헬리콥터 반 토크 시스템의 피치제어기 설계 및 성능 시험 평가

The Helicopter Anti-torque System, namely Tail Rotor System is generated a horizontal force to counterbalance with a torque from the main rotor system. It is required that the initial design of Tail rotor should have a thrust margin of 10% to a direction control ability after counterbalance with a torque from the main rotor system when the maximum power rise. At this time, Pitch Control System is enable to a direction control ability at the tail rotor System. This paper introduces the design of pitch control system and manufacture and carry out a experimental performance test at the real size scale of Tail rotor system.