留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

吸气式高超声速飞行器冷流试验设计及验证

邓帆 杜新 谭慧俊 曾宪政

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. doi: 10.13700/j.bh.1001-5965.2013.0617
引用本文: 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. doi: 10.13700/j.bh.1001-5965.2013.0617
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)

吸气式高超声速飞行器冷流试验设计及验证

doi: 10.13700/j.bh.1001-5965.2013.0617
详细信息
    作者简介:

    邓帆(1982-),男,四川三台人,高级工程师,dengfan8245@sina.cn.

  • 中图分类号: V211.3;V211.7

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

  • 摘要: 对于吸气式飞行器而言,地面冷流试验是检验其进气道性能及气动特性的一项重要手段.以二元混压式进气道、机体/推进系统耦合为基本特征,设计了采用超燃冲压发动机为推进系统的内外流一体化巡航飞行器,针对其高超声速特性开展了冷流风洞试验,来流速度范围Ma=5.0~7.0,攻角范围α=-4°~8°.测压试验结果表明,随着来流马赫数的增大,进气道的总压恢复系数下降;而流量系数先上升,在设计点达到最大值;在一定攻角范围内,进气道的总压恢复系数和流量系数提高,但当攻角增大至巡航攻角时,随着攻角的增大,进气道的总压恢复系数和流量系数逐渐下降.测力试验验证了数值算法的有效性,除轴向力系数以外,其余气动特性系数的发展规律及数值基本吻合,可通过修正试验值的方式外推出飞行器的气动特性数据.

     

  • [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)

  • 加载中
计量
  • 文章访问数:  823
  • HTML全文浏览量:  38
  • PDF下载量:  690
  • 被引次数: 0
出版历程
  • 收稿日期:  2013-10-30
  • 网络出版日期:  2014-10-20

目录

    /

    返回文章
    返回
    常见问答