摘要
给出在不同高度和β角的环月圆轨道下,探测器的太阳和月球红外热流密度,并分析了其热流随轨道变化的规律。在嫦娥三号探测器热分析中采用月面月壤热数学模型,计算了着陆月面探测器表面在全月昼不同太阳高度角下的太阳热流和月表红外热流密度。通过对各个表面散热能力的分析总结,得出了背月面和背阳面的两个有效散热面,可为环月和月表探测器热设计提供参考。
The solar heating and lunar heating of a cubic spacecraft are calculated in the different orbital altitude and β angle on the circumlunar orbit.The rule of heating change is gained.A lunar thermal mathematic model is firstly presented and applied for Chang＇e-3 exploration spacecraft.The solar heating and lunar infrared heating of the cubic spacecraft surface on the moon surface were calculated at the different elevation of the sun.On the basis of these solar heating and lunar heating,the rule of the radiating capability for spacecraft is summarized,and two effective radiating surfaces that point the back of the moon or the sun are gained.These have important reference value for spacecraft on the circumlunar orbit and moon surface.
出处
《航天器工程》
北大核心
2015年第5期73-78,共6页
Spacecraft Engineering
基金
国家重大科技专项工程
关键词
月球探测器
外热流
环月轨道
月面
散热面
散热能力
lunar spacecraft
external heating
circumlunar orbit
moon surface
radiating surface
radiating capability
