高速直升机共轴刚性旋翼悬停气动特性的参数影响研究  

Parameter Effect Research on Hovering Aerodynamic Characteristics of Coaxial Rigid Rotor of High-speed Helicopter

作　　者：胡志远[1] 史勇杰[1] 徐国华[1] 温小军 Hu Zhiyuan;Shi Yongjie;Xu Guohua;Wen Xiaojun(National Key Laboratory of Helicopter Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机动力学全国重点实验室,江苏南京210016

出　　处：《航空科学技术》2023年第9期15-23,共9页Aeronautical Science & Technology

基　　金：江苏高校优势学科建设工程资助项目。

摘　　要：共轴刚性旋翼是未来高速直升机的重要发展方向,开展气动特性参数影响研究具有重要的实际指导意义。基于计算流体力学(CFD)技术,本文建立了一个计入配平分析的共轴刚性旋翼气动特性计算方法。在该方法中,采用NavierStokes方程为控制方程,使用二阶迎风的Roe格式进行空间离散,选取隐式LU-SGS格式进行时间推进,湍流模型则为Spalart-Allmaras(S-A)模型,上下旋翼间的流场信息交换采用运动嵌套网格方法实现;通过Newton-Rhapson迭代方法求解旋翼操纵增量,可实现共轴刚性旋翼的有效配平。然后,应用所建立的方法,开展了共轴刚性旋翼悬停状态下的气动性能计算,着重分析了上下旋翼间距尤其是桨叶气动外形参数对共轴刚性旋翼气动特性的影响。结果表明,负扭转可以提高共轴刚性旋翼悬停效率,但与负扭转分布相比,采用正扭转分布,会降低共轴刚性旋翼悬停效率。The coaxial rigid rotor is an important development direction of high-speed helicopters,and it is of great practical significance to carry out research on the influence of aerodynamic parameters.This paper develops a method for calculating the aerodynamic characteristics of a coaxial rigid rotor based on CFD techniques considering the trim model.The governing equations of this method are Navier-Stokes equations with the second-order upwind Roe scheme used for spatial discretization and the implicit LU-SGS scheme selected for time stepping marching.The turbulence model is Spalart-Allmaras(S-A)model,and the flow field information exchange between the upper and lower rotors is achieved by the motion chimera moving overset gird method.The rotor pitch increment is solved by Newton-Rhapson iteration method,which can realize the effective trim of coaxial rigid rotor.Then,the aerodynamic performance of the coaxial rigid rotor in hover is calculated by using the established method.The effect of the distance between the upper and lower rotors,especially the aerodynamic shape parameters of the blades on the aerodynamic characteristics of the coaxial rigid rotor is analyzed.The results show that negative torsion twist can improve the hovering efficiency of coaxial rigid rotors,but using positive twist distribution will reduce the hovering efficiency of coaxial rigid rotors compared to negative twist.

关 键 词：共轴刚性旋翼 高速直升机 气动特性 配平 悬停 计算流体力学 

分 类 号：V211.46[航空宇航科学与技术—航空宇航推进理论与工程]