单组元发动机热回浸现象的理论分析

推进技术 ›› 1997, Vol. 18 ›› Issue (3): 40-44.

单组元发动机热回浸现象的理论分析

孙冰,蔡国飙,陈全,边炳秀

北京航空航天大学宇航学院!北京;100083;北京航空航天大学宇航学院!北京;100083;北京控制工程研究所!北京;100080;北京控制工程研究所!北京;100080

发布日期:2021-08-15

A THEORETICAL ANALYSES ON THERMO-SOAKBACK OF MONOPROPELLANT THRUSTER

School of Astronautics, Beijing Univ. of Aeronautics & Astronautics, Beijing, 100083;School of Astronautics, Beijing Univ. of Aeronautics & Astronautics, Beijing, 100083;Beijing Iust. of Control Engineering, Beijing, 100080;Beijing Iust. of Control Engineering, Beijing, 100080

Published:2021-08-15

摘要/Abstract

摘要： 用有限元法数值分析了通讯卫星上用于姿态和轨道控制的单组元发动机的热回浸现象。计算表明,燃烧室工作后的热量主要是通过支撑圆杆的热回浸和辐射而散失的。所得模拟结果还说明,工程设计中采用毛细管输送燃料,确实能有效地阻止发动机工作后燃烧室中的热量通过输料管传到电磁阀,可充分保证电磁间的安全。

关键词: 姿控火箭发动机;热控制;温度计算;传热;有限元法

Abstract: The thermo-sockback of the attitude and orbit control thrusters on satellite issimulated by finite element methods. The computation showed the left heat after combustor workedalmost lost through supporting sticks by thermo-soakback and radiation. The simulating results alsoshowed that the capillary tube used for transferring liquid fuel can effectively prevent the heat fromtransferrinng to the solenoid valve.

Key words: Attitude control rocket engine;Thermal conntrol;Temperature calculation;Heat transfer;Fimite element method

孙冰,蔡国飙,陈全,边炳秀. 单组元发动机热回浸现象的理论分析[J]. 推进技术, 1997, 18(3): 40-44.