直升机旋翼动态失速流动控制新方法探索研究

项目名称： 直升机旋翼动态失速流动控制新方法探索研究

项目编号： No.11472223

项目类型： 面上项目

立项/批准年度： 2015

项目学科： 数理科学和化学

项目作者： 许和勇

作者单位： 西北工业大学

项目金额： 90万元

中文摘要： 前飞旋翼的动态失速对直升机性能具有重要影响，减缓或抑制动态失速的研究一直是直升机旋翼设计的难点之一。本项目提出了一种新颖的基于前缘充气气囊的旋翼动态失速抑制方法，基本思路是：在旋翼前缘布置可充放气的气囊装置，在后行侧对其充气，改变前缘形状，达到减缓或抑制分离的效果；在前行侧放出气体，气囊在自身弹性作用下紧贴旋翼表面，恢复到原设计外形。该方法无复杂转动或传动机构、对旋翼原有结构改动不大、可控外形变化范围大，且适合旋翼弹性变形和摆振情况下的前缘变形控制。项目将采用计算流体力学方法和实验验证两种技术途径进行探索研究，主要研究内容包括旋翼动态失速机理数值模拟研究、充气气囊设计方法、气囊对旋翼动态失速抑制规律的数值模拟研究及实验研究。本项目预期将发展出一套完善的基于非结构网格的旋翼流动N-S方程求解程序，揭示旋翼动态失速机理，掌握充气气囊对动态失速的影响规律，探索出一种新颖的旋翼动态失速抑制方法。

中文关键词： 直升机旋翼；动态失速；充气气囊；流动控制；数值模拟

英文摘要： The dynamic stall has a significant impact on the performance of helicopter. It is always a challenge for the helicopter designer to develop an effective method to alleviate or suppress the dynamic stall. The present project proposes a novel method to suppress the rotor dynamic stall based on the inflatable leading edge bump. The basic idea is descripted as below. The inflatable bump is reasonably depolyed on the leading edge of the rotor, and it will be inflated when the rotor blade rotates to the retreating side. The changed shape of leading edge will influence the flow significantly and alleviate the separation of flow. When the rotor blade rotates to the forward side, the inflatable bump will be deflated and attaches to the blade surface keeping the original design shape. This method has no rotating or transmission mechanism, makes minimum change to the original rotor structure, gives maximum shape control range and suits the deformation control under complicated conditions such as rotor elastic and oscillation movements. This project will adopt both of computational fluid dynamics method and experimental method to investigate several aspects, including numerical simulation of rotor dynamic stall, design method of the inflatable leading edge bump, the influence of the inflatable bump on the dynamic stall suppression by means of both the numerical simulation and experiment. It is expected that the present project will develop a complete numerical simulation code for solving the helicopter rotor flow based on the unstructured grid and Navier-Stokes equations. The mechanism of rotor dynamic stall and influence of the inflatable bump on the dynamic stall suppression will be further discovered, and a novel method of rotor dynamic stall suppression will be explored.

英文关键词： Helicopter rotor;Dynamic stall;Inflatable bump;Flow control;Numerical simulation