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[1]陈锐达,余鹏,丁卫华,等.安装热控组件对空间液体火箭发动机工作特性的影响[J].火箭推进,2024,50(03):1-10.[doi:10.3969/j.issn.1672-9374.2024.03.001]
　CHEN Ruida,YU Peng,DING Weihua,et al.Influence of installing thermal control components on working characteristics of space liquid rocket engine[J].Journal of Rocket Propulsion,2024,50(03):1-10.[doi:10.3969/j.issn.1672-9374.2024.03.001]
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安装热控组件对空间液体火箭发动机工作特性的影响

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 50 期数: 2024年03期 页码: 1-10 栏目: 目次 出版日期: 2024-06-25
Title:
Influence of installing thermal control components on working characteristics of space liquid rocket engine
文章编号:
1672-9374(2024)03-0001-10
作者:
陈锐达1; 2; 余鹏1; 2; 丁卫华1; 2; 刘昌国1; 2; 陈泓宇1; 2; 徐辉1; 2
1.上海空间推进研究所,上海 201112; 2.上海空间发动机工程技术研究中心, 上海 201112
Author(s):
CHEN Ruida1; 2;  YU Peng1; 2;  DING Weihua1; 2;  LIU Changguo1; 2;  CHEN Hongyu1; 2;  XU Hui1; 2
1.Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2.Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China
关键词:
空间液体火箭发动机;  热控组件;  多层隔热材料;  遮光板;  热辐射
Keywords:
space liquid rocket engine;  thermal control component;  multilayer insulation material;  light shielding plate;  thermal radiation
分类号:
V439.7
DOI:
10.3969/j.issn.1672-9374.2024.03.001
文献标志码:
A
摘要:
准确掌握安装不同热控组件后对空间液体火箭发动机工作性能和温度特性的影响对其在轨使用可靠性至关重要。对双组元150 N发动机开展高空模拟热试车,依次考察了安装头部法兰下表面热控组件、头部包覆多层隔热材料和遮光板对发动机稳态工作特性的影响。结果表明:安装热控组件后,发动机推力输出稳定; 头部法兰下表面安装热控组件可以有效隔离高温身部的热辐射,可降温125～160 ℃,减少30%～44%的法兰温度增长; 后续安装的头部包覆多层隔热材料和遮光板对法兰温度分布基本没有影响,头部包覆多层隔热材料会导致头身焊缝温度升高约40 ℃; 遮光板不影响头身焊缝温度,但会增加头部法兰下表面受到的辐射热流。安装不同热控组件对发动机工作性能没有影响,发动机累计稳态工作4 163 s、脉冲工作25 000次后,多层隔热材料中心约20 mm区域发生烧蚀,此时热控组件仍能有效降低高温身部的热辐射影响,建议增大多层材料中心开孔直径至100 mm以上。
Abstract:
Accurately grasping the effects of installing different thermal control components on the working performance and temperature characteristics of space liquid rocket engine is crucial to its in-orbit reliability. High-altitude simulation hot fire tests of the 150 N bipropellant engine were carried out, and the influence of the thermal control component on the undersurface of the head flange, the head-wrapped multilayer insulation material and the light shielding plate on the engine steady-state working performance and temperature distribution were investigated in turn. The results show that the engine thrust output is stable after installing different thermal control components. The thermal control component installed on the undersurface of the head flange effectively isolates the heat radiation from the high-temperature body, which can cool down the temperature by 125-160 ℃, and reduce the flange temperature increasement by 30%-44%. The subsequent installation of the head-wrapped multilayer insulation material and the light shielding plate has little effect on the flange temperature distribution. The head-wrapped multilayer insulation material causes the temperature of the head and body weld seam to rise about 40 ℃. The light shielding plate has no effect on the head and body weld seam temperature, but increases the radiant heat flow to the undersurface of the head flange. Installing different thermal control components do not affect the engine working performance. After accumulating 4 163 s of steady state ignition and 25 000 times of pulse operation of the engine, the center of the multilayer insulation material is ablated in an area of about 20 mm, and the thermal control components are still effective in reducing the impact of heat radiation from the high-temperature body. It is recommended to increase the diameter of the multilayer insulation material center aperture to more than 100 mm.

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相似文献/References:

[1]陈锐达,王鹤茗,徐 辉,等.双组元150 N自燃推进剂发动机单阀打开脉冲特性[J].火箭推进,2023,49(06):10.
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备注/Memo

收稿日期:2024- 02- 22修回日期:2024- 03- 20
基金项目:“十四五”装备预研共用技术项目(50922010801)
作者简介:陈锐达(1995—),男,硕士,工程师,研究领域为空间液体火箭发动机技术。

更新日期/Last Update: 1900-01-01