液氧深度过冷大流量加注关键技术研究  

Research on Key Technologies for Deep Subcooling LO_(2) with Large Flow Rate Filling

作　　者：李佳超 刘聪聪[1] 刘忠明[1] 刘海飞[1] 唐强[1] 孙怡鹏 LI Jiachao;LIU Congcong;LIU Zhongming;LIU Haifei;TANG Qiang;SUN Yipeng(Beijing Institute of Space Launch Technology,Beijing 100076,China)

机构地区：[1]北京航天发射技术研究所,北京100076

出　　处：《宇航总体技术》2024年第4期64-70,共7页Astronautical Systems Engineering Technology

摘　　要：为了提高火箭运载系数和工作稳定性,有必要对液氧(LO_(2))深度过冷大流量加注进行研究。重点分析了国内外液氧深度过冷大流量加注的工程应用方案及关键设计参数,总结给出了液氧深度过冷大流量加注技术难点,提出了泵抽真空过冷与高压氮气引射抽真空过冷两种液氧深度过冷大流量加注设计方案。通过对液氧深度过冷大流量加注关键技术研究,为我国深度过冷液氧在低温火箭上大规模应用与地面加注系统的能力提升提供了技术参考。In order to improve the rocket's launch cofficient and operational stability,the deep subcooling liquid oxygen(LO_2) with large flow rate filling should be researched.Our paper focused on analysing engineering application schemes and key design parameters of deep subcooling LO_(2) with large flow rate filling at home and overseas,the technical difficulties of deep subcooling LO_(2) with large flow rate filling are summarized,and two design schemes for deep subcooling LO_(2) with large flow rate filling are proposed,namely pump vacuum subcooling and high-pressure nitrogen injection vacuum subcooling.Through researched key technologies for deep subcooling LO_(2) with large flow rate filling,this article provides a technical reference for large-scale application of deep subcooling LO_(2) with cryogenic rockets and the ability promotion of ground filling system in China.

关 键 词：液氧 深度过冷 大流量加注 真空 

分 类 号：V511[航空宇航科学与技术—航空宇航推进理论与工程]