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.
出处
《火箭推进》
CAS
2009年第4期14-20,43,共8页
Journal of Rocket Propulsion
作者简介
张小平（1970-），男，高级工程师，研究领域为液体火箭发动机系统设计。
