Actively controlled trailing edge flaps with electromechanical actuation

Abstract

The present paper studies Active Rotor Control for helicopters. It is shown that Individual Blade Control (IBC) concept is more preferable for the purposes of rotorcraft vibrations reduction. There described electromechanical pre-prototype actuator and active flap control model test simulator designed by the Mil Moscow Helicopter Plant. Active flap control model and electromechanical pre-prototype actuator test data obtained at the Mil Moscow Helicopter Plant test facilities are provided. The obtained results show that electromechanical actuator of the type could be applied in the active rotor control systems for both existing and future rotorcraft.