Dynamic Behavior of the Composite Rotor Blade Using an Adaptive Damper

The reduction of helicopter vibration is becoming increasingly important to the helicopter structure, due to increasingly higher cruise speeds and improved comfort objectives. The adaptive damper technique has been shown to be capable of reducing fuselage vibration during steady flight conditions, and also maintaining reduced vibration levels during severe manoeuvres. The work is based on modeling by finite element method the blade with viscoelastic damper by applying an aerodynamic force. To realize this modeling we have used the numerical simulation by ABAQUS software to analyze the aerodynamic forces of the helicopter blade; it calculates the frequencies and Eigen valuer, stress, strain and the displacement, however the stress increased with crack propagation. Numerical calculations prove that the elastomeric damper of viscoelastic type produces better results compared to other ordinary systems.