Deep Subcooling Filling of LO<sub>2</sub>/LCH<sub>4</sub> Cryogenic Propellants

MA Yuan; GAO Yan; GAO Qiang; SUN Qiang; XIE Fushou; LI Yanzhong

doi:10.7652/xjtuxb202209014

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Deep Subcooling Filling of LO₂/LCH₄ Cryogenic Propellants

更新时间：2025-07-09

- Deep Subcooling Filling of LO₂/LCH₄ Cryogenic Propellants
- Vol. 56, Issue 9, Pages: 134-141(2022)
- 作者机构：
  
  1. 西安交通大学制冷与低温工程系,西安,710049
  2. 西安航天动力试验技术研究所,西安,710100
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202209014
  CLC： TK421.4
- Online First：10 September 2022，
  
  Published：2022
- 稿件说明：
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MA Yuan, GAO Yan, GAO Qiang, et al. Deep Subcooling Filling of LO₂/LCH₄ Cryogenic Propellants[J]. 2022, 56(9): 134-141. DOI: 10.7652/xjtuxb202209014.
DOI：

MA Yuan, GAO Yan, GAO Qiang, et al. Deep Subcooling Filling of LO₂/LCH₄ Cryogenic Propellants[J]. 2022, 56(9): 134-141. DOI: 10.7652/xjtuxb202209014. DOI：

摘要

为了提高低温推进剂深度过冷技术成熟度

以充分利用其在降低过冷装置系统质量、延长贮存时间等方面的工程应用优势

针对液氧/液甲烷低温推进剂组合

以70 K/97 K为目标开展深度过冷方案对比与流程设计

并通过搭建中等规模液氧和液甲烷快速深度过冷加注实验系统进行可行性测试验证。结果表明:针对中大规模过冷装置系统

液氧系统采用常压液氮浴+负压液氮浴两级换热过冷方案(换热器均采用铝制板翅式换热芯)

液甲烷系统采用常压列管式液氮浴式换热器过冷加注方案; 为满足快速过冷加注需求

液氧/液甲烷系统均采用边过冷边加注的系统流程; 在加注流量为1.0 L·s

-1

左右的稳定测试阶段

液氧实验系统中入口温度约108 K的液氧经一级、二级换热器能够分别被冷却至约88 K及70 K以下

液甲烷实验系统也实现了97 K液甲烷的深度过冷与快速加注

成功验证了设计方案的可行性。研究工作能够为中国开展过冷低温推进剂的研究与工程应用提供理论与技术支持。

Abstract

To improve the readiness level of deep subcooling technology for cryogenic propellants

and then sufficiently utilize the advantages of subcooled cryogenic propellants in industry applications

such as reduced system weight and extended storage time

scheme comparison and system design of deep subcooling are carried out at 70 K/97 K for combination of LO

/LCH

cryogenic propellants

and a medium-scale experimental system for their rapid deep subcooling is established to test and verify the feasibility. The results show that for medium and large scale sy

stems

the heat exchange method with an atmospheric and a subatmospheric liquid nitrogen(LN

)bath heat exchangers(cores of aluminum fin-plate type)is adopted for LO

system while the subcooling filling scheme with an atmospheric LN

bath tubular heat exchanger is adopted for LCH

system. To meet the requirements for rapid subcooling and filling

the simultaneous subcooling scheme is adopted for both LO

and LCH

systems. At the stable testing stage with a filling flow rate of around 1.0 L·s

-1

in the LO

test system is cooled down from about 108 K at the inlet to around 88 K and below 70 K

respectively after flowing through the two heat exchangers

while for the LCH

test system

deep subcooling and rapid filling of 97 K LCH

is also achieved. This successfully verifies the feasibility of the designed deep subcooling and filling scheme. This study could provide theoretical and technical support for the future research and engineering applications of subcooling cryogenic propellants in China.

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Related Author

XIA Siqi

XIE Fushou

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⁰

Deep Subcooling Filling of LO2/LCH4 Cryogenic Propellants

DOI：10.7652/xjtuxb202209014

摘要

Abstract

关键词

Keywords

references

Deep Subcooling Filling of LO₂/LCH₄ Cryogenic Propellants