火箭推进2024，Vol.50Issue(3)：1-10,10.DOI:10.3969/j.issn.1672-9374.2024.03.001
安装热控组件对空间液体火箭发动机工作特性的影响
Influence of installing thermal control components on working characteristics of space liquid rocket engine
摘要
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.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Key words
space liquid rocket engine/thermal control component/multilayer insulation material/light shielding plate/thermal radiation分类
航空航天引用本文复制引用
陈锐达,余鹏,丁卫华,刘昌国,陈泓宇,徐辉..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(3):1-10,10.基金项目
"十四五"装备预研共用技术项目(50922010801) （50922010801）
