GANGED SERVO FLIGHT CONTROL SYSTEM FOR AN UNMANNED AERIAL VEHICLE

1 . A flight control system for controlling collective and cyclic pitch of a helicopter comprising:

a swashplate having one or more connection portions;

a first control assembly coupled to the first connection portion and having at least two first servo-actuators;

a third control assembly coupled to the third connection portion and having means for controlling the collective and cyclic pitch in a third manner by movement of third components arranged opposite each other in a facing relationship and moving within parallel planes.

2 . The flight control system of claim 1 , wherein the first control assembly includes means for controlling the collective and cyclic pitch in a first manner by movement of first components in a first common plane.

3 . The flight control system of claim 2 , wherein the means for controlling the collective and cyclic pitch in the first manner comprise:

a first servo arm,

a second servo arm,

a linkage assembly connecting the second servo arm to the first servo arm, and

wherein the linkage assembly operatively couples the first and the second servo arms to the first connection portion of the swashplate such that the first servo arm and the second servo arm rotate in unison to control the swashplate.

4 . The flight control system of claim 3 , wherein the at least two first servo-actuators are arranged in parallel and move in the first common plane.

5 . The flight control system of claim 1 , wherein the means for controlling the collective and cyclic pitch in the third manner comprise:

at least two third servo-actuators, wherein the at least two third servo-actuators are arranged in the facing relationship across the vertical midline of the helicopter

a first servo arm is attached to one of the at least two third servo-actuators, and

a second servo arm attached to the other of the at least two third servo-actuators,

wherein the first servo arm and the second servo arm move within the parallel planes.

6 . The flight control system of claim 1 , wherein the third connection portion includes an anti-rotation boss extending radially outward from the swashplate and a linkage assembly is coupled to the anti-rotation boss and the third control assembly.

7 . The flight control system of claim 1 , further comprising:

a second control assembly connected to a second connection portion of the more than one connection portions of the swashplate and including means for controlling the collective and cyclic pitch in a second manner by movement of second components in a second common plane.

8 . The flight control system of claim 6 , wherein the means for controlling the collective and cyclic pitch in the second manner comprise

at least two second servo-actuators connected to rotate in unison; and

wherein the second control assembly directly moves the second connection portion by the unified rotation of the at least two second servo-actuators.

9 . The flight control system of claim 1 , further comprising:

a control signal generator electrically coupled to the first control assembly by a first output and electrically coupled to the third control assembly by a third output; and

wherein the control signal generator manipulates both of the two or more servo-actuators of the first control assembly or the third control assembly with a single signal output.

10 . A flight control system for a helicopter comprising

a swashplate;

a first control assembly coupled to a first connection portion of the swashplate and having at least two first servo-actuators;

a third control assembly coupled to a third connection portion of the swashplate and having at least two third servo-actuators and including means for controlling the collective and cyclic pitch in a third manner by movement of third components arranged opposite each other in facing relationship and moving within parallel planes;

a control signal generator electrically coupled to the first control assembly by a first output and the third control assembly by a third output; and

wherein the control signal generator manipulates each of the at least two first servo-actuators or the at least two third servo-actuators with a single signal output.

11 . The flight control assembly of claim 9 , wherein:

the two or more third servo-actuators are arranged in a facing relationship across a vertical midline of the helicopter,

the means for controlling the collective and cyclic pitch in a third manner include a first servo arm attached to one of the at least two third servo-actuators and a second servo arm attached to the other of the at least two third servo-actuators.

12 . The flight control system of claim 11 , wherein the at least two third servo-actuators are coaxially arranged.

13 . The flight control system of claim 11 , further comprising:

a second control assembly coupled to a second connection portion of the swashplate and having at least two second servo-actuators;

wherein the control signal generator is electrically coupled to the second control assembly by a second output; and

wherein the control signal generator manipulates each of the at least two second servo-actuators with a single second signal output.

14 . The flight control system of claim 11 , wherein the single signal output includes the individual controls for roll, pitch, and collective control of the swashplate.

15 . The flight control system of claim 11 , wherein the control signal generator generates a known input signal and at least one of the at least two first servo-actuators or the at least two third servo-actuators are positioned in a known configuration to calibrate the flight control system.

16 . The flight control system of claim 11 , wherein the single signal output manipulates the at least two first servo-actuators or the at least two third servo-actuators to move in unison to control the swashplate.

17 . The flight control system of claim 10 , wherein the first control assembly comprises:

a first servo arm,

a second servo arm,

a linkage assembly connecting the second servo arm to the first servo arm, and

wherein the linkage assembly operatively couples the first and the second servo arms to the first connection portion of the swashplate such that the first servo arm and the second servo arm rotate in unison to control the swashplate.

18 . An aerial vehicle, wherein the aerial vehicle is in a form of a helicopter comprising:

a swashplate having a plurality of connection portions;

a rotor assembly including a plurality of rotor blades operably controlled by the swashplate;

two or more control assemblies, each of the two or more control assemblies operatively coupled to one of the plurality of connection portions, wherein:

one of the two or more control assemblies includes means for controlling the swashplate in one manner by movement of first components in a first common plane;

the other of the two or more control assemblies includes means for controlling the swashplate in another manner by the movement of two or more components within parallel planes and arranged in a facing relationship across a vertical midline of the helicopter;

a control signal generator having two or more outputs each electrically coupled to the two or more control assemblies; and

wherein the control signal generator controls both of the two or more servo-actuators of one of the two or more control assemblies by providing a respective single signal to change an orientation of the swashplate, the change in orientation of the swashplate changing a pitch of the one or more rotor blades.

19 . The aerial vehicle of claim 18 , further comprising:

a plurality of frame structures, each of the plurality of frame members coupled together by a plurality of connection members; and

wherein each of the plurality of connection members include a base portion having tabs extending from opposing ends of the base portion, each of the tabs attached to an interior surface of the plurality of frame members.

20 . The aerial vehicle of claim 19 , wherein:

the swashplate, the rotor assembly, the two or more control assemblies, and the control signal generator are received in an interior cavity defined by the interior surface of one of the plurality of frame members.