吸气式高超声速飞行器通气模型测力试验技术研究
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摘要
由于内阻测量方法限制,来流Ma_∞>4时常规通气模型测力试验精度无法满足吸气式高超声速飞行器设计和性能评估需求。为解决上述问题,确保试验精度满足飞行器研究需要,探索了将天平测量内阻技术引入常规通气模型测力试验的可行性。从改进试验方法角度提出了一种回避内阻测量难题的新型试验方法:采用"尾支+六分量天平"直接测量通气模型的气动特性(机体控制体产生的气动力载荷),并开展了试验验证。结果表明:由于减少了内阻测量环节,新型测力试验技术的精度高,Ma_∞=6时的阻力系数误差小于2%,远低于常规通气模型测力试验误差,具有精度高、模型相对简单、技术复杂程度较低、推广应用可能性大的优势。
Due to the limitation of the method of internal drag measurement,the accuracy of traditional aerodynamic experiments of force test with ducted models(TFTDM)is unable to meet the demands of airframepropulsion integrated design and aerodynamic performance estimation for air-breathing hypersonic vehicles at Ma∞>4.0. To solve this problem and ensure the aerodynamic accuracy experiments meet the demands of hypersonic vehicles development,the feasibility of introducing the internal drag measurement with the balance into TFTDM is explored firstly. After that,a new technique of force direct-test with ducted models(FDTDM)is proposed from improving the experimental method of TFTDM,to avoid the problem of internal drag measurement,which principle is the balance measurement of aerodynamic forces acting on the external component(airframe control volume)of ducted models with sting-supported model. A verification test is conducted and the accuracy of the technique is estimated. The results indicate that,due to cutting down the testing link of internal drag measurement,the accuracy of FDTDM is very high with the errors of drag coefficients less than 2% at Ma∞=6 and far below that of TFTDM. FDTDM has many advantages,such as high accuracy,simpler model structure,low technical complexity,large possibility of spread and application etc..
Due to the limitation of the method of internal drag measurement,the accuracy of traditional aerodynamic experiments of force test with ducted models(TFTDM)is unable to meet the demands of airframepropulsion integrated design and aerodynamic performance estimation for air-breathing hypersonic vehicles at Ma∞>4.0. To solve this problem and ensure the aerodynamic accuracy experiments meet the demands of hypersonic vehicles development,the feasibility of introducing the internal drag measurement with the balance into TFTDM is explored firstly. After that,a new technique of force direct-test with ducted models(FDTDM)is proposed from improving the experimental method of TFTDM,to avoid the problem of internal drag measurement,which principle is the balance measurement of aerodynamic forces acting on the external component(airframe control volume)of ducted models with sting-supported model. A verification test is conducted and the accuracy of the technique is estimated. The results indicate that,due to cutting down the testing link of internal drag measurement,the accuracy of FDTDM is very high with the errors of drag coefficients less than 2% at Ma∞=6 and far below that of TFTDM. FDTDM has many advantages,such as high accuracy,simpler model structure,low technical complexity,large possibility of spread and application etc..
引文
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[18]许晓斌,舒海峰,谢飞,等.通气模型内流道阻力直接测量技术[J].推进技术,2013,34(3):311-315.(XU Xiao-bin,SHU Hai-feng,XIE Fei,et al. Technique Investigation on Flow Through Model Inner Flow Drag Straightway Measured by Strain-Gauge Balance[J]. Journal of Propulsion Technology,2013,34(3):311-315.)
[19]邓帆,杜新,谭辉俊,等.吸气式高超声速飞行器冷流试验设计与验证[J].北京航空航天大学学报,2014,40(10):1341-1348.
[2] Huffuman J K,Jonston P J,Pittman J K. Integrated Scramjet Installation Effect on the Subsonic Performance of a Hypersonic Aerocraft[J]. Journal of Aircraft,1978,15(6):326-332.
[3] Heiser W H,Pratt D T. Hypersonic Airbreathing Propulsion[M]. Washington D C:AIAA Inc.,1994.
[4]王勋年.低速风洞试验[M].北京:国防工业出版社,2002.
[5]王发祥.高速风洞试验[M].北京:国防工业出版社,2001.
[6]唐志共.高超声速气动力试验[M].北京:国防工业出版社,2004.
[7] Yu P Goon’ko. Aerodynamic Experimentation with Ducted Models as Applied to Hypersonic Air-Breathing Vehicles[J]. Experiments in Fluids,1999,27(3):219-234.
[8]余平,段毅,尘军.高超声速飞行的若干气动问题[J].应用力学学报,2015,36(1):7-23.
[9] Cubbage J,Kirkham F,Small W,et al. Studies of Airframe-Propulsion-System Integration for Mach 6 Vehicles[R]. NASA-TND-4128.
[10] Ellison J C. Investigation of the Aerodynamic Characteristics of a Hypersonic Transport Model at Mach Numbers to 6[R]. NASA-TND-6191.
[11]黄湛,张江,宫建,等. DPIV技术在高超声速通气模型内阻测量中的应用[J].应用力学学报,2014,31(2):182-187.
[12] Mitani T,Hiraiwa T,Tarukawa Y,et al. Drag and Total Pressure Distributions in Scranjet Engines at Mach 8Flight[J]. Journal of Propulsion and Power,2002,18(4):953-960.
[13] Carpenter D,Corpening G,Matters L,et al. An Experimental Technique for the Measurement of Mass Flow of Scramjet Inlets Tested in Hypersonic Pulse Facilities[R]. AIAA 89-2331.
[14] Ledere M,Mc Candless R,Yanta W,et al. High Speed Inlet Testing in the NAVSWC Wind Tunnels[R]. AIAA1990-1412.
[15] Holland S D. Internal Aerodynamics of a Generic ThreeDimensional Scramjet Inlet at Mach 10[R]. NASA-TP3476.
[16] Voland R T. Methods for Determining the Internal Thrust of Scramjet Engine Modules from Experimental Data[R]. AIAA 90-2340.
[17]张绍武,关祥东,朱涛,等.高超声速风洞进气道流量系数测量精度影响因素研究[J].推进技术,2013,34(4):470-476.(ZHANG Shao-wu,GUAN Xiang-dong,ZHU Tao,et al. Investigation on Factors Affecting the Measurement Accuracy for Inlet Flow Coefficient in Hypersonic Wind Tunnel[J]. Journal of Propulsion Technology,2013,34(4):470-476.)
[18]许晓斌,舒海峰,谢飞,等.通气模型内流道阻力直接测量技术[J].推进技术,2013,34(3):311-315.(XU Xiao-bin,SHU Hai-feng,XIE Fei,et al. Technique Investigation on Flow Through Model Inner Flow Drag Straightway Measured by Strain-Gauge Balance[J]. Journal of Propulsion Technology,2013,34(3):311-315.)
[19]邓帆,杜新,谭辉俊,等.吸气式高超声速飞行器冷流试验设计与验证[J].北京航空航天大学学报,2014,40(10):1341-1348.