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Investigations of the vortex ring state on a helicopter main rotor based on computational methodology using URANS solver

机译：基于URANS求解器的计算方法对直升机主旋翼涡环状态的研究

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Computational investigations of the Vortex Ring State (VRS) on a helicopter main rotor have been conducted. The VRS phenomenon is a condition of powered flight that occurs most frequently during the vertical or nearly vertical descent of a rotorcraft. The characteristic feature of the VRS is a torus-shaped vortex around a rotor. The occurrence of this extensive vortex structure is a dangerous phenomenon that usually causes sudden decrease of main-rotor thrust, finally leading to an increase of the rate of descent and vibration level, disturbances of a helicopter balance, deterioration of manoeuvrability and deficit of power. The investigations presented in the paper, have been conducted based on computational methodology developed and implemented by the Authors. The methodology is based on a coupling of several methods of Computational Fluid Dynamics and Flight Dynamic. The approach consists of calculation of unsteady aerodynamic forces acting on the flying rotorcraft by simultaneous solution of the URANS equations, the equations of motion of the helicopter as well as the equations describing fluid-structure-interaction phenomena. Flow effects caused by rotating rotor blades, are modelled using a simplified approach based on the Virtual Blade Model. Using the described methodology, a series of helicopter flight simulations, in a vicinity of the VRS boundaries, have been conducted. Selected results of these simulations have been discussed in the paper.
机译：已经对直升机主旋翼的涡环状态（VRS）进行了计算研究。 VRS现象是动力飞行的一种状况，最常发生在旋翼飞机的垂直下降或接近垂直下降的过程中。 VRS的特征是围绕转子的圆环状涡流。这种大范围涡旋结构的出现是一种危险现象，通常会导致主旋翼推力突然下降，最终导致下降率和振动水平增加，直升机平衡受到干扰，机动性下降和动力不足。本文中提出的调查是基于作者开发和实施的计算方法进行的。该方法基于计算流体动力学和飞行动力学的几种方法的结合。该方法包括通过同时求解URANS方程，直升机的运动方程以及描述流固耦合现象的方程来计算作用在飞行旋翼飞机上的非恒定空气动力。使用基于虚拟叶片模型的简化方法对由旋转的转子叶片引起的流动影响进行建模。使用所描述的方法，已经在VRS边界附近进行了一系列直升机飞行模拟。这些模拟的选定结果已在本文中进行了讨论。

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