摘要
针对某型氢氧膨胀循环发动机直接换甲烷技术可行性进行研究。在氢氧膨胀循环发动机系统构成的基础上,通过启动仿真计算分析液氧/甲烷膨胀循环发动机上的启动特性,确定试验方案,进行点火试验。依据试车数据,进行比较分析,对仿真模型进行修正,为后续液氧/甲烷膨胀循环发动机的研究奠定理论基础。
The feasibility study of the LOX/LH2 expander cycle engine employing LOX/CH4 propellant was performed in this paper.On the basis of the LOX/LH2 expander cycle engine system, the start-up characteristics of LOX/CH4 expander cycle engine were analyzed through the starting simulation. Ignition test was carried out after the determination of the test scheme. Then the simulation model was modified according to the test data. These results serve as the theoretical foundation for the further study of the LOX/CH4 expander cycle engine.
出处
《导弹与航天运载技术》
北大核心
2015年第2期18-22,共5页
Missiles and Space Vehicles
