Elevon control system
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.
1 . An aerial vehicle, comprising:
an actuator rod, wherein the actuator rod is operable to extend through a first aperture to engage a first rudder surface, and wherein the actuator rod is operable to extend through a second aperture to engage a second rudder surface,
wherein the first rudder surface has a first retracted position disposed along an exterior surface, and wherein the second rudder surface has a second retracted position disposed along the exterior surface.
2 . The aerial vehicle of claim 1 , further comprising:
the first rudder surface configured to rotate towards a first deployed position.
3 . The aerial vehicle of claim 2 , further comprising:
the second rudder surface configured to rotate towards a second deployed position.
4 . The aerial vehicle of claim 3 , wherein the first rudder surface is rotatably disposed about a first hinge, and wherein the first rudder surface is configured to rotate about the first hinge towards a first deployed position.
5 . The aerial vehicle of claim 4 , wherein the second rudder surface is rotatably disposed about a second hinge, and wherein the second rudder surface is configured to rotate about the second hinge towards a second deployed position.
6 . The aerial vehicle of claim 5 , wherein the first hinge extends along an aft portion of the exterior surface, and wherein the second hinge extends along the aft portion of the exterior surface.
7 . The aerial vehicle of claim 6 , 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 the first deployed position, and wherein the second spring is configured to rotate the second rudder surface about the second hinge and into the second deployed position.
8 . The aerial vehicle of claim 7 , 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.
9 . The aerial vehicle of claim 6 , wherein the first hinge has a canted angle relative to a longitudinal axis of the aerial vehicle.
10 . The aerial vehicle of claim 6 , further comprising: a fuselage having the exterior surface, wherein the actuator rod is disposed in the aft portion of the fuselage, and wherein the first aperture and the second aperture are disposed on opposite sides of the fuselage.
11 . The aerial vehicle of claim 6 , wherein the exterior surface is tapered at the aft portion.
12 . The aerial vehicle of claim 6 , wherein the first rudder surface is configured to rotate about the first hinge from a stored position against the aft portion to the first deployed position.
13 . The aerial vehicle of claim 12 , wherein the first rudder surface is configured to rotate about the first hinge from the stored position to the first deployed position in response to dynamic pressure on the first rudder surface, wherein the second rudder surface is configured to rotate about the second hinge towards the second deployed position in response to dynamic pressure on the second rudder surface, wherein the extended actuator rod is configured to rotate the first rudder surface, wherein rotation of the first rudder surface provides yaw control for the aerial vehicle, wherein the extended actuator rod is configured to rotate the second rudder surface, and wherein rotation of the second rudder surface provides yaw control for the aerial vehicle.
14 . The aerial vehicle of claim 6 , wherein the first rudder surface is configured to rotate about the first hinge and into the first deployed position by at least one of: wind resistance and a resiliently mounted force, and wherein the second rudder surface is configured to rotate about the second hinge and into the second deployed position by at least one of: wind resistance and a resiliently mounted force.
15 . 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, 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, and wherein the first rudder surface is configured, by the guidance processor, to move independently from the second rudder surface.
16 . The aerial vehicle of claim 1 , 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, and 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.
17 . The aerial vehicle of claim 1 , wherein each end of the actuator rod is bulbous.
18 . The aerial vehicle of claim 1 , wherein the length of the actuator rod is less than a distance between the first aperture and the second aperture.
19 . The aerial vehicle of claim 1 , 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, wherein the actuator further comprises at least one of: an electro-mechanical linkage, a gear, a gear assembly, and a worm-gear.