菱形连翼布局俯仰力矩非线性特性数值分析

孙俊磊; 王和平; 周洲; 汪子义

doi:10.13700/j.bh.1001-5965.2016.0584

菱形连翼布局俯仰力矩非线性特性数值分析

doi: 10.13700/j.bh.1001-5965.2016.0584

1.
西北工业大学航空学院, 西安 710072
2.
北京机电工程研究所, 北京 100074

基金项目:

民机专项 MIE-2015-F-009

陕西省科技统筹 2015KTCQ01-78

详细信息

作者简介:
孙俊磊男, 博士研究生。主要研究方向:飞行器总体设计、气动布局设计

王和平男, 教授, 博士生导师。主要研究方向:飞行器总体设计、气动布局设计

通讯作者:
王和平, E-mail: wangheping@nwpu.edu.cn

中图分类号: V221⁺.3
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- 被引次数: 0
出版历程
- 收稿日期: 2016-07-07
- 录用日期: 2016-10-14
- 网络出版日期: 2017-08-20

Numerical analysis of pitching moment non-linear characteristics of diamond joined-wing configuration

1.
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072
2.
Beijing Electro-mechanical Engineering Institute, Beijing 100074, China

Funds:

Special Foundation for Civil Aircraft MIE-2015-F-009

Shaanxi Scientific and Technological Development Program 2015KTCQ01-78

More Information

Corresponding author: WANG H P, E-mail: wangheping@nwpu.edu.cn

摘要

摘要:
采用数值模拟和理论分析相结合的方法，对高空长航时（HALE）菱形连翼布局无人机（UAV）的俯仰力矩非线性特性进行了研究。研究结果显示菱形连翼布局飞机具有2个明显的俯仰力矩非线性区域并存在上仰现象。通过采用湍动能来表示后翼受前翼尾流直接扫掠而导致的流场结构改变的强度和影响范围来解释其中一个俯仰力矩非线性区域出现的原因。通过分析前后翼流场分离的特性来解释出现另一个俯仰力矩非线性区域和力矩上仰的原因。研究了总体布局参数变化对菱形连翼布局无人机俯仰力矩特性的影响，结果显示通过调整总体布局参数可以有效地缓解俯仰力矩特性曲线非线性对飞行性能带来的影响。
- 高空长航时(HALE) /
- 菱形连翼布局 /
- 数值模拟 /
- 俯仰力矩特性 /
- 总体参数
Abstract:
Investigation on the pitching moment non-linear characteristics of the high-attitude long-endurance (HALE) diamond joined-wing configuration unmanned aerial vehicle (UAV) was carried out by both numerical simulation and theoretical analysis method. The results show that the aircraft have two obvious pitching moment non-linear regions and there is a pitch-up phenomenon. The turbulent kinetic energy is used to represent the strength and the influence area of flow field structure of the aft-wing changed by the frt-wing wake direct sweep, which explains one of the causes of the non-linear region of the pitch moment. The other reason for the pitching moment non-linear region and pitch-up moment is explained by analyzing the separation characteristics of the aft-wing and the frt-wing. The influence of the general layout parameters of the UAV on the pitching moment characteristics of diamond joined-wing UAV was studied. The results show that adjusting the overall layout parameters can effectively mitigate the impact of pitching moment non-linear characteristics on flight performance.
- high-attitude long-endurance (HALE) /
- diamond joined-wing configuration /
- numerical simulation /
- pitching moment characteristics /
- layout parameters

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图 1 AFV-D机翼不同后掠角下展向截面位置示意图

Figure 1. Schematic of spanwise cross-sectional position of AFV-D wing at different backswept

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图 2 Case 1不同截面处压力系数分布与实验数据对比

Figure 2. Case 1 pressure coefficient distribution at different sections compared with experimental data

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图 3 Case 2不同截面处压力系数分布与实验数据对比

Figure 3. Case 2 pressure coefficient distribution at different sections compared with experimental data

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图 4 Model 1网格示意图

Figure 4. Schematic of grid of Model 1

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图 5 Model 1俯仰力矩特性曲线

Figure 5. Pitching moment characteristic curve of Model 1

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图 6 前后翼及全机焦点位置变化

Figure 6. Change of focus positions of frt-wing, aft-wing and aircraft

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图 7 前后翼焦点位置距全机焦点距离变化

Figure 7. Change of distance between frt-wing's and aft-wing's focus position and aircraft's focus position

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图 8 α=2°附近俯仰力矩特性曲线及升力特性曲线

Figure 8. Pitching moment characteristic curves and lift characteristic curves near α=2°

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图 9 α=2°附近的后翼翼根处极限流线分布

Figure 9. Limit streamline distribution of aft-wing root near α=2°

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图 10 截面位置

Figure 10. Sectional position

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图 11 α=0°, 2°, 4°, 6°时的湍动能

Figure 11. Turbulent kinetic energy at α=0°, 2°, 4°, 6°

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图 12 α=4°, 8°的极限流线

Figure 12. Limit streamlines at α=4°, 8°

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图 13 α=8°时菱形连翼布局和单独前翼布局的翼尖分离

Figure 13. Wingtip separation of diamond joined-wing configuration and separate frt-wing configuration at α=8°

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图 14 需调整参数示意图

Figure 14. Schematic of parameters to be adjusted

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图 15 改变翼间距的菱形连翼无人机布局

Figure 15. Diamond joined-wing UAV configuration with changing distance between wings

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图 16 翼间距影响的俯仰力矩特性曲线

Figure 16. Pitching moment characteristic curves influenced by distance between wings

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图 17 改变翼夹角的菱形连翼无人机布局

Figure 17. Diamond joined-wing UAV configuration with changing angle between wings

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图 18 改变翼夹角情况下的菱形连翼无人机俯仰力矩特性曲线

Figure 18. Pitching moment characteristic curves of diamond joined-wing configuration UAV with changing angle between wings

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图 19 Model 5、Model 6在α=-4°, 2Y/b=0.5时湍动能分布

Figure 19. Turbulent kinetic energy distribution of Modal 5, Model 6 at α=-4°, 2Y/b=0.5

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图 20 Model 7在α=6°, 2Y/b=0.5时湍动能分布

Figure 20. Turbulent kinetic energy distribution of Model 7 at α=6°, 2Y/b=0.5

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表 1 插值数据与数值模拟数据对比

Table 1. Comparison between interpolation data and numerical simulation data

位置插值数据数值模拟数据偏差/%

前翼 0.161 45 0.162 38 0.57

后翼 -0.237 6 -0.221 8 7.12

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参考文献(21)

[1]	WOLKOVITCH J.The joined wing:An overview[J].Journal of Aircraft, 1986, 23(3):161-178. doi: 10.2514/3.45285
[2]	KROO I, SMITH S, GALLMAN J.Aerodynamic and structural studies of joined-wing aircraft[J].Journal of Aircraft, 1991, 28(1):74-81. doi: 10.2514/3.45994
[3]	LIVNE E.Aeroelasticity of joined-wing airplane configurations:Past work and future challenges-A survey[C]//Proceedings of 19th AIAA Applied Aerodynamics Conference.Reston:AIAA, 2001:16-19.
[4]	CRAFT R L.Drag estimates for the joined-wing sensor craft:05J02[R].Dayton:AFIT, 2005.
[5]	PÉREZ-Á LVAREZ J, CUERNO-REJADO C, MESEGUER J.Aerodynamic parametric analysis of an unconventional joined-wing aircraft configuration[J].Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering, 2016, 230(10):1917-1933. doi: 10.1177/0954410015620444
[6]	ANDREWS S, RUBEN P E.Stability and control effects on the design optimization of a box-wing aircraft[C]//14th AIAA Aviation Technology Integration and Operations Conference.Reston:AIAA, 2014:1-22.
[7]	BOND V, CANFIELD R A, MATOS M, et al.Wind tunnel testing of a twisted wing for longitudinal control in a joined-wing aircraft[C]//48th Structures Structural Dynamics and Materials Conference.Reston:AIAA, 2007:1-7.
[8]	RASMUSSEN C C, CANFIELD R A, BLAIR M.Joined-wing sensor-craft configuration design[J].Journal of Aircraft, 2006, 43(5):1470-1478. doi: 10.2514/1.21951
[9]	LEDOUX S, VASSBERG J, FATTA G, et al.Aerodynamic cruise design of a joined wing sensorcraft[C]//26th AIAA Applied Aerodynamics Conference.Reston:AIAA, 2008:1-13.
[10]	MARTINEZ J, FLICK P, PERDZOCK J, et al.An overview of sensorcraft capabilities and key enabling technologies[C]//26th AIAA Applied Aerodynamics Conference.Reston:AIAA, 2008:1-13.
[11]	REICHENBACH E, CASTELLUCCIO M, SEXTON B.Joined wing sensorcraft aeroservoelastic wind tunnel test program[C]//52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference.Reston:AIAA, 2011:1-30.
[12]	TYLER C, SCHWABACHER G, CARTER D.Comparison of computational and experimental studies for a joined-wing aircraft[C]//Proceedings of 40th AIAA Aerospace Sciences Meeting & Exhibit, Aerospace Sciences Meetings.Reston:AIAA, 2002:1-8.
[13]	NANGIA R K, PALMER M E, TILMANN C P.Unconventional high aspect ratio joined-wing aircraft with aft- & forward-swept wing-tips[C]//Proceedings of the 41st AIAA Aerospace Sciences Meeting and Exhibit.Reston:AIAA, 2003:1-13.
[14]	楚亮, 马东立, 张朔, 等.一种联结翼布局气动特性的求解模型[J].航空学报, 2010, 31(5):909-913. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201005006.htm CHU L, MA D L, ZHANG S, et al.Solution model for aerodynamic characteristics of joined-wing configuration[J].Acta Aeronautica et Astronautica Sinica, 2010, 31(5):909-913(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201005006.htm
[15]	张晓萍, 曾会华, 余雄庆.CFD方法在联结翼飞机方案设计中的应用[J].南京航空航天大学学报, 2004, 36(6):763-768. http://www.cnki.com.cn/Article/CJFDTOTAL-NJHK200406019.htm ZHANG X P, ZENG H H, YU X Q.Application of CFD in conceptual design of joined-wing aircraft[J].Journal of Nanjing University of Aeronautics & Astronautics, 2004, 36(6):763-768(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-NJHK200406019.htm
[16]	刘学强, 李青, 柴建忠, 等.盒式机翼布局气动特性研究[J].南京航空航天大学学报, 2007, 39(6):722-725. http://www.cnki.com.cn/Article/CJFDTOTAL-NJHK200706005.htm LIU X Q, LI Q, CHAI J Z, et al.Aerodynamic characteristic research for box-wing aircraft[J].Journal of Nanjing University of Aeronautics & Astronautics, 2007, 39(6):722-725(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-NJHK200706005.htm
[17]	李军, 李占科, 宋笔锋.联翼高空长航时无人机总体布局设计研究[J].飞行力学, 2009, 27(4):1-4. http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX200904001.htm LI J, LI Z K, SONG B F.Conceptual layout design of the joined-wing high-altitude-long-endurance UAV[J].Flight Dynamics, 2009, 27(4):1-4(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX200904001.htm
[18]	吉笑峰. 传感器飞行器总体设计方案研究[D]. 西安: 西北工业大学, 2008. JI X F.Research on the overall design of the sensorcraft[D].Xi'an:Northwestern Polytechnical University, 2008(in Chinese).
[19]	李光里, 李国文, 黎军, 等.连接翼布局气动特性研究[J].空气动力学学报, 2006, 24(4):513-519. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200604022.htm LI G L, LI G W, LI J, et al.The aerodynamics investigation of the joined-wing configuration[J].Acta Aerodynamica Sinica, 2006, 24(4):513-519(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200604022.htm
[20]	王延奎, 单继祥, 田伟, 等.联翼布局俯仰力矩非线性变化特性的数值模拟[J].北京航空航天大学学报, 2012, 38(7):862-866. http://bhxb.buaa.edu.cn/CN/abstract/abstract12326.shtml WANG Y K, SHAN J X, TIAN W, et al.Investigation on non-linear characteristic of pitching moment of joined wing configuration aircraft[J].Journal of Beijing University of Aeronautics and Astronautics, 2012, 38(7):862-866(in Chinese). http://bhxb.buaa.edu.cn/CN/abstract/abstract12326.shtml
[21]	MANIE F, RAYNAL J C.Transonic measurements on the ONERA AFV D variable sweep wing in the ONERA S2 MA-wind tunnel:AGARD-AR-138[R].[S.l.:s.n.], 1979.