摘要
考虑卫星本体表面包覆绝热材料的实际物理状态,根据数值传热学和有限容积法建立了目标表面温度场的计算模型,对在轨飞行卫星的瞬态温度场进行数值模拟。考虑涂层表面自身辐射及空间轨道外热流等因素,建立了卫星多光谱辐射亮度的计算模型,计算了涂层表面在0.38～0.76μm、3～5μm和8～14μm波段的瞬态辐射亮度。分析了涂层参数(太阳短波吸收率、红外发射率)对瞬态温度和波段辐射亮度的影响。结果表明:卫星涂层温度同α/ε成正比,卫星的辐射能量主要集中在可见光和远红外波段,以及不能同时减小卫星在可见光和远红外波段的辐射能量。
Considering the physical condition of the multilayer insulation（MLI） of the satellite surface,the temperature field model of the thermal control coating was established based on the numerical heat transfer and finite volume methods,and the instantaneous temperature field of the satellite in the orbit was simulated.Taking into account the self-radiation of the thermal control coating and the external heat flux in the space orbit,the multispectral radiance luminance model of the satellite was also developed.The radiance luminance of the thermal control coating on 0.38-0.76 μm,3-5 μm and 8-14 μm waveband were calculated.The influence of the thermal control coating parameters（shortwave absorptivity α and emissivity ε） on the surface instantaneous temperature and wave band radiance luminance was analyzed.It is indicated that α/ε is proportionate to the temperature of the coating,and the radiance energy of the satellite concentrated on the visible and far-infrared spectrum band,which can not be decreased simultaneously.
出处
《红外与激光工程》
EI
CSCD
北大核心
2010年第4期593-596,638,共5页
Infrared and Laser Engineering
基金
国家863计划资助项目(2008AA8090311)
关键词
空间光学
热控涂层
温度场
多光谱辐射
Space optics
Thermal control coating
Temperature field
Multspectral radiance
