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多级压缩锥导/吻切锥乘波体设计与对比分析

吕侦军 王江峰

吕侦军, 王江峰. 多级压缩锥导/吻切锥乘波体设计与对比分析[J]. 北京航空航天大学学报, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740
引用本文: 吕侦军, 王江峰. 多级压缩锥导/吻切锥乘波体设计与对比分析[J]. 北京航空航天大学学报, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740
LYU Zhenjun, WANG Jiangfeng. Design and comparative analysis of multistage compression cone-derived waverider and osculating cone waverider[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740(in Chinese)
Citation: LYU Zhenjun, WANG Jiangfeng. Design and comparative analysis of multistage compression cone-derived waverider and osculating cone waverider[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(11): 2103-2109. doi: 10.13700/j.bh.1001-5965.2014.0740(in Chinese)

多级压缩锥导/吻切锥乘波体设计与对比分析

doi: 10.13700/j.bh.1001-5965.2014.0740
基金项目: 江苏高校优势学科建设工程项目
详细信息
    作者简介:

    吕侦军(1987-),男,江苏泰州人,博士研究生,lzhj1987124@126.com

    通讯作者:

    王江峰(1970-),男,江苏南京人,教授,wangjf@nuaa.edu.cn,主要研究方向为高超声速飞行器布局设计、燃烧流场数值模拟技术、气动加热计算技术等.

  • 中图分类号: V221+.3

Design and comparative analysis of multistage compression cone-derived waverider and osculating cone waverider

  • 摘要: 将乘波体作为以吸气式超燃冲压发动机为动力的高超声速飞行器的前体,不仅可以发挥乘波体优异的气动力性能,而且起到了高超声速飞行器前体对来流的预压缩作用.为了进一步提升乘波前体的预压缩作用,基于Sobieczky提出的吻切锥原理,发展了一种新的多级压缩乘波体外形的设计方法.将该设计方法应用到锥导和吻切锥乘波体的设计中,生成了具有多个压缩面的多级压缩锥导和吻切锥乘波体,同时对相同设计条件和具有相同投影曲线的前缘条件下获得的三级压缩锥导和吻切锥乘波体的性能进行了对比分析.研究结果表明数值模拟计算结果与设计预期完全吻合,该多级压缩乘波体设计方法可以应用于锥导和吻切锥乘波体.

     

  • [1] Nonweiler T R F.Aerodynamic problems of manned space vehicles[J].Journal of Royal Aeronautical Society, 1959, 63(9):512-528.
    [2] Rasmussen M L, Jischke M C, Daniel D C.Experimental forces and moments on cone-derived waveriders for M=3 to 5[J].Journal of Spacecraft and Rockets, 1982, 19(6):592-598.
    [3] Rasmussen M L, Jischke M C, Daniel D C.Waverider configurations derived from inclined circular and elliptic cones[J].Journal of Spacecraft and Rockets, 1980, 17(6):537-545.
    [4] Sobieczky H, Dougherty F C, Jones K D.Hypersonic waverider design from given shock waves[C]//First International Waverider Symposium.Maryland:University of Maryland, 1990.
    [5] Jones K D, Sobieczky H, Seebass A R, et al, Waverider design for generalized shock geometries[J].Journal of Spacecraft and Rockets, 1995, 32(6):957-963.
    [6] 王卓,钱翼稷.乘波机外形设计[J].北京航空航天大学学报, 1999, 25(2):180-183. Wang Z, Qian Y J.Waverider configuration design[J].Journal of Beijing University of Aeronautics and Astronautics, 1999, 25(2):180-183(in Chinese).
    [7] 刘嘉,王发民.乘波前体构型设计与压缩性能分析[J].工程力学, 2003, 20(6):130-134. Liu J, Wang F M.Waverider configuration design and forebody compressibility analysis[J].Engineering Mechanics, 2003, 20(6):130-134(in Chinese).
    [8] 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(in Chinese).
    [9] 姚文秀,雷麦芳,杨耀栋,等.高超声速乘波飞行器气动实验研究[J].宇航学报, 2002, 23(6):82-85. Yao W X, Lei M F, Yang Y D, et al.An aerodynamic experiment research of the hypersonic waverider vehicle[J].Journal of Astronautics, 2002, 23(6):82-85(in Chinese).
    [10] 吕浩宇,李椿萱,曹德一.乘波构型飞行器磁流体进气道一体化概念设计[J].北京航空航天大学学报, 2008, 34(10):1130-1134. Lü H Y, Lee C X, Cao D Y.Conceptual study on integrated design of magnetohydrodynamic by pass scramjet for a waverider based hypersonic vehicle[J].Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(10):1130-1134(in Chinese).
    [11] 贺旭照,倪鸿礼.密切内锥乘波体设计方法和性能分析[J].力学学报, 2011, 43(5):803-808. He X Z, Ni H L.Osculating inward turning cone(OIC) waverider design methods and performance analysis[J].Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(5):803-808(in Chinese).
    [12] 贺旭照,周正,毛鹏飞,等.密切曲面内锥乘波前体进气道设计和试验研究[J].实验流体力学, 2014, 28(3):39-44. He X Z, Zhou Z, Mao P F, et al.Design and experimental study of osculating inward turning cone waverider/inlet (OICWI)[J].Journal of Experiments in Fluid Mechanics, 2014, 28(3):39-44(in Chinese).
    [13] 张红文,张科南,陈万春.带静态参数的高超声速飞行器轨迹优化算法[J].北京航空航天大学学报, 2014, 40(2):141-147. Zhang H W, Zhang K N, Chen W C.Indirect method for trajectory optimization of hypersonic vehicle with static parameters[J].Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(2):141-147(in Chinese).
    [14] Harsha P T, Keel L C, Castrogiovanni A, et al.X-43A vehicle design and manufacture, AIAA-2005-3334[R].Reston:AIAA, 2005.
    [15] Matthew P B, Steven P S.Effect of freestream noise on roughness-induced transition for the X-51A forebody[J].Journal of Spacecraft and Rockets, 2008, 45(6):1106-1116.
    [16] 陈小庆,侯中喜,何烈堂,等.吻切锥乘波构型参数化设计与正交试验分析[J].推进技术, 2010, 31(4):385-389. Chen X Q, Hou Z X, He L T, et al.Parameterized design and orthogonal experiment analysis of osculating-cone waverider[J].Journal of Propulsion Technology, 2010, 31(4):385-389(in Chinese).
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出版历程
  • 收稿日期:  2014-11-27
  • 修回日期:  2015-01-04
  • 网络出版日期:  2015-11-20

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