Abstract: The modeling of priming process of Liquid Propellant Rocket Engines(LPRE)was studied.By dividing the feed pipes into uniform finite elements,applying the basic conservation laws to the elements filled with propellant or purge gas,and employing the equivalent flow capacitance equation to deal with the two phase element,the finite element state variable models for the priming process of normal temperature propellant feed pipes system were developed.The models are oriented to the control and versatile simulation of LPRE system transient.The simulated results of the priming process of a pipe were given.

Key words: Liquid propellant rocket engines;Propellant transfer;Pipeflow;Finite elements method;State space methed;Simulation mo?

摘要： 研究了常温推进剂液体火箭发动机充填过程的建模问题。对推进剂充填管道系统进行有限元分割 ,应用基本守恒定律于充满推进剂的单元和充满气体的单元 ,两相单元则采用等效流容方程 ,建立了常温推进剂管道系统充填过程的有限元状态变量模型。模型面向液体推进系统动态过程控制与通用仿真。利用该模型 ,对一管道充填过程进行了仿真计算 ,给出了有关计算结果。

关键词: 液体推进剂火箭发动机;推进剂输送;管流;有限元法;状态空间法;仿真