动力布局对分布式电推进飞机气动性能的影响  

Effects of power layout on aerodynamic performance of distributed electric propulsion aircraft

作　　者：成志勇 杨佑绪 卢嘉成 刘易斯 CHENG Zhiyong;YANG Youxu;LU Jiacheng;LIU Yisi(School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China;Department of Mechanics and Aerospace Engineering,Southern University of Science and Technology,Shenzhen518055,China;The Third Military Representative Office of Army Equipment Department in Nanjing,Nanjing 210000,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063 [2]南方科技大学力学与航空航天工程系,深圳518055 [3]陆军装备部驻南京地区第三军事代表室,南京210000

出　　处：《空气动力学学报》2024年第5期81-96,共16页Acta Aerodynamica Sinica

基　　金：某计划(2022_JCJQ-JJ-1135);江西省“双千计划”人才项目(CK202006470)。

摘　　要：分布式电推进(DEP)飞机气动综合收益受分布式动力/机翼强气动耦合效应的影响,揭示其变化规律及流动机理是开展分布式电推进飞行器设计的关键。本文针对分布式螺旋桨-机翼布局,基于涡格法-激励盘理论(VLM-ADT)气动特性快速求解方法开展DEP布局气动性能研究,重点研究了螺旋桨数量、旋转方向、螺旋桨间隔3个要素对升阻比L/D、功率载荷T/P、总效率L/P等气动性能指标的影响。结果表明:随着螺旋桨数量的增加叠加效应会减弱,升阻比减小,但总效率增大。当螺旋桨数量小于等于5时,同向旋转构型的升阻比大于反向旋转构型。当螺旋桨数为7时,反向旋转构型升阻比大于同向旋转构型。与同向旋转构型相比,桨盘载荷增加时,反向旋转构型的升阻比会增加。分布式螺旋桨密集布置在翼尖时会同时增加升力和阻力;当翼尖螺旋桨固定在翼尖、其他螺旋桨密集布置在机翼中心附近时,翼尖螺旋桨的上洗效应会削弱翼尖涡,具有增升减阻效果,且升力比螺旋桨集中在翼尖构型时增加得更多。In order to carry out the design of distributed electric propulsion(DEP)aircraft,it is important to understand the flow mechanism and the changing law of aerodynamic comprehensive gain of DEP aircraft under strong coupling effects of the distributed power and the wing.Aiming at distributed propeller-wing layouts,the present study investigates the aerodynamic performance of DEP configurations based on the VLM-ADT(vortex lattice method-actuator disk theory)fast solver for aerodynamic characteristics.The effects of three factors,i.e.,the propeller number,the rotating direction,and the propeller spacing,on the aerodynamic performance metrics such as the lift-to-drag ratio L/D,the power load T/P,and the overall efficiency L/P,are studied in particular.As the number of propellers increases,the lift-to-drag ratio decreases,but the overall efficiency increases.When the number of propellers is not larger than 5,the lift-to-drag ratio of the co-rotating configuration is greater than that of the counter-rotating configuration.When the number of propellers is 7,the lift-to-drag ratio of the counter-rotating configuration is greater than that of the co-rotating configuration.Compared to the co-rotating configuration,the lift-to-drag ratio of the counter-rotating configuration increases when the propeller disk load is increased.The distributed propellers increase the lift and drag at the same time when they are densely concentrated at the wing tip.When the wing-tip propeller is fixed at the wing tip while the other propellers are densely concentrated near the center of the wing,it has the effect of increasing the lift and reducing the drag,and the lift increase is more than that of the propeller concentrating at the wing tip.

关 键 词：分布式电推进 动力布局 气动特性 螺旋桨滑流 涡格法-激励盘理论 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]