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

机译：20to直升机旋翼模型通过IBC减振的数值研究

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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：本文介绍了基于数值计算的20to直升机旋翼模型通过IBC（个体叶片控制）进行减振的理论结果。进行研究是为了分析六叶片全铰接转子模型的直升机振动时单模式和混合模式IBC输入的效率。此外，在此框架内，提出并验证了一种数值研究方法。这种方法用于减振研究的一个重要好处是可以大大减少计算量。这种减少成为可能，因为通常用于此目的的大量耗时的非线性计算机仿真被基于脱机识别的T矩阵模型的数值计算所代替。结果表明，所提出的方法非常适合于减振研究。除此之外，将详细介绍单模和混合模IBC减少六叶片20转子模型振动的潜力。

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