液氧加注过程热力性能分析  

Thermal performance analysis of liquid oxygen filling process

作　　者：高婉丽[1] 罗天培[1] 刘瑞敏[1] 孙德[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《火箭推进》2017年第3期22-27,78,共7页Journal of Rocket Propulsion

摘　　要：为满足某型号运载火箭动力系统试验液氧加注温度要求,需对加注过程进行热力性能分析。通过对常规氧加注过程因漏热和流阻损失引起的温升、液氧泵效率损失引起的温升进行理论计算,得出常规氧加注过程液氧温度变化规律。此外,通过对过冷氧温度掺混特性进行理论计算和数值仿真,得出过冷氧加注的热力性能。上述分析结果与实测数据进行了比对,结果表明,理论分析结果与实测结果吻合性好,液氧加注过程热力特性分析方法正确可行。In order to meet the requirement of liquid oxygen filling temperature in the test of a launch vehicle power system, the thermal performance in the filling process is analyzed. The temperature rise caused by heat leakage and flow resistance loss in normal liquid oxygen filling process, and the temperature rise caused by efficiency loss of liquid oxygen pump are calculated theoretically to get the temperature variation regularity in normal liquid oxygen filling process. The thermal performance of super cooling liquid oxygen filling process was obtained by theoretical calculation and numerical simulation of super cooling temperature mixing characteristics. The above analysis result and the detected result are contrasted. The resuRs are coincided with experimental data. The results show that the thermal characteristic analysis method for liquid oxygen filling process is correct and feasible.

关 键 词：液氧加注系统 温度调节 数值模拟 

分 类 号：V433-34[航空宇航科学与技术—航空宇航推进理论与工程]