A flight control system for an unmanned aerial vehicle in a form of a helicopter comprising: a swashplate constituting a component of the unmanned aerial vehicle and having a first (166, 168), a second (166, 168), and a third connection portions; a first control assembly (182A, 182B) connected to the first connection portion (166, 168); a second control assembly (182A, 182B) connected to the second connection portion (166, 168); a third control assembly for the unmanned aerial vehicle including two or more servo-actuators (184C, 188C) connected to rotate in unison, wherein the third control assembly (182A, 182B) has a third output, the third control assembly comprising: a first servo-actuator (184C, 188C) having a first servo arm (186C, 190C); a second servo-actuator having (184C, 188C) a second servo arm (186C, 190C); and characterised in that it further comprises a linkage assembly connecting the second servo arm (186C, 190C) to the first servo arm (186C, 190C) and the third output to the third connection portion; wherein the first servo-actuator (184C, 188C) and the second servo-actuator (184C, 188C) are arranged opposite each other in a facing relationship such that the first servo arm (186C, 190C) and the second servo arm (186C, 190C) reside and move within parallel planes, the two or more servo-actuators (184C, 188C) mechanically connected to the third connection portion of the swashplate to directly move the third connection portion by the unified rotation of and by power of the two or more servo-actuators (184C, 188C). a swashplate constituting a component of the unmanned aerial vehicle and having a first (166, 168), a second (166, 168), and a third connection portions; a first control assembly (182A, 182B) connected to the first connection portion (166, 168); a second control assembly (182A, 182B) connected to the second connection portion (166, 168); a third control assembly for the unmanned aerial vehicle including two or more servo-actuators (184C, 188C) connected to rotate in unison, wherein the third control assembly (182A, 182B) has a third output, the third control assembly comprising: a first servo-actuator (184C, 188C) having a first servo arm (186C, 190C); a second servo-actuator having (184C, 188C) a second servo arm (186C, 190C); and characterised in that it further comprises a linkage assembly connecting the second servo arm (186C, 190C) to the first servo arm (186C, 190C) and the third output to the third connection portion; wherein the first servo-actuator (184C, 188C) and the second servo-actuator (184C, 188C) are arranged opposite each other in a facing relationship such that the first servo arm (186C, 190C) and the second servo arm (186C, 190C) reside and move within parallel planes, the two or more servo-actuators (184C, 188C) mechanically connected to the third connection portion of the swashplate to directly move the third connection portion by the unified rotation of and by power of the two or more servo-actuators (184C, 188C). a first servo-actuator (184C, 188C) having a first servo arm (186C, 190C); a second servo-actuator having (184C, 188C) a second servo arm (186C, 190C); and characterised in that it further comprises a linkage assembly connecting the second servo arm (186C, 190C) to the first servo arm (186C, 190C) and the third output to the third connection portion; wherein the first servo-actuator (184C, 188C) and the second servo-actuator (184C, 188C) are arranged opposite each other in a facing relationship such that the first servo arm (186C, 190C) and the second servo arm (186C, 190C) reside and move within parallel planes, the two or more servo-actuators (184C, 188C) mechanically connected to the third connection portion of the swashplate to directly move the third connection portion by the unified rotation of and by power of the two or more servo-actuators (184C, 188C).