旋翼布局对共轴刚性旋翼直升机气动特性影响研究  

Research on influence of rotor configuration on the aerodynamic characteristics of coaxial rigid rotor helicopter

作　　者：刘星亮 徐国华[1] 史勇杰[1] LIU Xingliang;XU Guohua;SHI Yongjie(National Key Laboratory of Rotorcraft Aeromechanics,NUAA,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《飞行力学》2022年第1期41-47,53,共8页Flight Dynamics

基　　金：江苏高校优势学科建设工程资助项目。

摘　　要：为研究旋翼布局对共轴刚性旋翼直升机气动特性的影响,建立了一种基于计算流体力学(CFD)技术的共轴刚性旋翼直升机全机气动干扰分析方法。通过某模型旋翼进行计算并与试验数据对比,验证了该方法的正确性。然后,针对旋翼间距、旋翼轴前倾角和桨毂中心相对直升机重心位置对共轴旋翼与旋翼/机身的气动特性进行了研究,分析了旋翼布局改变对共轴旋翼及旋翼/机身气动影响。结果表明:3个旋翼布局参数改变对悬停及前飞状态的气动特性均存在一定影响,其中旋翼轴前倾角影响明显;随旋翼轴前倾程度增加,悬停状态下轴向速度峰值与机身上表面相对压力峰值出现前移情况,前飞状态下桨毂中心后侧的轴向速度和机身上表面相对压力数值均有所减小。In order to study the influence of rotor layout on the aerodynamic characteristics of coaxial rigid rotor helicopters, a method of analysing the whole aircraft aerodynamic disturbance of coaxial rigid rotor helicopters based on Computational Fluid Dynamics(CFD) technology was established. The correctness of the method was verified by calculating a rotor model and comparing with the experimental data. Then, the aerodynamic characteristics of the coaxial rotors and the rotor/fuselage were studied according to the vertical separation of rotor, the forward tilting angle of the rotor shaft and hub position relative to the centre of gravity of the helicopter. The aerodynamic effects of the change of the layout on the coaxial rotor and rotor/fuselage were analyzed. The results show that the aerodynamic characteristics of hover and forward flight are affected by the changes of three rotor layout parameters, and the influence of the forward tilting angle of the rotor shaft is obvious. With the increase of rotor shaft forward inclination, the peak of axial velocity and the relative pressure on the upper surface of the fuselage move forward in the hovering state, and the axial velocity behind the hub center and the relative pressure on the upper fuselage surface both decrease in the forward flight.

关 键 词：共轴刚性旋翼 计算流体力学 旋翼布局 气动特性 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]