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首页> 外文期刊>Journal of guidance, control, and dynamics >Linear Analysis of Vibration Reduction Using an Active N-Bladed Helicopter Rotor
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Linear Analysis of Vibration Reduction Using an Active N-Bladed Helicopter Rotor

机译：主动N叶片直升机旋翼减振的线性分析

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摘要

In the field of active rotor control, the use of individual blade control (IBC) systems for vibration reduction is a major topic of research. However, as most studies are focused on a specific helicopter rotor, the influence of topological rotor parameters, such as the number of rotor blades, is seldom investigated. The present investigation analyzes vibration reduction using an IBC system in a very general manner with particular focus on the influence of the number of rotor blades. To this end, a model for the quasi-steady transfer behavior of an IBC rotor with an arbitrary number of rotor blades is derived as a function of the blade transfer behavior using only a minimal set of assumptions. Using this model, a minimal set of blade-root load components relevant for the rotor hub loads is determined. Based on this set of components, a coordinate frame of effective blade-root loads is introduced. Subsequently, the vibration reduction potential for the N-bladed rotor is assessed, showing no direct relation between the number of rotor blades and the vibration reduction potential. Finally, the assumptions for the model, as well as the results of the investigation of the vibration reduction potential, are validated using open-loop flight data.
机译：在主动转子控制领域，使用单个叶片控制（IBC）系统来减少振动是研究的主要课题。但是，由于大多数研究都集中在特定的直升机旋翼上，因此很少研究拓扑旋翼参数的影响，例如旋翼叶片的数量。本研究以非常普遍的方式分析了使用IBC系统的减振效果，尤其着眼于转子叶片数量的影响。为此，仅使用最少的一组假设就可以得出具有任意数量的转子叶片的IBC转子的准稳态传递特性的模型。使用该模型，可以确定与转子轮毂负载相关的最小的叶根负载分量集。基于这组组件，引入了有效叶根负载的坐标系。随后，评估了N叶片转子的减振潜力，结果表明转子叶片的数量与减振潜力之间没有直接关系。最后，使用开环飞行数据验证了模型的假设以及减振潜力的研究结果。

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