Development of an SNU Intelligent Rotor Blade with an Active Trailing-Edge Flap

Helicopters are operated in unsteady and asymmetric aerodynamic environment. This generates high vibratory loads and critical aerodynamic noises upon helicopter rotor. Conventional control system has a limitation upon reducing those problems because of its restrictive control displacement. Therefore many technologies involving passive and active control method have been examined to alleviate the problems. In this paper, a procedure to design and fabricate a blade using the active control method is pursued. The present active blade is Seoul National University flap blade (SNUF blade). UM/VABS, NASTRAN and 1-D beam analysis are used for its structural analysis. For an estimation of its hinge moment, FLUENT is used. APA 200M is selected as an actuator of SNUF blade. And a detailed design of the flap actuation region is conducted in this paper.