Cross-section Analysis Design of a Composite Rotor Blade with an advanced Trailing-edge Flap

摘要

A helicopter main rotor which generates lift andthrust as well as vehicle control forces gives a unique characteristic such as vertical flight, hover, and low speed maneuver, which are distinguished from those of the other flight vehicles. However, a conventional rotor system generates a significant amount of vibration and noise when the blades encounter complex and unsteady aerodynamic environment combined with structural dynamic responses. Reducing vibration loads benefits to reducing maintenance cost caused by the fatigue also increasing passenger's comfortable ride quality. Therefore, various methodologies have been pursued to alleviate these vibration loads.