Advanced Search
Volume 40 Issue 10
Oct.  2014
Turn off MathJax
Article Contents
Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(10): 1341-1348.
Deng Fan, Du Xin, Tan Huijun, et al. Design and validation of cold-flow test for air-breathing hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(10): 1341-1348. doi: 10.13700/j.bh.1001-5965.2013.0617(in Chinese)
Citation: Deng Fan, Du Xin, Tan Huijun, et al. Design and validation of cold-flow test for air-breathing hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(10): 1341-1348. doi: 10.13700/j.bh.1001-5965.2013.0617(in Chinese)
shu

Design and validation of cold-flow test for air-breathing hypersonic vehicle

doi: 10.13700/j.bh.1001-5965.2013.0617
  • 1.

    Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing 100076, China

  • 2. Internal Flow Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • 3. The Second Institute, China Academy of Aerospace Aerodynamics, Beijing 100074, China

  • Received Date: 30 Oct 2013
  • Publish Date: 20 Oct 2014
    Abstract
  • Cold-flow test is an important method for air-breathing vehicle to validate the inlet capability and aerodynamic characteristics. An airframe/propulsion integrative cruise vehicle with scramjet egine was designed; two-dimensional mixed-compression inlet and airframe/propulsion system coupling was used. The cold-flow wind tunnel test of the model was finished in hypersonic wind tunnel. Experimental data was measured when free Mach number was 5.0,6.0,7.0, and angle of attack was between -4° and 8°. The pressure performance test results indicate that, with the increase of the free stream Mach number, the total pressure recovery coefficient decreases, while the mass flow ratio increases firstly, and the maximum is obtained at design point; with the range of the angle of attack to a certainty, the total pressure recovery coefficient and the flow ratio increases. But after the cruise angle of attack, with the increase of the angle of attack, the total pressure recovery coefficient and the mass flow ratio decreases. The aerodynamics force performance wind tunnel test results validate the efficiency of the numerical simulation method, which shows a consistent trend with the experimental results, except the axial force coefficient. The aerodynamics characteristics of air-breathing hypersonic cruise vehicle could be obtained by revising the experimental results.

     

    • FullText(HTML)
  • loading
    • References(18)
  • [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]
    William H H, David T P.Hypersonic airbreathing propulsion[M]. Washington D C:American Institute of Aeronautics and Astronautics,1994
    [3]
    Hiroaki K, Tetsuya S,Nobuhiro T.Optimization of airbreathing propulsion system for the TSTO spaceplane[R].AIAA-2001-1912,2001
    [4]
    Chavez F R, Schmidt D K.Analytical aero-propulsive/aeroelastic hypersonic vehicle model with dynamic analysis[J].Journal of Guidance Control and Dynamics,1994,17(6):1308-1319
    [5]
    Rudd L V, Pines D J.Integrated propulsion effects on dynamic stability and control of hypersonic waveriders[R].AIAA-2000-36948,2000
    [6]
    孟中杰,陈凯, 黄攀峰,等.高超声速飞行器机体/发动机耦合建模与控制[J].宇航学报,2008,29(5):1509-1524 Meng Zhongjie,Chen Kai,Huang Panfeng,et al.The coupling model and control between scramjet and airframe for hypersonic vehicle[J].Journal of Astronautics,2008,29(5):1509-1524(in Chinese)
    [7]
    Bolender M A, Doman D B.Nonlinear longitudinal dynamical model of an air-breathing hypersonic vehicle[J].Journal of Spacecraft and Rockets,2007,44(2):374-387
    [8]
    马辉,袁建平, 方群.吸气式高超声速飞行器动力学特性分析[J].宇航学报,2007,28(5):1100-1104MaHui,Yuan Jianping,Fang Qun.Dynamics analysis of air-breathing hypersonic vehicle[J].Journal of Astronautics,2007,28(5):1100-1104(in Chinese)
    [9]
    张晓嘉,梁德旺. 内压缩通道几何参数对高超声速进气道性能的影响[J].南京航空航天大学学报,2005,37(6): 685689 Zhang Xiaojia,Liang Dewang.Performance effects of geometry parameters on hypersonic inlet[J].Journal of Nanjing University of Aeronautics and Astronautics,2005,37(6):685-689(in Chinese)
    [10]
    Trapier S, Duveau P,Deck S.Experimental study of supersonic inlet buzz[R].AIAA-20451-244,2006
    [11]
    张晓嘉,梁德旺, 李博,等.典型二元高超声速进气道设计方法研究[J].航空动力学报,2007,22(8):1290-1296 Zhang Xiaojia,Liang Dewang,Li Bo,et al.Study of design method of typical two-dimensional hypeisonic inlet[J].Journal of Aerospace Power,2007,22(8):1290-1296(in Chinese)
    [12]
    洛广琦,郑九州, 宋頔源.考虑附面层影响的二元混压式进气道设计[J].航空动力学报,2009,24(9):2063-2068 Luo Guangqi,Zheng Jiuzhou,Song Diyuan.Design of a two-dimensional mixed-compression supersonic inlet with boundary layer consideration[J].Journal of Aerospace Power,2009, 24(9): 2063-2068(in Chinese)
    [13]
    Ryan P, Starkey M,Lewis J.Critical design issues for airbreathing hypersonic waverider missiles[J].Journal of Spacecraft and Rockets,2001,38(4):510-519
    [14]
    车竞,唐硕. 高超声速飞行器机身/超燃冲压发动机设计方法研究[J].试验流体力学,2006,20(2):41-49 Che Jing,Tang Shuo.Research of airframe/scramjet integrated design of hypersonic vehicle[J].Journal of Experiments in Fluid Mechanics,2006,20(2):41-49(in Chinese)
    [15]
    黎明,宋文艳,贺伟. 高超声速二维混压式前体/进气道设计方法研究[J].航空动力学报,2004,19(4):459-465 Li Ming,Song Wenyan,He Wei.Design method of two-dimensional hypersonic forebody/inlet of mixed compression[J].Journal of Aerospace Power,2004,19(4):459-465(in Chinese)
    [16]
    李留刚,谭慧俊, 孙姝,等.二元高超声速进气道不起动状态的信号特征及预警[J]. 航空学报,2010,31(12): 23242331 Li Liugang,Tan Huijun,Sun Shu,et al.Signal characteristics and prediction of unstarting process for two-dimensional hypersonic inlet[J].Acta Aeronautica et Astronautica Sinica,2010,31(12):2324-2331(in Chinese)
    [17]
    张红英,孙姝, 程克明,等.进气道工作状态对吸气式高超飞行器气动力特性影响的实验研究[J].宇航学报,2007,28(4):624-628 Zhang Hongying,Sun Shu,Cheng Keming,et al.Experimental investigation of inlet start/unstart influences on the aerodynamic characteristic of a hypersonic vehicle[J].Journal of Astronautics,2007,28(4):624-628(in Chinese)
    [18]
    罗金玲,徐敏,刘杰. 一体化外形的高超声速飞行器升阻特性研究[J].宇航学报,2007,28(6):1478-1481 Luo Jinling,Xu Min,Liu Jie.Research on lift and drag characteristics for the integrated configuration of hypersonic vehicle[J].Journal of Astronautics,2007,28(6):1478-1481(in Chinese)
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF
    XML

    Article Metrics

    Article views(797) PDF downloads(689) Cited by()
    Proportional views
    Related

    Copyright © Journal of Beijing University of Aeronautics and Astronautics

    Address: Editorial Department of Journal of Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing Post Code: 100191 Email: jbuaa@buaa.edu.cn

    Supported by: Beijing Renhe Information Technology Co., Ltd.    

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return