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首页> 外文期刊>The Aeronautical Journal >Modelling a helicopter rotor's response to wake encounters
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Modelling a helicopter rotor's response to wake encounters

机译：模拟直升机旋翼对遭遇尾声的反应

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摘要

In recent years, various strategies for the concurrent operation of fixed- and rotary-wing aircraft have been proposed as a means of increasing airport capacity. Some of these strategies will increase the likelihood of encounters with the wakes of aircraft operating nearby. Several studies now exist where numerical simulations have been used to assess the impact of encounters with the wakes of large transport aircraft on the safety of helicopter operations under such conditions. This paper contrasts the predictions of several commonly-used numerical simulation techniques when each is used to model the dynamics of a helicopter rotor during the same idealised wake encounter. In most previous studies the mutually-induced distortion of the wakes of the rotor and the interacting aircraft has been neglected, yielding the so-called 'frozen vortex' assumption. This assumption is shown to be valid only when the helicopter encounters the aircraft wake at high forward speed. At the low forward speeds most relevant to near-airfield operations, however, injudicious use of the frozen vortex assumption may lead to significant errors in predicting the severity of a helicopter's response to a wake encounter.
机译：近年来，已经提出了用于固定翼飞机和旋翼飞机同时运行的各种策略，作为增加机场容量的一种手段。这些策略中的某些策略会增加与附近运营的飞机尾流相遇的可能性。现在存在一些研究，其中使用数值模拟来评估在这种条件下大型运输机的尾流遭遇对直升机操作安全性的影响。本文对比了几种常用的数值模拟技术的预测结果，每种技术都用于在同一理想的尾声相遇期间为直升机旋翼的动力学建模。在大多数以前的研究中，旋翼和相互作用的飞机的尾流相互感应引起的变形被忽略了，从而产生了所谓的“冻结涡”假设。该假设仅在直升机遇到高前进速度的飞机苏醒时才有效。但是，在低速前进时，最接近于近场操作的情况，如果不合理地使用冻结涡旋假设，可能会在预测直升机对遭遇尾声的反应的严重性方面导致重大错误。

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