涂层参数对卫星动态辐射特性影响分析

Effect of Parameters of Thermal Control Coating on Dynamic Radiation Characteristic of Satellite

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,建立了卫星多光谱有效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波段的瞬态有效辐射亮度。分析了涂层参数(太阳短波吸收率α、红外发射率ε)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比值成正比,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。

By considering the physical condition of the multilayer insulation（MLI） of the satellite, the temperature field of the thermal control coating was established, and the model was computed with the numerical heat transfer and the finite volume method. By taking into account of the external heat flux in the space orbit and the self-radiation of the thermal control coating, the effective radiance luminance model was also developed. The effective radiance luminance of the thermal control coating on 0.38-0.76 μm, 3-5 μm and 8-14μ m waveband were calculated. The influence of the parameters of thermal control coating （shortwave absorptivity α emissivity ε） on the surface temperature and radiance luminance was analyzed. The analytical results show that α ε is in direct proportion to the temperature of the coating, the radiance energy is concentrated on the visible and far-infrared spectrum band, and the radiance energy of the visible and farinfrared spectrum band can not be decreased at one time.