Elevon control system

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.

What is claimed is: 
     
         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.