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首页> 外文会议>AHS 59th Annual Forum Proceedings Vol.1 May 6-8, 2003 Phoenix, Arizona >Rotorcraft Vibration Reduction and Noise Prediction Using a Unified Aeroelastic Response Simulation
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Rotorcraft Vibration Reduction and Noise Prediction Using a Unified Aeroelastic Response Simulation

机译：使用统一的气弹响应模拟的旋翼机减振和噪声预测

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摘要

A study of the combined helicopter noise and vibration problem was conducted. A refined aerodynamic and wake model is coupled with an aeroelastic analysis simulation code. The rational function approximation approach is extended to the prediction of unsteady surface pressure distribution on rotor blade/flap combinations. An acoustic prediction tool based on WOPWOP is combined with the aeroelastic analysis based on a flexible blade with coupled flap-lag-torsional dynamics. This unified analysis program is validated with experimental data. The acoustic environment of the helicopter is characterized by microphones mounted on the rotorcraft. Actively controlled flaps are used to reduce vibrations, and noise levels and acoustic signatures are monitored throughout this process. Changes in the properties of the individual blade-vortex interactions are related to the acoustic results. This paper represents the careful theoretical treatment of the combined helicopter noise and vibration problem using actively controlled flaps for vibration reduction.
机译：对直升机噪声和振动的综合问题进行了研究。完善的空气动力学和尾流模型与空气弹性分析模拟代码结合在一起。有理函数逼近方法扩展到了转子叶片/襟翼组合上的非稳态表面压力分布的预测。基于WOPWOP的声学预测工具与基于弹性叶片的气动弹性分析相结合，并具有襟翼滞后扭转动力学特性。该统一分析程序已通过实验数据验证。直升机的声学环境的特征是安装在旋翼飞机上的麦克风。主动控制的襟翼用于减少振动，并且在整个过程中都会监控噪音水平和声学特征。各个叶片涡旋相互作用的特性变化与声学结果有关。本文介绍了使用主动控制襟翼减少振动对直升机噪声和振动组合问题进行的认真理论处理。

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