A virtual environment for rotorcraft vibration analysis

Abstract

This work aims at showing how a modern state space aeroservoelastic virtual simulation environment can be effective in evaluating the combined performance of several passive and active systems for helicopter vibration reduction. A general purpose helicopter model is used to demonstrate the approach. On the airframe, performance indicators are formulated based on the accelerations on the pilot seats and critical structural connection points. To illustrate the method: three helicopter-related passive vibration absorbers, which are located at main rotor hub, gearbox-fuselage connection and pilot seat, are considered.