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为了改善大展弦比飞翼模型纵向操纵性和稳定性, 在低速风洞中开展了等离子体流动控制技术的试验研究. 采用粒子图像测速技术获取了等离子体对翼面流场的影响. 采用静态测力技术获取了等离子体对模型气动力和升降舵舵效的影响. 采用虚拟飞行试验技术获取了等离子体对俯仰角和俯仰角速度时间历程的影响. 通过对粒子图像测速和测力试验结果的分析表明, 等离子体能够抑制翼面流动分离, 阻止气动中心前移, 改善模型的大迎角纵向气动特性. 通过分析不同舵偏角的测力数据, 来流风速V = 50 m/s时等离子体能够改善飞翼模型大迎角的升降舵舵效, 在不同舵偏角时均使模型的最大升力系数提高约0.1、失速迎角推迟4°以上. 通过分析虚拟飞行试验结果, 等离子体能够将模型的临界俯仰角提高3.6°, 能够改善飞翼模型的纵向飞行稳定性和操纵性.Horizontal tail is eliminated from the flying wing layout for improving the low observable and aerodynamic efficiency, resulting in degrading longitudinal maneuverability and fight stability. The low speed wind tunnel test study of improving the longitudinal aerodynamic characteristics of large aspect ratio flying wing model is carried out by using plasma flow control technology. The flying wing model has a leading-edge sweep angle of 34.5° and an aspect ratio of 5.79. The reasons for deteriorating the static maneuverability and stability of the flying wing model and the mechanism of plasma control of the flow field and longitudinal aerodynamic characteristics are studied by particle image velocimetry (PIV) flow visualization and static force measurement test. The control law of plasma control of the flight maneuverability and stability of the flying wing model is studied through flight test. The fact that the flow separation of the outer wing of the flying wing model occurs earlier than the inner wing and the wing is swept back can result in the forward movement of the aerodynamic center and the deterioration of the longitudinal static stability. The shock disturbance induced by plasma can suppress the flow separation of the suction surface, thereby extending the linear section of the lift curve of the model, preventing the aerodynamic center from moving forward, and improving the longitudinal static stability. When the wind speed is 50 m/s, the plasma control improves the horizontal rudder efficiency at a high angle of attack of the flying wing model, increases the maximum lift coefficient of the model by about 0.1, and postpones the stall angle of attack by more than 4° at different rudder angles. The plasma control allows the flying model to follow the command movement better while flying, increases the flying pitch limit angle from 11.5° to 15.1°, reduces the amplitude of longitudinal disturbance motion by 2°, and reduces the oscillation attenuation time from 15 to 8 s, thereby improving the longitudinal flight maneuverability and stability of the flying wing model. It can be seen that plasma flow control technology has great potential applications in improving the flight quality of flying wing layout.
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Keywords:
- plasma /
- flow control /
- flying wing /
- wind tunnel test
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图 5 等离子体电源和飞翼模型安装
Fig. 5. The installation of plasma power supply and flying wing model.
图 6 风洞试验段的等离子体控制飞翼模型
Fig. 6. The fly wing model with plasma control in the test section.
图 7 粒子图像测速(PIV)试验设备布局图
Fig. 7. Schematic diagram of particle image velocimetry (PIV) test set-up.
图 10 α = 10°时P1剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 10. The velocity cloud map of PIV test on P1 at α = 10°: (a) Plasma off; (b) plasma on.
图 11 α = 10°时P2剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 11. The velocity cloud map of PIV test on P2 at α = 10°: (a) Plasma off; (b) plasma on.
图 12 α = 12°时P1剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 12. The velocity cloud map of PIV test on P1 at α = 12°: (a) Plasma off; (b) plasma on.
图 13 α = 12°时P2剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 13. The velocity cloud map of PIV test on P2 at α = 12°: (a) Plasma off; (b) plasma on.
图 14 α = 14°时P1剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 14. The velocity cloud map of PIV test on P1 at α = 14°: (a) Plasma off; (b) plasma on.
图 15 α = 14°时P2剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 15. The velocity cloud map of PIV test on P2 at α = 14°: (a) Plasma off; (b) plasma on.
图 16 α = 16°时P1剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 16. The velocity cloud map of PIV test on P1 at α = 16°: (a) Plasma off; (b) plasma on.
图 17 α = 18°时P1剖面PIV试验速度云图 (a)无等离子体; (b)有等离子体
Fig. 17. The velocity cloud map of PIV test on P1 at α = 18°: (a) Plasma off; (b) plasma on.
图 18 V = 27 m/s飞翼模型等离子体控制试验曲线 (a) 升力系数曲线; (b) 阻力系数曲线; (c) 俯仰力矩系数曲线
Fig. 18. The test curve of plasma flow control on flying wing at V = 27 m/s: (a) Lift coefficient curves; (b) drag coefficient curves; (c) pitching moment coefficient curves.
图 19 V = 50 m/s时不同升降舵舵偏时等离子体控制试验曲线 (a) 升力系数曲线; (b) 阻力系数曲线; (c) 俯仰力矩系数曲线; (d) 滚转力矩系数曲线; (e) 偏航力矩系数曲线; (f) 侧力系数曲线
Fig. 19. The plasma control test curve for different elevator deflection at V = 50 m/s: (a) Lift coefficient curves; (b) drag coefficient curves; (c) pitching moment coefficient curves; (d) roll moment coefficient curves; (e) yaw moment coefficient curves; (f) lateral force coefficient.
图 20 飞翼布局模型升降舵舵效随迎角变化的曲线
Fig. 20. Elevator efficiency curves of flying wing model with angle of attack.
图 21 等离子体控制对飞翼模型纵向扰动运动的影响 (a) 不加等离子体控制俯仰角时间历程曲线; (b) 等离子体控制时俯仰角时间历程曲线; (c) 不加等离子体控制俯仰角速度时间历程; (d) 等离子体控制俯仰角速度时间历程
Fig. 21. The influence of plasma control on the longitudinal disturbance motion of flying wing model: (a) Time history curve of pitch angle without plasma control; (b) time history curve of pitch angle with plasma control; (c) time history curve of pitch angle velocity without plasma control; (d) time history curve of pitch angle velocity with plasma control.
图 22 等离子体控制对飞翼模型纵向操纵控制的影响 (a)不加等离子体控制俯仰角时间历程曲线; (b) 等离子体控制时俯仰角时间历程曲线; (c)不加等离子体控制俯仰角速度时间历程; (d)等离子体控制俯仰角速度时间历程
Fig. 22. The influence of plasma control on the longitudinal control of flying wing model: (a) Time history curve of pitch angle without plasma control; (b) time history curve of pitch angle with plasma control; (c) time history curve of pitch angle velocity without plasma control; (d) time history curve of pitch angle velocity with plasma control.
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[1] Wood R, Bauer S 2001 39th Aerospace Sciences Meeting and Exhibit Reno, Nevada, January 8−11, 2001
[2] 王豪杰, 李杰, 周洲 2011 西北工业大学学报 29 789
Google Scholar
Wang H J, Li J, Zhou Z 2011 J. Northwestern Polytech. Univ. 29 789
Google Scholar
[3] Nangia R, Palmer M 2002 AIAA Atmospheric Flight Mechanics Conference and Exhibit Monterey, California, August 5−8, 2002
[4] 吴云, 李应红 2015 航空学报 36 381
Google Scholar
Wu Y, Li Y H 2015 Acta Aeronaut. Astronaut. Sin 36 381
Google Scholar
[5] Zhao Z J, Li J M, Zheng J G, Gui Y, Khoo B 2014 AIAA J. 53 1336
Google Scholar
[6] 张鑫, 黄勇, 王勋年, 王万波, 唐坤, 李华星 2016 航空学报 37 1733
Google Scholar
Zhang X, Huang Y, Wang X N, Wang W B, Tang K, Li H X 2016 Acta Aeronaut. Astronaut. Sin. 37 1733
Google Scholar
[7] 史志伟, 杜海, 李铮, 陆纪椿, 蒋旋 2017 高压电器 53 72
Google Scholar
Shi Z W, Du H, Li Z, Lu J C, Jiang X 2017 High Voltage Appar. 53 72
Google Scholar
[8] 李应红, 吴云, 梁华, 宋慧敏, 贾敏 2010 科学通报 55 3060
Google Scholar
Li Y H, Wu Y, Liang H, Song H M, Jia M 2010 Chin. Sci. Bull. 55 3060
Google Scholar
[9] 杜海, 史志伟, 程克明, 李甘牛, 宋天威, 李铮 2016 航空学报 37 2102
Google Scholar
Du H, Shi Z W, Cheng K M, Li G N, Song T W, Li Z 2016 Acta Aeronaut. Astronaut. Sin. 37 2102
Google Scholar
[10] Thomas F, Corke T, Iqbal M, Kozlov A, Schatzman D 2009 AIAA J. 47 2169
Google Scholar
[11] Xie Q, Gan W Y, Zhang C, Che X K, Yan P, Shao T 2019 IEEE Trans. Dielectr. Electr. Insul. 26 346
Google Scholar
[12] Yadalaa S, Hehner M, Serpieri J, Benard N, Dorr P, Kloker M, Kotsonis M 2018 J. Fluid Mech. 844 R2
Google Scholar
[13] Duong A, Midya S, Corke T, Hussain F, Thomas F 2019 11th International Symposium on Turbulence and Shear Flow Phenomena, Southampton, UK, July 30−August 2, 2019
[14] Corke T, Thomas F 2018 AIAA J. 56 1
Google Scholar
[15] Akbıyık H, Akansu Y, Yavuz H 2017 Flow Meas. Instrum. 53 215
Google Scholar
[16] Kwan P, Huang X 2019 IEEE Trans. Ind. Electron. 67 451
Google Scholar
[17] Correale G, Kotsonis M 2017 Exp. Therm. Fluid Sci. 81 406
Google Scholar
[18] Singhal A, Castaneda D, Webb N, Samimy M 2017 AIAA J. 56 1
Google Scholar
[19] Moreau E, Debien A, Benard N, Zouzou N 2016 IEEE Trans. Plasma Sci. 44 2803
Google Scholar
[20] Komuro A, Takashima K, Tanaka N, Konno K, Nonomura T, Kaneko T, Ando A Asai K 2018 Exp. Fluids 59 129
Google Scholar
[21] Singh A, Durasiewicz C, Little J 2017 70th Annual Meeting of the APS Division of Fluid Dynamics Denver, Colorado, November 19−21, 2017
[22] Kaparos P, Koltsakidis S, Panagiotou P, Yakinthos K 2018 2018 Flow Control Conference Atlanta, Georgia, June 25−29, 2018
[23] Keisar D, Hasin D, Greenblatt D 2018 AIAA J. 57 1
Google Scholar
[24] Patel M P, Ng T T, Vasudevan S, Corke T C, He C 2007 J. Aircr. 44 1264
Google Scholar
[25] Matsuno T, Kawaguchi M, Yamada G, Kawazoe H 2013 29th AIAA Applied Aerodynamics Conference Honolulu, Hawaii, 27 June 27–30, 2011
[26] Kwak D, Nelson R 2010 5th Flow Control Conference Chicago, Illinois, June 28−July 01, 2010
[27] Nelson R, Corke T, He C, Othman H, Matsuno T, Patelk M, Ng T 2007 45th AIAA Aerospace Sciences Meeting and Exhibit Reno, Nevada, January 8−11, 2007
[28] Grundmann S, Frey M, Tropea C 2009 47th AIAA Aerospace Science Meeting Orlando, Florida, USA, January 5−8, 2009
[29] Friedrichs W 2014 Ph. D. Dissertation (Darmstadt: Darmstadt University of Technology)
[30] 牛中国, 胡秋琦, 梁华, 刘捷, 许相辉, 蒋甲利 2019 推进技术 40 2816
Google Scholar
Niu Z G, Hu Q Q, Liang H, Liu J, Xu X H, Jiang J L 2019 J. Propul. Technol. 40 2816
Google Scholar
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