共轴刚性旋翼气动特性试验与分析  

Experiment and Analysis of Aerodynamic Performance of Coaxial Rigid Rotor

作　　者：刘向楠 邵天双[1,2] 刘实 刘少腾 陈宝 LIU Xiang-nan;SHAO Tian-shuang;LIU Shi;LIU Shao-teng;CHEN Bao(AVIC Aerodynamics Research Institute,Harbin 150001,China;Low Speed High Reynolds Number Aeronautical Key Laboratory,Harbin 150001,China)

机构地区：[1]中国航空工业空气动力研究院,哈尔滨150001 [2]低速高雷诺数航空科技重点实验室,哈尔滨150001

出　　处：《科学技术与工程》2024年第14期6082-6088,共7页Science Technology and Engineering

摘　　要：共轴刚性旋翼直升机是高速直升机的主要发展方向之一,为了深入了解前进比及升力偏置对共轴刚性旋翼气动特性的影响,在航空工业气动院FL-52风洞开展了共轴刚性旋翼气动特性风洞试验,通过合理的操纵与配平策略,实现了共轴刚性旋翼配平,并对悬停、多种前飞状态下气动特性及升力偏置对旋翼操纵特性及性能的影响机理进行了研究。结果表明,试验取得了比较好的配平效果,桨毂力矩、合扭矩及升力偏置配平误差分别优于±2 N·m、±0.5 N·m、±0.01;悬停状态扭矩配平与非配平状态下,上旋翼效率都大于下旋翼,差动总距效率随联动总距的增大而增大;前飞状态升力偏置可有效提升大前进比时旋翼气动效率而小前进比时则并不明显,升力偏置的增大会使上下旋翼的桨毂滚转力矩大幅增加。The high speed coaxial helicopters with rigid blades will be the future development direction of rotor aircraft,to gain insights into the effect of of the advance ratio and lift offset on the aerodynamic characteristics of coaxial rigid rotor,a trim strategy was developed and the wind tunnel test was carried out in the FL-52 wind tunnel of AVIC Aerodynamics Research Institute to investigate the performance of coaxial rigid rotor.The rotor aerodynamic performance in hover and forward flight conditions and the influence of lift offset were studied.The results indicate that the trim strategy is reasonable,and the trim results are satisfactory.The trim errors of hub torque,total torque of rotors and lift offset are better than±2 N·m,±0.5 N·m and±0.01 respectively.The efficiency of the upper rotor is greater than that of the lower rotor under torque balanced and unbalanced in hover.The efficiency of differential collective increases with the increase of coupled collective.In forward flight.The lift offset in forward flight can effectively improve the rotor aerodynamic efficiency at high forward ratio,but it is not significant at low forward ratio,increasing the lift offset will significantly increase the hub rolling moment of the upper and lower rotors.

关 键 词：共轴刚性旋翼 风洞试验 气动特性 旋翼配平 升力偏置 

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]