基于射流掺混的甲烷推进剂热力学特性分析  

Analysis on Thermodynamic Characteristics of Methane Propellant Based on Jet Mixing

作　　者：苏健 王昊 黄辉 黄平瑞 罗泰茗 谢永奇[1] SU Jian;WANG Hao;HUANG Hui;HUANG Pingrui;LUO Taiming;XIE Yongqi(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;National Key Laboratory of Deep Space Exploration,Hefei 230000,China;Beijing Institute of Aerospace Testing Technology,Beijing 100074,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]北京宇航系统工程研究所,北京100076 [3]深空探测全国重点实验室,合肥230000 [4]北京航天试验技术研究所,北京100074

出　　处：《宇航总体技术》2025年第2期1-10,共10页Astronautical Systems Engineering Technology

基　　金：深空探测全国重点实验室开放课题(NKLDSE2023B003)。

摘　　要：空间环境中甲烷推进剂热力学参数的不均匀分布,是阻碍未来低温航天器发动机快速、可靠再起动的关键问题之一。射流掺混作为一种能在短时间内消除温度不均匀分布的推进剂管理技术,为上述问题提供了可行的解决方案。为研究微重力下射流掺混过程对甲烷推进剂热力学特性的影响规律,针对0~0.03 kg/s射流流量下甲烷推进剂的流动与相变传热过程开展仿真分析。计算结果表明:在轨贮存期间,过冷甲烷推进剂的热力学特性存在不同的变化趋势;甲烷的初始过冷度虽然能在短期内抑制贮箱压力上升,但无法起到长期蒸发量控制的作用。射流掺混能在短时间内抑制甲烷推进剂的增压、温升与蒸发,并改善温度分布不均的问题,有利于甲烷推进剂快速达到发动机再起动条件。The non-uniform distribution of methane propellant thermodynamic parameters in the space environment is one of the critical challenges impeding the rapid and reliable engine restart in prospective cryogenic spacecraft.The issue can be solved by applying a propellant management technology,called jet mixing,which is capable of homogenizing temperature distributions.To investigate the influence of jet mixing on the thermodynamic characteristics of methane propellant in microgravity,computational study were performed on the flow and phase change heat transfer processes of methane propellants with jet flow rates from 0 to 0.03 kg/s.The results demonstrate that during on-orbit storage,the thermodynamic characteristics of subcooled methane propellant exhibit distinct trends.Although the initial degree of subcooling in methane can suppress the tank pressure increase over a short duration,it fails to serve as an effective long-term control method for evaporation rates.It is found that jet mixing can effectively suppress the pressurization,temperature rise,and evaporation of methane propellant,while rectifying the issue of non-uniform temperature distribution.This method can shorten the time consumed to meet the engine restart requirement for methane propellant.

关 键 词：甲烷推进剂 射流掺混 热力学特性 仿真分析 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计]