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。
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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1997年第3期40-44,共5页
Journal of Propulsion Technology
关键词
姿控火箭发动机
热控制
有限元
热回浸
Attitude control rocket engine,Thermal conntrol, Temperature calculation, Heat transfer, Fimite element method
