无人旋翼机旋翼气动分析与试验研究  

Analysis and Experimental Study on Rotor Aerodynamics of Unmanned Gyroplane

作　　者：吴裕平[1] 解望 WU Yuping;XIE Wang(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,景德镇333001

出　　处：《南京航空航天大学学报》2021年第2期253-259,共7页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为支撑某无人旋翼机方案设计,采用叶素理论和动态入流建立旋翼气动模型,进行旋翼参数分析。评估了旋翼半径和总距对旋翼拉力及轴倾角的影响,得到旋翼拉力和操纵规律。在大尺寸低速风洞开展无人旋翼机的试验研究,对独立机身、机身+旋翼组合体进行吹风,得到了不同风速及迎角下机身和旋翼的升力与阻力,并与计算结果进行对比,从而验证计算方法的有效性。通过旋翼气动计算与试验结果分析,研究了旋翼气动特性与设计参数、飞行状态及轴倾角操纵之间关系。最后提出了旋翼拉力与飞行速度和轴倾角的关系公式。In order to support the design of an unmanned gyroplane,a rotor aerodynamics model based on blade element theory and dynamic inflow is developed to perform rotor parameter analysis.The influence of rotor radius and collective pitch on rotor thrust and shaft angle is discussed,and the law of rotor thrust and control is obtained.The experiments of unmanned gyroplane are conducted in the low speed wind tunnel,including the single fuselage experiment and the fuselage and rotor group experiment.The rotor lift and drag at different wind speeds and angle conditions are measured.The validity of the computing method is verified by comparing the experimental results with the computed result.By computational analysis and experimental study,rotor aerodynamic characteristics versus design parameters,flight state,and shaft angle are investigated.In the end,the formula for rotor thrust on flight speed and shaft angle is observed.

关 键 词：旋翼机 气动 旋翼 转速 飞行速度 风洞试验 

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]