Experimental research on aerodynamic force effect of multiple plumes based on pressure-sensitive paint technique
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摘要:
多股羽流相互作用会形成复杂流场形态的干扰羽流，为了对干扰羽流开展气动力效应试验研究，采用压敏漆（PSP）表面压力光学测量技术，对以常温空气为工质的单喷嘴羽流和双喷嘴干扰羽流撞击平板模型的气动力进行了高分辨率的全场测量，分析了喷嘴和平板间不同入射距离和入射角对羽流气动力作用强度和范围的影响。试验结果表明，以高透氧聚合物为基层的压敏漆在羽流气动力测量中具有快速响应的特性，能分辨Pa级的微小压力变化。相对传统离散测压孔方法，压敏漆温度敏感度低，能捕捉大梯度的压力变化，准确描述羽流气动力效应。通过对比，发现干扰羽流对气动力具有明显增强作用，且增强作用随着入射距离的降低而减弱，干扰羽流的气动力不能直接用单股羽流的气动力进行线性叠加；羽流相互作用增强羽流返流，在航天器设计中需要考虑多股羽流相互作用后的羽流防护问题。
Abstract:The interaction of multiple plumes may cause interacted plumes with complex flow field. To experimentally study the aerodynamic force effects of interacted plumes, an optical measurement technique for surface pressure based on Pressure-Sensitive Paint (PSP) was employed to globally measure the aerodynamic force of a plate model impinged by single-and dual-nozzle plumes which used normal-temperature air as the working gas with high resolution. The strength and region of the aerodynamic force under different distances and angles between the nozzles and the plate were analyzed. The experimental results show that PSP using poly(TMSP) as the binder and PtTFPP as the luminophore exhibits fast response and can distinguish tiny pressure variation of Pa level in the plume aerodynamic force measurement. Compared to the conventional method based on discrete pressure taps, PSP is low temperature-dependent, is capable of measuring large pressure gradient, and can accurately describe the aerodynamic force effect of plume. It is found that the aerodynamic force is significantly enhanced by the interacted plumes, and the enhancement effect decreases as the incident distance reduces. The aerodynamic force of the interacted plumes cannot be directly superimposed by those of single plumes linearly. Plume interaction enhances the backflow intensity, and thus the plume shield after multi-plume interaction should be taken into account in spacecraft design.
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图 1 基于PSP的羽流撞击平板气动力试验系统示意图
Figure 1. Experimental system schematic of aerodynamic force induced by plumes impinging plate based on PSP
图 2 气动力试验系统坐标系XOY平面
Figure 2. XOY plane of coordinate system in aerodynamic force experiment
图 3 真空舱中进行的PSP气动力试验流程
Figure 3. Flowchart of aerodynamic force experiment based on PSP in vacuum chamber
图 4 原位点对点标定法计算表面压力分布流程示意
Figure 4. Flowchart of calculating surface pressure distribution using in-situ point-to-point calibration method
图 5 Kulite压力传感器压力和PSP压力随时间变化的典型关系曲线(h=5 mm，β=20°)
Figure 5. Representative time-history plots of Kulite sensor and PSP pressures(h=5 mm, β=20°)
图 6 单喷嘴羽流撞击平板模型表面压力分布云图
Figure 6. Surface pressure distribution contour of single-nozzle plume impinging plate model
图 7 单喷嘴羽流在不同入射距离和入射角时沿平板中线上的压力分布曲线
Figure 7. Pressure distribution curves along plate center line of single-nozzle plume with different incident distances and angles
图 8 双喷嘴干扰羽流撞击平板模型表面压力分布云图
Figure 8. Surface pressure distribution contour of dual-nozzle interacted plumes impinging plate model
图 9 单、双喷嘴羽流沿平板X=3 mm的压力分布对比
Figure 9. Comparison of pressure distribution along line X=3 mm on plate between single- and dual-nozzle plumes
图 10 双喷嘴干扰羽流气动力沿平板中线的压力分布与单喷嘴羽流在相同轴线偏移线的压力分布比较
Figure 10. Comparison of pressure distribution of aerodynamic force along center line of plate in dual-nozzle interacted plumes and along the same off-axis line in single-nozzle plume
表 1 单喷嘴羽流在不同入射距离和入射角时平板中线上的压力最大值及位置
Table 1. Maximum pressures and their locations on plate center line of single-nozzle plume with different incident distances and angles
工况 压力最大值/Pa 最大值X坐标/mm h=5 mm, β=20° 276 3.0 h=5 mm, β=10° 187 3.5 h=2 mm, β=20° 1 496 1.5 h=2 mm, β=10° 836 2.0 
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[1] BOYD I D, STARK J P W.Assessment of impingement effects in the isentropic core of a small satellite control thruster plume[J].Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering, 1989, 203(2):97-103. doi: 10.1243/PIME_PROC_1989_203_060_01 [2] DETTLEFF G.Plume flow and plume impingement in space technology[J].Progress in Aerospace Sciences, 1991, 28(1):1-71. doi: 10.1016-0376-0421(91)90008-R/ [3] 蔡国飙, 祖国君, 王慧玉, 等.羽流问题研究概况[J].推进技术, 1995, 16(4):50-54. http://d.old.wanfangdata.com.cn/Conference/271220CAI G B, ZU G J, WANG H Y, et al.The sketchy situation of study on plume[J].Journal of Propulsion Technology, 1995, 16(4):50-54(in Chinese). http://d.old.wanfangdata.com.cn/Conference/271220 [4] 张建华, 贺碧蛟, 蔡国飙, 等.卫星姿控发动机喷管羽流撞击效应试验[J].空气动力学学报, 2007, 25(2):250-255. doi: 10.3969/j.issn.0258-1825.2007.02.021ZHANG J H, HE B J, CAI G B, et al.Experimental study on plume impingement effects of satellite attitude control thruster nozzle[J].Acta Aerodynamica Sinica, 2007, 25(2):250-255(in Chinese). doi: 10.3969/j.issn.0258-1825.2007.02.021 [5] GERASIMOV Y I, KRYLOV A N, YARYGIN V N.Structure and gas parameters of plume expiring into vacuum from four nozzles located around the space vehicle case[C]//Proceedings of the 25th International Symposium on Rarefied Gas Dynamics.St.Petersburg: AIP Publishing, 2006: 610-615. [6] GERASIMOV Y I, YARYGIN V N, KRYLOV A N, et al.Modelling of the flow structure in a composite jet behind two thrusters located near the spacecraft case[J].Thermophysics and Aeromechanics, 2009, 16(3):375-383. doi: 10.1134/S0869864309030068 [7] WU J, CAI G B, HE B J, et al.Experimental and numerical investigations of vacuum plume interaction for dual hydrogen/oxygen thrusters[J].Vacuum, 2016, 128:166-177. doi: 10.1016/j.vacuum.2016.03.020 [8] PIESIK E T, KOPPANG R R, SIMKIN D J.Rocket-exhaust impingement on a flat plate at high vacuum[J].Journal of Spacecraft & Rockets, 1966, 3(11):1650-1657. http://cn.bing.com/academic/profile?id=f3fe9f21811bc964cbb4bcb606410945&encoded=0&v=paper_preview&mkt=zh-cn [9] 王文龙, 周建平, 蔡国飙.钟型喷管10 N推力器冷流羽流气动力试验研究[J].空间控制技术与应用, 2013, 39(1):51-56. doi: 10.3969/j.issn.1674-1579.2013.01.009WANG W L, ZHOU J P, CAI G B.On the aerodynamic force experiment of vacuum plume for 10 N bell-shaped thruster[J].Aerospace Control and Application, 2013, 39(1):51-56(in Chinese). doi: 10.3969/j.issn.1674-1579.2013.01.009 [10] GREGORY J W, SAKAUE H, LIU T, et al.Fast pressure-sensitive paint for flow and acoustic diagnostics[J].Annual Review of Fluid Mechanics, 2014, 46(1):303-330. http://cn.bing.com/academic/profile?id=a4d97f04c3c994cac973e55699c45f15&encoded=0&v=paper_preview&mkt=zh-cn [11] 林敬周, 解福田, 钟俊, 等.高超声速风洞压敏漆试验技术[J].航空学报, 2017, 38(7):192-200. http://d.old.wanfangdata.com.cn/Periodical/hkxb201707016LIN J Z, JIE F T, ZHONG J, et al.Pressure sensitive paint test technique in hypersonic wind tunnel[J].Acta Aeronautica et Astronautica Sinica, 2017, 38(7):192-200(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/hkxb201707016 [12] PENG D, GREGORY J W.Asymmetric distributions in pressure/load fluctuation levels during blade-vortex interactions[J]. Journal of Fluids and Structures, 2017, 68:58-71. doi: 10.1016/j.jfluidstructs.2016.10.008 [13] ANYOJI M, NUMATA D, NAGAI H, et al.Pressure-sensitive paint technique for surface pressure measurements in a low-density wind tunnel[J].Journal of Visualization, 2015, 18(2):297-309. doi: 10.1007/s12650-014-0239-9 [14] MORI H, NIIMI T, HIRAKO M, et al.Pressure sensitive paint suitable to high knudsen number regime[J].Measurement Science and Technology, 2006, 17(6):1242-1246. doi: 10.1088/0957-0233/17/6/S02 [15] NIIMI T, YOSHIDA M, KONDO M, et al.Application of pressure-sensitive paints to low-pressure range[J].Journal of Thermophysics and Heat Transfer, 2005, 19(1):9-16. http://cn.bing.com/academic/profile?id=a964d93799bfa56f4f1c83923002ba28&encoded=0&v=paper_preview&mkt=zh-cn [16] MORI H, NIIMI T, YOSHIDA M, et al.Application of psp to low density gas flows[J].Journal of Visualization, 2004, 7(1):55-62. doi: 10.1007/BF03181485 [17] NIIMI T, MORI H, YAMAGUCHI H, et al.Experimental analyses of high knudsen number flows[J].International Journal of Emerging Multidisciplinary Fluid Sciences, 2009, 1(3):213-227. doi: 10.1260/175683109789686691 [18] MATSUDA Y, MORI H, NIIMI T, et al.Development of pressure sensitive molecular film applicable to pressure measurement for high knudsen number flows[J].Experiments in Fluids, 2007, 42(4):543-550. doi: 10.1007/s00348-007-0259-5 [19] LIU T, SULLIVAN J P. Pressure and temperature sensitive paints[M]. Berlin:Springer, 2005. [20] EGAMI Y, IIGIMA Y, ASAI K.Optimization of polymer-based psp for cryogenic wind tunnels[C]//19th International Congress on Instrumentation in Aerospace Simulation Facilities, 2001: 177-185. [21] WU J, BITTER M, CAI G B, et al.Investigation on aerodynamic force effect of vacuum plumes using pressure-sensitive paint technique and CFD-DSMC solution[J].Science China Technological Sciences, 2017, 60(7):1058-1067 doi: 10.1007/s11431-016-9015-7 -
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