多喷管火箭上升段羽流流场及其底部热环境

任帆涛; 姜毅; 刘汉宇; 贾启明

doi:10.13224/j.cnki.jasp.20230575

多喷管火箭上升段羽流流场及其底部热环境

doi: 10.13224/j.cnki.jasp.20230575

任帆涛^1,,
姜毅^1,*, ,,
刘汉宇²,
贾启明³

1.
北京理工大学宇航学院，北京 100081
2.
北京宇航系统工程研究所，北京 100076
3.
北京电子工程总体研究所，北京 100854

基金项目: GF基础科研项目（JCKY2021602b030）

详细信息

作者简介:
任帆涛（1999-），男，硕士生，主要从事火箭发射燃气动力学研究。E-mail：rftao_2018@163.com

通讯作者:
姜毅（1965-），男，教授、博士生导师，博士，主要从事航天发射技术研究。E-mail：jy2818@163.com

中图分类号: V434
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出版历程
- 收稿日期: 2023-09-08
- 网络出版日期: 2024-06-28

Plume flow field and base heating environment of the multi-nozzle rocket in ascent phase

REN Fantao^1
,,
JIANG Yi^{1,*
, ,},
LIU Hanyu²,
JIA Qiming³

1.
School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China
2.
Beijing Institute of Astronautical Systems Engineering，Beijing 100076，China
3.
Beijing Institute of Electronic System Engineering，Beijing 100854，China

摘要

摘要:
针对多喷管并联运载火箭上升段羽流流场结构与底部加热导致的火箭热防护问题，建立了九喷管构型运载火箭分析模型，通过数值仿真研究了不同高度下的羽流流场及底部热环境现象。通过与风洞试验数据对比，验证了数值方法的可靠性。分析结果表明：多喷管运载火箭上升段射流间发生碰撞，不同海拔高度分别出现了循环涡、燃气回流以及反溅等现象，高度越高，射流膨胀角越大。飞行高度较低时，箭体底部加热主要以辐射加热为主；随着高度增加，对流加热的影响增大。底部热流密度峰值出现在30～40 km范围内，对流热流密度最大为318.16 kW/m²，辐射热流密度最大为315.38 kW/m²，总热流密度最大为570.31 kW/m² 。底板温度梯度是对流加热的主要影响因素，辐射加热主要受辐射强度、距离及辐射微元面积影响。
- 液体运载火箭 /
- 燃气羽流 /
- 对流热/辐射热 /
- 多喷管 /
- 底部热环境
Abstract:
A nine-nozzle configuration rocket was established for the heating protection problem of the multi-nozzle rocket caused by the plume flow field structure and base heating in the ascent phase. Compared with the wind tunnel test data, the reliability of the numerical method was verified, and the numerical simulations were carried out for the plume flow field and the base heating environment at different altitudes. The results indicated that collisions occurred between gas jets, and there existed circulation vortices, gas backflow and back splash at different altitudes. The higher altitude indicated the greater expansion angle of the jet. At low flight altitudes, the base heating was mainly affected by radiation heating, and as the altitude increased, the effect of convection heating was enhanced. The peak of base heating flow density occurred within the range of 30 km to 40 km, with a maximum convective heating flow density of 318.16 kW/m², a maximum radiant heating flow density of 315.38 kW/m² and a maximum total heating flow density of 570.31 kW/m². The temperature gradient of rocket base was the main influence on convection heating, while radiation heating was mainly influenced by the radiation intensity, distance and area of the radiation micro-element.
- liquid rocket /
- gas jet and plume /
- convection/radiative heating transfer /
- multi-nozzle /
- base heating environment

HTML

图 1 箭体几何模型

Figure 1. Geometric model of the rocket

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图 2 喷管安装位置（单位：mm）

Figure 2. Disposition of nozzle installation （unit：mm）

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图 3 网格划分及边界条件

Figure 3. Grid division and boundary conditions

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图 4 底部热流密度沿径向分布对比

Figure 4. Comparison of the radial distribution of heating flow density at the bottom

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图 5 切面取样方式

Figure 5. Sampling section method

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图 6 马赫数云图

Figure 6. Contours of Mach number

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图 7 火箭底部流场动压云图

Figure 7. Contours of dynamic pressure distribution in the bottom of rocket

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图 8 对流热流密度云图

Figure 8. Contours of convective heating flow density

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图 9 对流热流密度径向分布

Figure 9. Radial distribution of the convection heating flow density

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图 10 湍流强度沿径向分布

Figure 10. Radial distribution of the turbulence intensity

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图 11 温度沿径向分布

Figure 11. Radial distribution of temperature

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图 12 辐射热流密度云图

Figure 12. Contours of the radiant heating flow density

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图 13 辐射热流密度径向分布

Figure 13. Radial distribution of the radiant heating flow density

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图 14 不同海拔热流密度最大值分布

Figure 14. Distribution of maximum heating flow density at different altitudes

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表 1 气体摩尔分数

Table 1. Molar percentage of gases

气体组分	摩尔分数/%
${{\mathrm{H}}_2}{\mathrm{O}}$	0.3741
${\mathrm{C}}{{\mathrm{O}}_2}$	0.2932
${\mathrm{CO}}$	0.2404
${{\mathrm{H}}_2}$	0.0301
${\mathrm{OH}}$	0.0229
${{\mathrm{O}}_2}$	0.0126
其他	0.0267

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表 2 环境参数

Table 2. Atmospheric environmental parameters

工况	飞行高度/km	来流马赫数	压强/Pa	温度/K
1	5	0.65	54019.91	255.65
2	10	1.28	26436.23	223.15
3	16	1.81	12044.60	216.65
4	25	2.83	2511.02	221.65
5	35	3.62	558.92	237.05
6	45	4.24	143.13	265.05
7	50	4.87	75.94	270.65
8	55	5.70	39.97	259.45
9	65	7.25	9.92	231.45

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