液氧/甲烷发动机动力循环方式研究  

Study on the LOX/methane rocket engine power cycles

作　　者：张小平[1] 李春红[1] 马冬英[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2009年第4期14-20,43,共8页Journal of Rocket Propulsion

摘　　要：综述了液氧/甲烷发动机的研究进展,分析了液氧/甲烷发动机的特性和应用前景,对比了大推力液氧/甲烷发动机的动力循环方式,提出发动机动力循环方式选择应综合用途、性能、研制难度及使用成本等多方面因素,一次性使用的发动机应采用高性能的高压补燃循环,其中部分甲烷冷却推力室的富燃补燃循环较佳;重复使用的发动机应根据工作次数和工作寿命,重点考虑系统压力低的燃气发生器循环和低压的补燃循环。Development of LOX/methane rocket engine was described in this paper. The characteristic and potential use were analyzed. Different power cycles of high thrust engine was compared. The application, the performance, the difficulties in developing and the cost all should be considered for the choice of power cycles. High pressure staged combustion cycle with high performance should be used for expandable engines, and the fuel-rich staged combustion cycle with partial methane cooling chamber is the best. Gas generation cycle and low pressure staged combustion cycle should be considered to use for reusable engines according to operating times and operating life.

关 键 词：液体火箭发动机 液氧/甲烷 无毒推进剂 重复使用 循环方式 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]