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首页> 外文期刊>Journal of the American Helicopter Society >Prediction and Fundamental Understanding of Stall Loads in UH-60A Pull-Up Maneuver
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Prediction and Fundamental Understanding of Stall Loads in UH-60A Pull-Up Maneuver

机译：UH-60A上拉机动中失速载荷的预测和基本理解

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摘要

This paper isolates the physics governing the aerodynamics and structural dynamics of UH-60A rotor in an unsteady maneuvering flight and proposes a hypothesis for the mechanism of advancing blade stall observed during pull-up maneuvers. The advancing blade stall observed during the Counter 11029 pull-up maneuver is in addition to the two conventional dynamic stall events observed on the retreating side of the blade. Both lifting-line as well as computational fluid dynamics analyses predict all three stall cycles with calculated deformations. The advancing blade transonic stall, observed from revolution 12 onward, is a twist stall triggered by 5/rev elastic twist deformation that increases the angle of attack beyond the static stall limit, resulting in shock-induced flow separation culminating in stall. The S/rev elastic twist is triggered by the two retreating blade stalls from previous revolution, which are separated by l/5th rev. The accurate prediction of both stall cycles on retreating blade holds the key to prediction of advancing blade stall. In analysis, advancing blade stall is triggered by a correct combination of control angles and 5/rev elastic twist.
机译：本文隔离了控制UH-60A转子在非平稳机动飞行中的空气动力学和结构动力学的物理学原理，并提出了在上拉机动过程中观察到的推进叶片失速机理的假设。在Counter 11029上拉操作期间观察到的前进叶片失速是对在叶片后退侧观察到的两个常规动态失速事件的补充。提升线以及计算流体动力学分析都可以预测所有三个失速周期，并计算出变形。从转数12开始观察到，前进的叶片跨音速失速是由5 / rev弹性扭曲变形触发的扭曲失速，这种扭曲失速将攻角增加到静态失速极限之外，导致激振引起的流分离最终导致失速。 S / rev弹性扭曲由前一转的两个后退叶片失速触发，它们之间的间隔为l / 5th rev。后退叶片失速周期的准确预测是预测叶片失速提前的关键。在分析中，前进叶片失速是由控制角度和5 / rev弹性扭曲的正确组合触发的。

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