vehicle system, comprising:

a launch tube;

a fuselage disposed inside the launch tube;

a first pair of airfoils, a proximal portion of each of the first pair of airfoils disposed in a stacked arrangement and rotatably attached at a forward pivot point at the exterior surface; and

a second pair of airfoils, a proximal portion of each of the second pair of airfoils rotatably attached at an aft pivot point;

wherein the first pair of airfoils and second pair of airfoils are disposed in the launch tube and in a retracted position that is aligned with a longitudinal axis of the fuselage.

22. The system of claim 21, further comprising:

an aft positioned forward-folding propeller coupled to the fuselage.

23. They system of claim 22, wherein each airfoil of the first pair of airfoils further comprises a respective resiliently mounted control surface, wherein each of the respective control surfaces is articulated at a respective lineal joint about its respective airfoil.

24. The system of claim 21, wherein the first pair of airfoils is operable to rotate aft into a deployed position.

25. The system of claim 24, wherein the second pair of airfoils is operable to rotate forward into a deployed position.