Numerical Investigation of Vibration Reduction Through IBC for a 20to Helicopter Rotor Model

Abstract

This paper presents theoretical results of vibration reduction through IBC (Individual Blade Control) for a 20to helicopter rotor model which are based on numerical computations. The investigations were performed in order to analyse the efficiency of single and mixed mode IBC inputs on the helicopter vibra-tions of a model for a six bladed fully articulated rotor. Moreover, within this framework a method for the numerical investigations is proposed and validated. One important benefit of this method for the vibration reduction investigations is, that the compu-tational effort can be decreased significantly. This reduction becomes possible, because a consider-able portion of time consuming non linear computer simulations usually used for this purpose is replaced by numerical computations based on offline identi-fied T-matrix models. It is shown, that the proposed method is well suited for vibration reduction investi-gations. Besides this, the potential of single and mixed mode IBC for reducing vibrations of the six bladed 20to rotor model will be presented in detail.