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高超声速飞行器尾喷管的优化设计

曹德一 李椿萱

曹德一, 李椿萱. 高超声速飞行器尾喷管的优化设计[J]. 北京航空航天大学学报, 2007, 33(10): 1162-1165.
引用本文: 曹德一, 李椿萱. 高超声速飞行器尾喷管的优化设计[J]. 北京航空航天大学学报, 2007, 33(10): 1162-1165.
Cao Deyi, Lee Chunhian. Optimal design of nozzle for hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(10): 1162-1165. (in Chinese)
Citation: Cao Deyi, Lee Chunhian. Optimal design of nozzle for hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(10): 1162-1165. (in Chinese)

高超声速飞行器尾喷管的优化设计

详细信息
    作者简介:

    曹德一(1980-),男,辽宁本溪人,博士生,CaoDy@ase.buaa.edu.cn.

  • 中图分类号: V 231.3

Optimal design of nozzle for hypersonic vehicle

  • 摘要: 以喷管上壁折转角、下壁长度、舵面长度及其折转角为设计变量,结合遗传算法和特征线法对高超声速飞行器尾喷管进行了优化设计,并对设计变量进行了参数研究.结果表明,所采用的优化设计方法计算效率高且比较准确,特别适合于高超声速飞行器尾喷管的优化设计;所采用的4个设计参数均能有效地影响尾喷管的气动性能,其中喷管上壁折转角和舵面折转角分别对喷管的升力和推力的影响相对明显,对其进行均衡选择方能得到最优的结果.

     

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出版历程
  • 收稿日期:  2006-10-13
  • 刊出日期:  2007-10-31

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