固液混合火箭发动机高效喷注燃烧技术发展与应用  

Research and application of high-performance injection and combustion in hybrid rocket motor

作　　者：李承恩 王宗伟 刘筑 苏立超 杨延婷 LI Chengen;WANG Zongwei;LIU Zhu;SU Lichao;YANG Yanting(Science and Technology on Space Physics Laboratory,Beijing 100076,China)

机构地区：[1]空间物理重点实验室,北京100076

出　　处：《固体火箭技术》2022年第6期891-901,共11页Journal of Solid Rocket Technology

摘　　要：固液火箭发动机通常采用液体氧化剂和固体燃料作为推进剂组合,是一种具有良好应用前景的火箭动力系统。氧化剂喷注燃烧特性是固液火箭发动机性能和可靠性的决定性影响因素之一。按照喷注介质的物理聚集态,固液火箭发动机常用气体喷注器和液体喷注器两类。气体喷注器的典型喷注介质为气氧(GOX)、催化过氧化氢(H_(2)O_(2)),液体喷注器的典型喷注介质为液氧(LOX)、高浓度H_(2)O_(2)、氧化亚氮(N_(2)O)。对国内外研究机构开展各类喷注器的高效喷注燃烧技术的代表性研究进行了分类介绍,对其典型探索性工程实践中使用的氧化剂喷注方案进行了梳理总结,分析归纳了固液火箭发动机高效喷注燃烧的主要关键技术,即氧化剂喷注稳燃技术、喷注流场高效药柱传热技术、喷注流场高效推进剂掺混技术、喷注结构长时间热防护技术。Hybrid rocket motor,which usually utilizes liquid oxidizer and solid fuel as propellants,is a rocket propulsion system with promising application prospects.Oxidizer injection and combustion characteristics are key factors affecting performance and reliability of hybrid rocket motor.According to the physical aggregation state of injection mediums,the injectors in hybrid rocket motor are classified as gaseous injector and liquid injector.Typical mediums for gaseous injector are gaseous oxygen(GOX)and catalytic hydrogen peroxide(H_(2)O_(2)).Typical mediums for liquid injector are liquid oxygen(LOX),high-concentration H_(2)O_(2)and nitrous oxide(N_(2)O).Representative researches on high-efficiency injection and combustion technology of hybrid rocket motor were classified and introduced.Schemes of oxidizer injection in typical exploratory engineering applications of hybrid rocket motor were summarized.The key technologies of high-efficiency injection and combustion were analyzed,that is injection method for steady combustion of oxidizer,injection flow field efficient thermal transfer technology for grain,efficient mixing technology of propellants,and long-term thermal protection technology for injection structure.

关 键 词：固液火箭发动机 喷注器 氧化剂 燃烧性能 关键技术 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]