新型双机身鸭式布局无人机气动特性  

Aerodynamic Characteristics of a New type of Canard UAV with Twin-fuselage

作　　者：刘战合[1] 张璇[1] 夏陆林 王菁[1] 周鹏[3] 曾宪泽 LIU Zhan-he;ZHANG Xuan;XIA Lu-lin;WANG Jing;ZHOU Peng;ZENG Xian-ze(School of Aerospace,Zhengzhou University of Aeronautics,Zhengzhou 450046,China;Naval Architecture and Ocean Engineering College,Dalian Maritime University,Dalian 116026,China;School of Intelligent Engineering,Zhengzhou University of Aeronautics,Zhengzhou 450046,China)

机构地区：[1]郑州航空工业管理学院航空宇航学院,郑州450046 [2]大连海事大学船舶与海洋工程学院,大连116026 [3]郑州航空工业管理学院智能工程学院,郑州450046

出　　处：《科学技术与工程》2023年第9期3966-3972,共7页Science Technology and Engineering

基　　金：国家自然科学基金(11702255);河南省科技攻关计划(212102210052,212102210144,212102210109)。

摘　　要：优化载重性能的气动布局设计是当前无人机研究重要方向,为提高物资运载能力和结构性能,基于连接翼、双机身、鸭式布局设计,提出一种新型双机身鸭式布局无人机,采用FLUENT详细研究了两种飞行速度下的升阻特性、压力云图、涡量分布等。研究结果表明,双机身鸭式布局无人机具有较高的升阻性能,速度提高时,升力系数增加而阻力系数减小,速度由30 m/s增加到60 m/s时,最大升力系数增加7.6%,升阻比增加4.8%;从表面压力云图看,升力主要贡献为前机翼、鸭翼和后机翼,失速迎角前后,后机翼未受前机翼和鸭翼气流干扰,提高了无人机的失速特性;巡航迎角状态的涡量较弱,仅在翼梢及部件连接处出现,失速迎角前后,翼梢、部件连接处涡系增强,且产生了干扰,机翼表面趋于分离。The aerodynamic layout design of payload performance optimization is an important research interests of unmanned aerial vehicle(UAV).In order to improve the cargo carrying capacity and structural performance,a new type of UAV with twin-fuselage and canard configuration was proposed based on the design of joint-wings,twin-fuselage and canard configuration.And the lift-drag characteristics,pressure nephograms and vorticity distributions were studied at two different airspeeds by FLUENT in detail.The research results show that the twin-fuselage canard UAV possesses high lift-drag performance.When the airspeed increases,the lift coefficient increases and the drag coefficient decreases.When the airspeed increases from 30 m/s to 60 m/s,the maximum lift coefficient increases by 7.6%,lift-drag ratio increases by 4.8%.From the surface pressure nephograms,the main contribution of lift is contributed by the front wing,canard and rear wing,and the rear wing is not disturbed by the airflow of the front wing and canard around the stall angle of attack,which improves the stall characteristics of the UAV.The vorticity at the cruising angle of attack is weak,which only occurs at the wingtip and connection of components.Around the stall angle of attack,the vortex system at the wingtip and component connection is strengthened,and simultaneous the interference is appeared,the airflow of wing surface tends to be separated.

关 键 词：双机身 鸭式布局 无人机 升阻比 升力系数 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V221