火箭推进2026，Vol.52Issue(4)：14-19,6.DOI:10.3969/j.issn.1672-9374.2026.04.002
长期在轨低温推进剂贮箱隔热特性传热分析
Analysis of thermal insulation characteristics for long-duration in-orbit cryogenic propellant tank
摘要
Abstract
According to the thermal insulation requirements for liquid oxygen tank in rocket engine under both in-orbit and ground conditions,a composite multilayer insulation scheme was proposed in this article.A layer-by-layer heat transfer analysis model was utilized to conduct detailed analysis of the impact trends of insulation layer thickness and density on heat leakage.With the objective of minimizing heat flux density,the layer density distribution scheme was optimized,resulting in an insulation structure with superior thermal insulation performance.The heat transfer mechanisms of the insulation were systematically investigated.The results show that the heat leakage of the composite multilayer insulation decreases with increasing insulation layer thickness and layer density,while the solid thermal conduction and radiation dominate the heat transfer characteristics of the insulation layer.关键词
液氧贮箱/复合多层隔热方案/逐层传热分析模型/热流密度Key words
liquid oxygen tank/multi-layer insulation/layer-by-layer heat transfer analysis model/heat flux分类
航空航天引用本文复制引用
付秀文,郭维..长期在轨低温推进剂贮箱隔热特性传热分析[J].火箭推进,2026,52(4):14-19,6.基金项目
国家自然科学基金青年基金(12502398) （12502398）
