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双喷管运载火箭起飞阶段发射平台热环境研究

赵晨耕 乐贵高 苏逸飞 孙中一 王逸尘

赵晨耕, 乐贵高, 苏逸飞, 等. 双喷管运载火箭起飞阶段发射平台热环境研究[J]. 航空动力学报, 2024, 39(9):20220717 doi: 10.13224/j.cnki.jasp.20220717
引用本文: 赵晨耕, 乐贵高, 苏逸飞, 等. 双喷管运载火箭起飞阶段发射平台热环境研究[J]. 航空动力学报, 2024, 39(9):20220717 doi: 10.13224/j.cnki.jasp.20220717
ZHAO Chengeng, LE Guigao, SU Yifei, et al. Investigations on thermal environment of launch pads during the two-nozzle launch vehicle launching[J]. Journal of Aerospace Power, 2024, 39(9):20220717 doi: 10.13224/j.cnki.jasp.20220717
Citation: ZHAO Chengeng, LE Guigao, SU Yifei, et al. Investigations on thermal environment of launch pads during the two-nozzle launch vehicle launching[J]. Journal of Aerospace Power, 2024, 39(9):20220717 doi: 10.13224/j.cnki.jasp.20220717

双喷管运载火箭起飞阶段发射平台热环境研究

doi: 10.13224/j.cnki.jasp.20220717
详细信息
    作者简介:

    赵晨耕(1997-),男,博士生,主要研究火箭导弹发射技术。E-mail:2846822647@qq.com

    通讯作者:

    乐贵高(1964-),男,研究员、博士生导师,博士,主要研究火箭导弹发射技术。E-mail:leguigao@njust.edu.cn

  • 中图分类号: V421.1

Investigations on thermal environment of launch pads during the two-nozzle launch vehicle launching

  • 摘要:

    以双喷管运载火箭动力系统构成的发射平台为研究对象,采用数值模拟的方法对火箭起飞阶段发射平台的热环境展开研究。基于三维可压缩Navier-Stokes方程、k-ε方程湍流模型、2阶迎风TVD(total variation diminishing)离散格式,构建了双喷管运载火箭燃气射流模型。研究表明:喷管中心轴线与导流槽的交点处为导流面的冲击最大处,温度和压强极高,火箭尾焰射流冲击导流槽造成的反溅可能会进一步恶化发射台的热环境。火箭起飞过程中的漂移会加大射流对发射台的冲击,使其表面温度和压强迅速升高,减少其使用寿命。该研究为运载火箭起飞阶段发射平台的热环境评估提供了有效的方法,对热防护系统的安全设计具有重要的工程应用价值。

     

  • 图 1  计算模型

    Figure 1.  Computational model

    图 2  计算网格

    Figure 2.  Computational grid

    图 3  不同工况下的流场分布

    Figure 3.  Flow field contours of different working conditions

    图 4  射流冲击斜板表面的压力分布

    Figure 4.  Pressure distributions on the inclined plate

    图 5  网格无关性验证

    Figure 5.  Grid independence verification

    图 6  不同高度下的运载火箭尾焰冲击导流槽流场

    Figure 6.  Impact flow field of the flame deflector at different altitudes

    图 7  不同高度下的导流槽底面温度和压强云图

    Figure 7.  Temperature and pressure contours of the flame deflector at different altitudes

    图 8  不同高度下的马赫数等值面和发射台表面温度云图

    Figure 8.  Mach number isosurface and temperature contours of the launch pad surface at different altitudes

    图 9  不同高度下的发射台表面温度云图

    Figure 9.  Temperature contours of the launch pad surface at different altitudes

    图 10  不同高度下的发射台表面压强云图

    Figure 10.  Pressure contours of the launch pad surface at different altitudes

    图 11  不同高度下的发射台表面温度和压强对比图

    Figure 11.  Comparison of temperature and pressure on the launch pad surface at different altitudes

    表  1  喷管入口处的摩尔分数

    Table  1.   Molar fraction at nozzle inlet

    组分摩尔分数
    H2O0.3883
    CO20.2622
    CO0.2551
    H20.0941
    H0.0002
    OH0.0001
    下载: 导出CSV

    表  2  斜板冲击工况设置

    Table  2.   Setting of inclined plate impact working condition

    工况号h/dRnp
    121.2
    231.2
    下载: 导出CSV

    表  3  尾焰冲击发射台工况设置

    Table  3.   Working conditions setting of impact launch pads

    工况号H/mD/m
    10.20
    220
    3100
    40.20.2545
    520.4018
    6101.0137
    下载: 导出CSV
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出版历程
  • 收稿日期:  2022-09-22
  • 网络出版日期:  2024-01-22

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