吸气式高超声速飞行器冷态测力试验支撑校正
|
摘要
吸气式高超声速飞行器整体外形与推进系统性能高度耦合,在风洞测力试验中,支撑机构不可避免会对其气动特性产生影响。针对该类飞行器冷态气动力试验中存在的支撑干扰问题,以基于乘波前体的机体/发动机一体化飞行器为研究对象开展试验和计算研究,对比了尾支撑、背支撑和背支撑+虚拟尾支撑3种风洞支撑机构对飞行器主要气动力参数的影响,并通过比较不同支撑方式的测量结果对气动力进行了校正。试验在来流马赫数4和6两个工况下进行。结果表明:相对于背支撑,尾支撑对飞行器气动力参数的影响较小,更适合作为吸气式高超声速飞行器冷态测力试验的支撑机构;结合背支撑和背支撑+虚拟尾支撑的方式,可以有效地对尾支撑测量结果进行校正,提供更为精准的气动力试验数据。
The supporting mechanism greatly influences the aerodynamic force measurement of the air-breathing hypersonic flight vehicles in wind tunnel tests.In this paper,the supporting interference is studied by both wind tunnel experiments and CFD.First,an integrated vehicle is developed based on the wedge-elliptical cone waverider configuration method.Three types of supporting mechanisms are adopted to conduct the force measurement at Mach 4 and 6 in the hypersonic wind tunnel,with the rear sting mount,the back blade mount,and the back blade mount+ dummy rear sting mount.And,a correction method is adopted here to account for the supporting interference.With this method,the interference increments due to the supporting mechanism can be eliminated from the results obtained from the rear sting mount.The result shows that all the supporting mechanisms have an influence on the aerodynamic force and the rear sting mount is more suitable to be used as the supporting mechanism with a less influence in contrast with the back blade and the back blade mount+ dummy rear sting mount.In addition,it is recommended to use the correction method to improve the measurement accuracy of the experiment data.
The supporting mechanism greatly influences the aerodynamic force measurement of the air-breathing hypersonic flight vehicles in wind tunnel tests.In this paper,the supporting interference is studied by both wind tunnel experiments and CFD.First,an integrated vehicle is developed based on the wedge-elliptical cone waverider configuration method.Three types of supporting mechanisms are adopted to conduct the force measurement at Mach 4 and 6 in the hypersonic wind tunnel,with the rear sting mount,the back blade mount,and the back blade mount+ dummy rear sting mount.And,a correction method is adopted here to account for the supporting interference.With this method,the interference increments due to the supporting mechanism can be eliminated from the results obtained from the rear sting mount.The result shows that all the supporting mechanisms have an influence on the aerodynamic force and the rear sting mount is more suitable to be used as the supporting mechanism with a less influence in contrast with the back blade and the back blade mount+ dummy rear sting mount.In addition,it is recommended to use the correction method to improve the measurement accuracy of the experiment data.
引文
[1]McClinton C R,Hunt J L,Ricketts R H,et al.Airbreathing hypersonic technology vision vehicles and development dreams[R].AIAA-1999-4978,1999.
[2]Kobayashi H,Sato T,Tanatsugu N.Optimization of airbreathing propulsion system for the TSTO spaceplane[R].AIAA-2001-1912,2001.
[3]邓帆,杜新,谭慧俊,等.吸气式高超声速飞行器冷流试验设计及验证[J].北京航空航天大学学报,2014,40(10):1341-1348.Deng F,Du X,Tan H J,et al.Design and validation of coldflow test for air-breathing hypersonic vehicle[J].Journal of Beijing University of Aeronautics and Astronautics,2014,40(10):1341-1348.
[4]王泽江,孙鹏,李绪国,等.吸气式高超声速飞行器内外流同时测力试验[J].航空学报,2015,36(3):797-803.Wang Z J,Sun P,Li X G,et al.Force test on internal and external flow simultaneous measurement of air-breathing hypersonic vehicle[J].Acta Aeronautica et Astronautica Sinica,2015,36(3):797-803.
[5]罗金玲,周丹,康宏琳,等.典型气动问题试验方法研究的综述[J].空气动力学学报,2014,32(5):600-609.Luo J L,Zhou D,Kang H L,et al.Summarization of experimental methods associated with typical aerodynamic issuses[J].Acta Aerodynamica Sinica,2014,32(5):600-609.
[6]唐志共,许晓斌,杨彦广,等.高超声速风洞气动力试验技术进展[J].航空学报,2015,36(1):86-97.Tang Z G,Xu X B,Yang Y G,et al.Research progress on hypersonic wind tunnel aerodynamic testing techniques[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):86-97.
[7]Holland S D,Woods W C,Engelund W C.Hyper-X research vehicle experimental aerodynamics test program overview[J].Journal of Spacecraft and Rockets,2001,38(6):828-835.
[8]Frendi A.On the CFD support for the Hyper-X aerodynamic database[C]//Proc of the 37th Aerospace Sciences Meeting and Exhibit,Aerospace Sciences Meetings.1999.
[9]Voland R T,Rock K E,Huebner L D,et al.Hyper-X engine design and ground test program[R].AIAA-1998-1532,1998.
[10]张红英,程克明,伍贻兆.某高超飞行器流道冷流特征及气动力特性研究[J].空气动力学学报,2009,27(1):119-123.Zhang H Y,Cheng K M,Wu Y Z.A study on the flowpath and the aerodynamic characteristics of a hypersonic vehicle[J].Acta Aerodynamica Sinica,2009,27(1):119-123.
[11]范晓樯,李桦,易仕和,等.侧压式进气道与飞行器机体气动一体化设计及实验[J].推进技术,2004,25(6):499-502.Fan X Q,Li H,Yi S H,et al.Experiment of aerodynamic performance for hypersonic vehicle integrated with sidewall compression inlet[J].Journal of Propulsion Technology,2004,25(6):499-502.
[12]金亮,柳军,罗世彬,等.高超声速一体化飞行器冷流状态气动特性研究[J].实验流体力学,2010,24(1):42-45.Jin L,Liu J,Luo S B,et al.Aerodynamic characterization of an integrated hypersonic vehicle[J].Journal of Experiments in Fluid Mechanics,2010,24(1):42-45.
[13]吴颖川,贺元元,贺伟,等.吸气式高超声速飞行器机体推进一体化技术研究进展[J].航空学报,2015,36(1):245-260.Wu Y C,He Y Y,He W,et al.Progress in airframe-propulsion integration technology of air-breathing hypersonic vehicle[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):245-260.
[14]谢飞,许晓斌,舒海锋,等.吸气式高超声速飞行器气动力试验研究[C]//第九届全国实验流体力学学术会议文集(上册).2013.Xie F,Xu X B,Shu H F,et al.Experiment study of aerodynamic performance for airbreathing hypersonic vehicle[C]//Proc of the 9th Chinese Experiments in Fluid Mechanics Technologies Conference.2013.
[15]Yin G L,Qin Y P,Yang Y.Numerical and experiment studies of the support interference in the force prediction of an airbreathing hypersonic flight vehicle[C]//Proc of the 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conferences.2017.
[16]王发民,李立伟,姚文秀,等.乘波飞行器构型方法研究[J].力学学报,2004,36(5):513-519.Wang F M,Li L W,Yao W X,et al.Research on waverider configuration method[J].Acta Mechanica Sinica,2004,36(5):513-519.
[2]Kobayashi H,Sato T,Tanatsugu N.Optimization of airbreathing propulsion system for the TSTO spaceplane[R].AIAA-2001-1912,2001.
[3]邓帆,杜新,谭慧俊,等.吸气式高超声速飞行器冷流试验设计及验证[J].北京航空航天大学学报,2014,40(10):1341-1348.Deng F,Du X,Tan H J,et al.Design and validation of coldflow test for air-breathing hypersonic vehicle[J].Journal of Beijing University of Aeronautics and Astronautics,2014,40(10):1341-1348.
[4]王泽江,孙鹏,李绪国,等.吸气式高超声速飞行器内外流同时测力试验[J].航空学报,2015,36(3):797-803.Wang Z J,Sun P,Li X G,et al.Force test on internal and external flow simultaneous measurement of air-breathing hypersonic vehicle[J].Acta Aeronautica et Astronautica Sinica,2015,36(3):797-803.
[5]罗金玲,周丹,康宏琳,等.典型气动问题试验方法研究的综述[J].空气动力学学报,2014,32(5):600-609.Luo J L,Zhou D,Kang H L,et al.Summarization of experimental methods associated with typical aerodynamic issuses[J].Acta Aerodynamica Sinica,2014,32(5):600-609.
[6]唐志共,许晓斌,杨彦广,等.高超声速风洞气动力试验技术进展[J].航空学报,2015,36(1):86-97.Tang Z G,Xu X B,Yang Y G,et al.Research progress on hypersonic wind tunnel aerodynamic testing techniques[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):86-97.
[7]Holland S D,Woods W C,Engelund W C.Hyper-X research vehicle experimental aerodynamics test program overview[J].Journal of Spacecraft and Rockets,2001,38(6):828-835.
[8]Frendi A.On the CFD support for the Hyper-X aerodynamic database[C]//Proc of the 37th Aerospace Sciences Meeting and Exhibit,Aerospace Sciences Meetings.1999.
[9]Voland R T,Rock K E,Huebner L D,et al.Hyper-X engine design and ground test program[R].AIAA-1998-1532,1998.
[10]张红英,程克明,伍贻兆.某高超飞行器流道冷流特征及气动力特性研究[J].空气动力学学报,2009,27(1):119-123.Zhang H Y,Cheng K M,Wu Y Z.A study on the flowpath and the aerodynamic characteristics of a hypersonic vehicle[J].Acta Aerodynamica Sinica,2009,27(1):119-123.
[11]范晓樯,李桦,易仕和,等.侧压式进气道与飞行器机体气动一体化设计及实验[J].推进技术,2004,25(6):499-502.Fan X Q,Li H,Yi S H,et al.Experiment of aerodynamic performance for hypersonic vehicle integrated with sidewall compression inlet[J].Journal of Propulsion Technology,2004,25(6):499-502.
[12]金亮,柳军,罗世彬,等.高超声速一体化飞行器冷流状态气动特性研究[J].实验流体力学,2010,24(1):42-45.Jin L,Liu J,Luo S B,et al.Aerodynamic characterization of an integrated hypersonic vehicle[J].Journal of Experiments in Fluid Mechanics,2010,24(1):42-45.
[13]吴颖川,贺元元,贺伟,等.吸气式高超声速飞行器机体推进一体化技术研究进展[J].航空学报,2015,36(1):245-260.Wu Y C,He Y Y,He W,et al.Progress in airframe-propulsion integration technology of air-breathing hypersonic vehicle[J].Acta Aeronautica et Astronautica Sinica,2015,36(1):245-260.
[14]谢飞,许晓斌,舒海锋,等.吸气式高超声速飞行器气动力试验研究[C]//第九届全国实验流体力学学术会议文集(上册).2013.Xie F,Xu X B,Shu H F,et al.Experiment study of aerodynamic performance for airbreathing hypersonic vehicle[C]//Proc of the 9th Chinese Experiments in Fluid Mechanics Technologies Conference.2013.
[15]Yin G L,Qin Y P,Yang Y.Numerical and experiment studies of the support interference in the force prediction of an airbreathing hypersonic flight vehicle[C]//Proc of the 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conferences.2017.
[16]王发民,李立伟,姚文秀,等.乘波飞行器构型方法研究[J].力学学报,2004,36(5):513-519.Wang F M,Li L W,Yao W X,et al.Research on waverider configuration method[J].Acta Mechanica Sinica,2004,36(5):513-519.