共轴式双旋翼直升机桨毂减阻设计方法研究  

Study on Drag Reduction Design Method of Coaxial Twin Rotor Helicopter Hub

作　　者：龙海斌[1] 吴裕平[1] 朱仁淼[1] LONG Haibin WU Yuping ZHU Renmiao(China Helicopter Research and Development Institute, Jingdezhen 333001, China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2017年第2期22-26,共5页Helicopter Technique

摘　　要：针对共轴式双旋翼直升机高速前飞时桨毂产生的阻力在全机阻力中占比很大的问题,采用参数化建模方法对某型共轴式双旋翼直升机的桨毂进行了减阻设计,然后采用CFD对该型机桨毂和各减阻方案进行了数值模拟计算。通过深入研究桨毂各部件的阻力特性和流场数据,剖析了桨毂阻力的产生机理,结果表明上下椭圆形回旋体+瘦腰圆柱体带切线后体整流罩的减阻方案能降低52%左右的阻力,中间轴整流罩尾缘的压力分布对减阻的效果有比较大的影响。类似地,该研究成果对降低共轴高速直升机的桨毂阻力具有显著效果。Aiming at the problem that the drag of hub accounted for a large proportion of the whole coaxial twin rotor helicopter drag in high - speed forward flight, adopted the method of parametric to design hub fairing for a coaxial twin rotor helicopter, then calculated and analyzed the drag of the helicopter hub and the drag reduction schemes by the CFD method. Through studying the drag characteristics and flow field data of all parts of the hub,analyzed the mechanism of hub drag,The results showed that the drag reduction scheme of upper and lower elliptical cyclotron add thin waist cylinder with tangent after body hub fairing could reduce about 52% of the drag, the pressure distribution of the trailing edge of the rotor shaft fairing had great influence on the drag reduction effect. Similarly, the research results had a significant effect on reducing the drag of the coaxial high - speed helicopter hub.

关 键 词：直升机 共轴式双旋翼 桨毂 减阻 参数化 

分 类 号：V225[航空宇航科学与技术—飞行器设计]