搭载辅助动力系统的二级火箭底部热环境分析

孙中一; 王舒雅; 尉志源; 乐贵高

doi:10.7638/kqdlxxb-2023.0106

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搭载辅助动力系统的二级火箭底部热环境分析

研究论文 | 更新时间：2026-07-27

- 搭载辅助动力系统的二级火箭底部热环境分析
- Analysis on the thermal environment at the bottom of a secondary rocket equipped with an auxiliary power system
- 空气动力学学报 2024年42卷第7期页码：48-57
- 作者机构：
  
  1. 南京理工大学机械工程学院,南京,210094
  2. 中国船舶工业公司第七〇八研究所,上海,200000
- 作者简介：
  
  孙中一（1998—），男，黑龙江哈尔滨人，博士研究生，研究方向：火箭导弹发射技术. E-mail：982658200@qq.com
  乐贵高*（1964—），教授，研究方向：火箭导弹发射技术. E-mail：leguigao@njust.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0106
  中图分类号： V421.1
- 纸质出版：2024
- 稿件说明：
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孙中一, 王舒雅, 尉志源, 等. 搭载辅助动力系统的二级火箭底部热环境分析[J]. 空气动力学学报, 2024, 42(7): 48−57.

SUN Zhongyi, WANG Shuya, WEI Zhiyuan, et al. Analysis on the thermal environment at the bottom of a secondary rocket equipped with an auxiliary power system[J]. 2024, 42(7): 48-57.
孙中一, 王舒雅, 尉志源, 等. 搭载辅助动力系统的二级火箭底部热环境分析[J]. 空气动力学学报, 2024, 42(7): 48−57. DOI： 10.7638/kqdlxxb-2023.0106

SUN Zhongyi, WANG Shuya, WEI Zhiyuan, et al. Analysis on the thermal environment at the bottom of a secondary rocket equipped with an auxiliary power system[J]. 2024, 42(7): 48-57. DOI： 10.7638/kqdlxxb-2023.0106.

摘要

针对某二级运载火箭辅助动力系统发动机空间布局复杂、箭体底部部件数量多、底部热环境恶劣的情况，本文采用数值模拟和风洞试验验证相结合的方式开展高空二级运载火箭在辅助动力系统工作状态下箭体底部热环境研究。基于Navier-Stokes组分输运方程、DOM热辐射模型、RNG

-$\varepsilon $模型建立高空含复杂底部部件的二级运载火箭燃气喷流模型。结果表明：二级运载火箭在辅助动力系统工作时，高热流区域主要集中在燃料箱后短壳和辅助动力系统支座，沉底发动机工作时支座热流峰值最大，比其余部件高300%～400%。60 N、300 N发动机同向工作时，除支座和后短壳外的底部部件的热流达到峰值，比其余工况增长300%～600%。随着飞行高度和速度的增加，各部件热流均呈现下降趋势，但下降幅度较小。本文计算结果对二级运载火箭底部热防护设计有重要的工程指导意义。

Abstract

Certain secondary launch vehicle has complex spatial layouts of the auxiliary power system engine

which cause a harsher thermal environment where a large number of components are at the bottom of the rocket body. To address the aforementioned situation

research on the thermal environment at the bottom of the rocket body during the operation of the high-altitude secondary launch vehicle's auxiliary power system is conducted by means of a combined approach which are method of numerical simulation and of wind tunnel testing for validation. Based on the Navier-Stokes component transport eq

uation

the DOM thermal radiation model

and the RNG

model

a gas jet model of a two-stage launch vehicle with complex bottom components at high altitudes has been established. The calculation results indicate that in the operation of the auxiliary power system

the high heat flux regions of the second-stage launch vehicle are mainly concentrated in the short shell behind the fuel tank and the auxiliary power system support. The peak heat flux at the support during the operation of the submerged engine is 300%-400% higher than that of the other components. When the 60 N and 300 N engines operate in the same direction

the heat flux of the other bottom components reaches its peak

with an increase of 300%-600% compared to the other operating conditions. With increasing flight altitude and velocity

the heat flow of each bottom component shows a decreasing trend but with a small magnitude. The calculation results provide important engineering guidance for the thermal protection design of the bottom of the second-stage launch vehicle.

关键词

Keywords

references

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