论文:0-0
引用本文:
张乐, 周洲, 李盈盈, 甘文彪, 许晓平. 飞翼无人机保形非对称尾喷管设计与流场特性[J]. 西北工业大学学报
Zhang Le, Zhou Zhou, Li Yingying, Gan Wenbiao, Xu Xiaoping. Conformal Asymmetry Nozzle Design and Flow Field Characteristics of Flving Wing Unmanned Aerial Vehicle[J]. Northwestern polytechnical university

飞翼无人机保形非对称尾喷管设计与流场特性
张乐, 周洲, 李盈盈, 甘文彪, 许晓平
西北工业人学尤人机特种技术国防科技重点实验室, 陕西 西安 710072
摘要:
基于飞翼布局无人机隐身与保形设计要求,设计了不同面积比的四边形和圆矩形2类非对称尾喷管,并利用数值模拟方法对无人机内外流耦合流动进行了计算分析,获得了无人机全机纵向气动性能与尾喷管三维流场特性。结果表明:保形非对称尾喷管可用于改善飞翼无人机的纵向力矩特性,且圆矩形喷管升阻特性和力矩特性比四边形喷管更优;收敛型喷管(面积比Ar≤1.0)无法在设计点(发动机喷口)而是在尾喷管出口处形成喉道,并在喉道处形成强激波阻滞喷流排出;随着面积比增大,轴向推力系数先增大后减小,存在最佳面积比,而且相同面积比下圆矩形喷管比四边形喷管推力性能更佳;扩张型喷管内激波的强度随着面积比增大变得更强,圆矩形喷管结尾处的激波角比四边形喷管小,喷流阻滞作用更小;对于此类飞翼布局无人机采用面积比为1.2~1.4的圆矩形喷管,将获得较理想的气动性能。
关键词:    飞翼无人机    保形设计    非对称尾喷管    圆矩形    面积比    流场特性    数值模拟   
Conformal Asymmetry Nozzle Design and Flow Field Characteristics of Flving Wing Unmanned Aerial Vehicle
Zhang Le, Zhou Zhou, Li Yingying, Gan Wenbiao, Xu Xiaoping
National Key Laboratory of Science and Technology on UAV, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
Asymmetry nozzle of flying wing UAV(Unmanned Aerial Vehicle) was designed based on stealth andconformal requirements;this was set up into quadrilateral nozzle and circular-rectangle nozzle with different area ra-tins.The coupled numerical simulation was also carried out on the inflow/outflow integrated for flying wing UAV,and it is applied to studying the longitudinal aerodynamic performance of UAV and three-dlimensional flow fieldcharacteristics of nozzle.Results and their analysis indicate:asymmetry nozzle of flying wing UAV can be used toimprove the moment characteristic,and the lift/drag characteristic of circular-rectangle nozzle show better thanquadrilateral nozzle;the convergent nozzle whose area ratio A<=1.0 will form the throat at the nozzle vent but notthe design point expected at the engine vent ,and that the strong shock will form at the throat which is not condu-Give forjetAlow to exhaust;with the increase of the area ratio,the axial thrust coefficient firstly increases and thendecreases so that we could believe that there is an optimal area ratio,and that the circular-ectangle nozzle obtainsbetter thrust performance than the quadrilateral nozzle along with the same area ratio;the intensity of shock wave al-so becomes stronger in the nozzle with increasing area ratio,and the shock wave angle formed at the root of circular-rectangle nozzle is smaller than quadrilateral nozzle which causes less blocking for jet-flow.Generally speaking itis better to adopt circular-rectangle nozzle for the flying wing UAV with area ratio between 1.2 and 1.4;this leadsto ideal aerodynamic performance.
Key words:    angle of attack    boundary conditions    calculations    computer simulation    conformal mapping    design    drag coefficient    finite volume method    flow fields    lift drag ratio    Mach number    mathematical mod-els    mesh generation    Navier Stokes equations    nozzles    pressure    schematic diagrams    shock waves    three dimensional    turbulence models    unmanned aerial vehicles(UAV);area ratio    asymmetry noz-zle    circular-rectangle nozzle    conformal design    flow field characteristics    flying wing UAV   
收稿日期: 2014-03-18     修回日期:
DOI:
基金项目: 国家自然科学基金(11302178)资助
通讯作者:     Email:
作者简介: 张乐(1988-),西北工业人学博士研究生,主要从事飞行器总体设计、气动隐身-体化研究。
相关功能
PDF(KB) Free
打印本文
把本文推荐给朋友
作者相关文章
张乐  在本刊中的所有文章
周洲  在本刊中的所有文章
李盈盈  在本刊中的所有文章
甘文彪  在本刊中的所有文章
许晓平  在本刊中的所有文章

参考文献:
[1] 司源高速巡航无人机总体布局研究[D」西安:西北工业人学,2011 Si Yuan. Research on Configuration Layout for High Speed Cruise UAV [D]. Xi'an,Northwestern Polytec;hnic;al University 2011 (in Chinese)
[2] Johansson M. Propulsion Integration in an UAV [R]. AIAA20062834
[3] Lozanova M,Stantov P. Experimental Investigation on the Similarity of a 3D Rec;tangular Turbulent Jet [J]. Experiments in Fluid 1998,24:470-478
[4] Mi J,Nathan G J,Luxton R E. Centerline Mixing Characteristic、of Jets from Nine Differently Shaped Nozzles [J]. Experi-menu in Fluid,2000 28:93-94
[5] 张勃,吉洪湖人宽高比矩形喷管的射流与外流掺混特性的数值研究[J] 航空动力学报,2005 , 20 (1):104-110 Zhang Bo,Ji Honghu. Numerical Investigation of Mixing Characteristic、of Jets from Rectangular Nozzles with Large Aspect Ra-tio Journal of Aerospace Power 2005,20(1):104-110 (in Chinese)
[6] Capone F J,Re R J,BareE A.Parametric Investigation of Single-Expansion-Ramp Nozzles at Mach Numbers from 0. 60 to 1.20[R].NASA-TP-3240,1992
[7] Capone F J,NASA TP 3240, Re R J,Bare E A.Parametric; Study of Single Expansion Ramp Nozzles at Subsonic/Transonice Speeds [R] AIAA-1987-1836
[8] 谭杰,金捷.单边膨胀喷管儿何参数对内流特性和流场的影响[J].推进技术,2013, 34(2):152-1 60 Tan Jie,Jin Jie. Elfec;ts of Geometric; Parameters on Internal Performance and Flowfield of Single Expansion Ramp Nozzles[J]. Journal of Propulsion Technology,2013,34 (2):152-160 (in Chinese)
[9] Karen A Deere Scott C Asbury. An Experimental and Computational Investigation of a Translating Throat Single Expansion-Ramp Nozzle [R]. AIAA-1996-2540
[10] Carlson J. Prediction of Static; Performance for Single Expansion Ramp Nozzles [R]. AIAA-1993-2571
[11] 谭杰,金捷,杜刚,等过膨胀单边膨胀喷管试验和数值模拟[J].推进技术,2009,30 (3):292-296 Tan Jie,Jin Jie,Du Gang et al. Experimental and Computational Investigation of a Over-Expanded Single-Expansion-amp-Nozzle [J]. Journal of Propulsion Technology,2009,30 (3):292-296 (in Chinese)
[12] Carboni J D,Shyne R J,Leavitt L D,et al. Supersonic; Investigation of Two-Dimensional Hypersonic Exhaust Nozzles [R] NASA TM-105687,1992
[13] Collie WV,Burgun R,Heinzen S N,et al. Advanced Propulsion System Design and Integration for a Turbojet Powered Un-manned Aerial Vehicle [R]. AIAA 2003-0415
[14] 谢文忠,郭荣伟_元保形非对称膨胀喷管流场特性[J].航空动力学报,2011, 26(1):141-147 Xie Wenzhong,Guo Rongwei. Flow Field Characteristics of a Two-Dimensional Integrated Asymmetry-Expansion Nozzle [J].Journal of Aerospace Power 2011,26(1):141-147 (in Chinese)
[15] Michael Atkinson. A Computational Fluid Dynamics Investigation of the 1303 UCAV Configuration with Deployable Road Vortex Flaps [R]. AIAA-2006-126
[16」张丽芬,刘振侠,吕亚国S弯扩压器中四种湍流模型的比较[J].航空动力学报,2008, 23 (10): 1888-1891Zhang Lifen,Liu Zhenxia,Lii Yaguo. Comparison of Four Turbulence Models in Diffusing S-Duct [J]. Journal of Aerospace Power,2008,23(10):1888-1891 (in Chinese)
[17] Lee B J,Kim C. Automated Design Methodology of Turbulent Internal Flow Using Discrete Adjoint Formulation [J]. Aerospace Science and Tec;hnology,2007,11 (2):163-173
相关文献:
1.张乐, 周洲, 许晓平, 王红波.飞翼无人机保形进排气系统动力数值模拟与流场特性分析[J]. 西北工业大学学报, 2015,33(3): 353-360