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

机译：通过IBC对20TO直升机转子模型进行振动减少的数值研究

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摘要

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 vibrations 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 computational effort can be decreased significantly. This reduction becomes possible, because a considerable portion of time consuming non linear computer simulations usually used for this purpose is replaced by numerical computations based on offline identified T-matrix models. It is shown, that the proposed method is well suited for vibration reduction investigations. 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.
机译：本文介绍了通过IBC（单独刀片控制）的振动减少的理论结果，该振动通过基于数值计算的20TO直升机转子模型。进行研究以分析单一和混合模式IBC输入的效率，用于六个叶片完全铰接转子的模型的直升机振动。此外，在该框架内，提出并验证了用于数值研究的方法。这种方法对于减振调查的方法的一个重要益处是，计算工作可以显着下降。这种降低是可能的，因为通常用于通常用于此目的的非线性计算机模拟的相当长的时间由基于离线识别的T-矩阵模型的数值计算代替。示出了，所提出的方法非常适合减振调查。除此之外，将详细介绍用于减少六个叶片20型转子模型的振动的单个和混合模式IBC的电位。

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