Kinematic design improvement and validation of ATF(Active Trailing-edge Flap) for helicopter vibration reduction

헬리콥터의 진동하중 저감을 위한 능동 뒷전플랩의 기구학적 설계 개선 및 검증

In this paper, an improved small-scaled blade prototype was designed with the flap-driving mechanism classified as an active vibration reduction method, in order to reduce vibratory load in the helicopter. In detail, the previous Active Trailing-Edge Flap based on piezoelectric actuator, called SNUF(Seoul National University Flap), failed to achieve the target value (${\pm}4^{\circ}$) of the flap deflection angle. Therefore, the flap-driving mechanism design was improved, and a new piezoactuator was selected to accomplish the target value of the flap deflection angle in both static and rotating situations.