高比冲双组元液体远地点火箭发动机研究  

Research on the High Specific Impulse Bipropellant Liquid Apogee Engine

作　　者：刘昌国 张中光 韩宏印 汪允武 孙得川 

机构地区：[1]上海航天动力机械研究所,上海200233

出　　处：《上海航天》2003年第4期30-33,共4页Aerospace Shanghai

摘　　要：综述了国内外研制的双组元液体远地点火箭发动机的性能、特点和发展趋势。在分析了液体远地点发动机提高比冲的各种技术途径后 ,提出可通过改进喷注器设计、减少边区液膜冷却流量、采用扰流环二次燃烧和使用新型耐更高温材料等措施 。The performance, characteristic and development trend of the liquid apogee engine both domestic and abroad were described in this paper. The measures, including improving injector design, decreasing cool flow of boundary liquid film, adopting secondary burning and new material that can stand higher temperature, to promote the performance of the liquid apogee engine were given after the analysis methods to high impulse specific of the engine.

关 键 词：远地点发动机 比冲 液体火箭发动机 发展趋势 二次燃烧技术 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程] V439.8