摘要
制定液氧煤油发动机的起动点火程序时,必须考虑液氧充填燃气发生器氧头腔的特性。为此,建立了一种用于模拟低温推进剂充填和换热过程的动态模型。模型考虑了液相与结构壁面、气相与结构壁面以及气—液两相之间的非稳定换热过程以及气—液两相流动过程。同时,通过分相假设描述了气相对充填过程的影响。仿真结果的准确性已经得到综合热调试验数据的验证。
Characteristic of oxygen filling the gas generator must be taken into account when the starting scheme of a LOX/Kerosene LRE is decided. So, a dynamic model has been built to simulate liquid oxygen＇s filling course. Heat transfer between gas-liquid phase and the structural wall, as well as two-phase flow, are considered in the model. At the same time, influence of gas phase on filling process is described by the hypothesis of separated phase flow. Further application to engineering has been verified by engineering method the veracity of the simulation result.
出处
《火箭推进》
CAS
2006年第2期11-15,共5页
Journal of Rocket Propulsion
关键词
液体火箭发动机
低温推进剂
传热
充填过程
仿真
liquid rocket engine （LRE）
cryogenic propellant
heat transfer
filling process
simulation
