基于横流风扇技术的直升机反扭验证  

Helicopter anti-torque verification based on cross flow fan technology

作　　者：杜思亮[1,2] 吉孟江 唐正飞[1] 陈仁良[1] 

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,南京210016 [2]淮阴工学院机械与材料工程学院,淮安223003

出　　处：《北京航空航天大学学报》2017年第5期981-991,共11页Journal of Beijing University of Aeronautics and Astronautics

基　　金：江苏高校优势学科建设工程资助项目~~

摘　　要：为了提高单旋翼带尾桨直升机的低空飞行安全性,利用横流风扇流动控制技术,设计了一种可以替代单旋翼直升机尾桨的反扭装置。通过风洞试验验证了该装置具有产生侧向力的特性,同时建立了该装置的数值模拟计算方法,得出了横流风扇转速、旋翼下洗流和前飞来流对该反扭装置的气动特性影响较大,初步分析了该反扭装置的侧向力的来源,证明了可以通过控制横流风扇转速来控制反扭装置侧向力的大小,因此应用于直升机的反扭系统是可行的。In order to improve the safety of low altitude flight for the helicopter with tail rotor, an alternative anti-torque device has been proposed by using the flow control technology of the cross flow fan. Wind tunnel tests show that the device has the characteristics of lateral force. At the same time, the numerical simulation calculation method of the device has been established. It is concluded that the influence of the cross flow fan rotating speed, the rotor down wash flow and the front flying flow on the aerodynamic characteristics of the anti-torque device is great. The source of the force of the anti-torque device is analyzed. It is proved that the lateral force can be controlled by controlling the speed of cross flow fan and this device can be used as anti-torque device for helicopter.

关 键 词：直升机 反扭 横流风扇 风洞试验 计算流体力学(CFD) 

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]