Fin control actuation system
A mechanism for steering and maneuvering an airborne body comprised of at least one actuator comprising an electric motor having a first axis, and a gear transmission for transmitting power from the electric motor to an angular motion axis of a fin that has an angular motion around a second axis to steer the airborne body, and wherein the mechanism is characterized in that the gear transmission is a beveloid gear type of transmission, an airborne body that comprised the mechanism, and a method for achieving the desired flight path of an airborne body implementing the mechanism.
1 . A mechanism for steering and maneuvering an airborne body comprising:
a plurality of actuators arranged circumferentially about a longitudinal central axis of the airborne body, each actuator comprising: an electric motor having a first axis, and
a gear transmission for transmitting power from the electric motor to an angular motion axis of a respective fin coupled to the actuator to steer the airborne body by aerodynamic maneuvering or Thrust Vector Control (TVC), wherein the gear transmission is a beveloid gear transmission, wherein the beveloid gear transmission transmits power from the electric motor to the fin, while the first axis of the motor is not parallel to the angular motion axis of the fin, but is positioned to create an angle between the two axes.
2 . A Fin Control Actuation System (FCAS) assembly comprising the mechanism for steering and maneuvering an airborne body of claim 1 , the airborne body having a rocket propulsion system along its central longitudinal axis.
3 . The FCAS assembly of claim 2 , wherein the plurality of actuators is a circumferential array of four actuators.
4 . The FCAS assembly of claim 2 , wherein the FCAS assembly comprises an apparatus having a toroidal ring-like cross-section configuration, wherein the plurality of actuators is installed in the apparatus, the apparatus is adapted for installation around a rear section of a missile motor of a rocket propulsion system such that the apparatus encompasses the rear section of the missile motor.
5 . The FCAS assembly of claim 4 wherein the plurality of actuators is packaged in one plane perpendicular to the central axis of the airborne body.
6 . An airborne body that comprises the mechanism for steering and maneuvering of claim 1 .
7 . A method of achieving the desired flight path of an airborne body having the mechanism of claim 1 by means of the respective fins of each actuator that move in the desired direction and to the extent required for achieving the desired flight path of the airborne body by aerodynamic maneuvering or Thrust Vector Control (TVC), the method comprising packaging the airborne body with an assembly comprised of the beveloid gear transmissions of each actuator as a means for transferring power from the electric motors in the assembly to the angular motion axes of the fins of the airborne body.
8 . The method of claim 7 , further comprising steering the airborne body by transferring powers, as required, from the electric motors of the assembly to the angular motion axes of the fins of the airborne body through the transmissions of beveloid gear type to change the position of the fins in an angular motion, thereby obtaining the desired flight path of the airborne body.
9 . The mechanism of claim 1 , wherein the plurality of actuators is packaged in one plane perpendicular to the central axis of the airborne body.
10 . The mechanism of claim 9 , wherein the plurality of actuators is a circumferential array of four actuators.
11 . An airborne body comprising the mechanism of claim 10 .
12 . An airborne body comprising the mechanism of claim 9 .
13 . An airborne body comprising the mechanism of claim 1 wherein the airborne body is selected from: jet-propelled cruise missiles, guided bombs, guided artillery shells and a missile.
14 . A Fin Control Actuation System (FCAS) assembly comprising the mechanism for steering and maneuvering an airborne body of claim 1 , wherein the FCAS assembly comprises an apparatus having a toroidal ring-like cross-section and the plurality of actuators is installed in the apparatus.
15 . The FCAS assembly of claim 14 , wherein the apparatus is adapted for installation around a rear section of a missile motor of a rocket propulsion system such that the apparatus encompasses the rear section of the missile motor.
16 . The FCAS assembly of claim 14 , wherein the plurality of actuators is packaged in one plane perpendicular to the central axis of the airborne body.
17 . The FCAS assembly of claim 14 , wherein the plurality of actuators is a circumferential array of four actuators.
18 . The FCAS assembly of claim 17 , wherein the assembly is adapted for installation of four fins on the airborne body, each of which has an angular motion revolving around an axis by means of the circumferential array of four actuators.
19 . The FCAS assembly of claim 18 , wherein the four fins serve as tail wings of the airborne body for steering the airborne body by tail control of the four fins.