摘要
根据航天器轨道动力学和热辐射理论,建立了运行于近地倾斜轨道的圆柱形航天器外热流数学模型;用数值方法对外热流和等效热沉温度进行求解,计算出瞬态工况及周期平均工况下的航天器表面辐射热流及辐射散热器和防辐射涂层表面等效热沉温度的波动。结果表明,航天器受到的辐射热流除了随航天器绕地球公转变化外,还随其轨道面的旋转在更长的周期上产生更大的变化;对柱面上的不同位置受到的辐射作了比较,发现辐射散热器布置在顶部时其等效热沉温度最低。
Space thermal radiant environment is one of the most important factors for design and control of spacecraft. The mathematical model was built with theories of dynamics of orbits and thermal radiation for space radiation of the spacecraft which runs on incline near-earth elliptical orbit. The outer thermal radiant heat flux and equivalent heat sink temperature were solved with numerical method, and the wave of thermal radiation during long period was given. The results showed that the thermal radiation has larger fluctuation with the rotation of the orbit plate than that during the revolution period; the heat flux that absorbed by craft surface is least at the top area and is largest at the bottom; the equivalent sink temperature is related to the character of the surface.
出处
《太阳能学报》
EI
CAS
CSCD
北大核心
2004年第5期717-721,共5页
Acta Energiae Solaris Sinica
关键词
热辐射
航天器
倾斜轨道
等效热沉
Dynamics
Earth (planet)
Heat flux
Heat radiation
Heat sinks
Mathematical models
Numerical methods
Orbits
Temperature
