氧化亚氮基氧燃一体化推进剂及推进系统研究进展  

Research progress of nitrous-oxide-based oxidizer-fuel integrated propellant and propulsion system

作　　者：韩伟[1] 王永忠 单世群[1] 杜宗罡[1] 朱成财[1] 于忻立 HAN Wei;WANG Yongzhong;SHAN Shiqun;DU Zonggang;ZHU Chengcai;YU Xinli(Xi'an Aerospace Test Technology Research Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力试验技术研究所,陕西西安710100

出　　处：《火箭推进》2020年第5期1-9,共9页Journal of Rocket Propulsion

基　　金：军委科技委创新特区项目(18-H863-03)。

摘　　要：氧化亚氮基氧燃一体化推进剂因具有无毒、高比冲、宽温幅等诸多优异性能,受到各航天科研工作者的广泛关注。美国、荷兰、英国、德国、中国在该推进剂及其推进系统研究方面开展了许多卓有成效的工作。综述了2016年以来国内外在氧化亚氮基氧燃一体化推进剂的配方体系、发动机设计、燃烧过程及防回火特性等方面的研究进展,结合我国实际现状,提出了下一步开展氧化亚氮基氧燃一体化推进剂及推进系统的建议。Nitrous-oxide-based oxidizer-fuel integrated propellant has been widely concerned by many aerospace scientists due to its excellent properties such as non-toxic,high specific impulse and wide temperature range.The United States,the Netherlands,the United Kingdom,Germany and China have carried out a lot of successful work on the propellant and its propulsion system.In this paper,the research progress in the formula system,engine design,combustion process and anti-tempering characteristics of nitrous-oxide-based oxidizer-fuel integrated propellant at home and abroad since 2016 is reviewed.Combined with the actual situation in China,some suggestions for the further development of nitrous-oxide-based oxidizer-fuel integrated propellant and propulsion system are put forward.

关 键 词：氧化亚氮 一体化推进剂 推进系统 燃烧特性 

分 类 号：V511[航空宇航科学与技术—航空宇航推进理论与工程]