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摘要:
构建空间目标辐射特性对于发展空间态势感知技术具有重要意义。本文针对空间目标红外辐射特性，基于有限元方法，采用非结构四面体网格研制了仿真程序，通过矢量坐标变换，计算得到了目标各表面受到的轨道外热流，并结合表面材料和双向反射分布函数（BRDF）对目标各表面温度和红外辐射特性进行了仿真，并与文献结果进行了对比。进而考虑大气衰减和背景辐射的影响，对地基探测条件下升轨和降轨弧段的目标光谱辐射强度进行了分析。结果显示：对于三轴稳定太阳同步轨道沿飞行方向固定式帆板卫星，各表面在阳照区和地影区内温度变化范围较小；使用8~14 μm长波波段对目标进行观测的效果比3~5 μm中波波段好；辐射强度最大值在770 W/sr左右；地基红外光谱探测受大气影响较大，需要对探测波段进行优选。
Abstract:Constructing the radiation characteristics of space targets is of great significance for the development of space situational awareness technology. In this study, we aim to investigate the infrared radiation characteristics of space targets by developing a simulation program based on the finite element method and unstructured tetrahedral mesh. Through vector coordinate transformation, we calculate the orbit external heat flux received by each surface of the target. By combining the surface material properties and Bidirectional Reflection Distribution Function (BRDF), the temperature and infrared radiation characteristics of each target surface were simulated. Furthermore, we analyze the spectral radiation intensity of the target in the ascending and descending orbital arcs under ground-based detection conditions, taking into account the effects of atmospheric attenuation and background radiation. The results show that, for a three-axis stabilized synchronous orbit satellite with solar panels fixed in the flight direction, the temperature variation range of each surface in the sunlight area and the shadow area is small. The detection effect of the long-wave band of 8~14 μm is better than that of the medium-wave band of 3~5 μm, and the maximum radiation intensity is about 770 W/sr. Ground-based infrared spectrum detection is more affected by the atmosphere, and the detection band must be optimally selected.
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图 1 目标表面与探测器入瞳的位置关系示意图
Figure 1. Schematic diagram of the position relationship between the target surface and the probe's entrance pupil
图 4 不考虑遮挡效应时本文计算得到的轨道外热流与商用软件的结果对比
Figure 4. Comparison of calculation results of orbit external heat flow by proposed method and commercial software without taking into account the occulusion effect
图 5 考虑遮挡效应时轨道外热流计算结果
Figure 5. Calculation results of orbit external heat flow with taking into account the occlusion effect
图 9 升轨观测红外光谱辐射强度
Figure 9. Infrared radiation spectral intensity of ascending detection
图 10 降轨观测红外光谱辐射强度
Figure 10. Infrared radiation spectral intensity of descending detection
图 11 考虑大气影响的升轨观测红外光谱辐射强度
Figure 11. Infrared radiation spectral intensity of ascending detection with the atmosphere impact
图 12 考虑大气影响的降轨观测红外光谱辐射强度
Figure 12. Infrared radiation spectral intensity of descending detection with the atmosphere impact
表 1 轨道参数
Table 1. Orbit parameters
时间 (UTC) 半长轴 / km 偏心率 倾角/（°） 升交点赤经 /（°） 近地点幅角 /（°） 真近点角 /（°） 2000-03-21 04:00:00 7225.578 0.00345 98.757 124.893 102.064 156.019 
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表 2 表面材料热参数
Table 2. Thermal parameters of surface material
表面 材料 吸收率 发射率 本体 聚酰亚胺 0.23 0.62 太阳帆板 电池片 0.82 0.81 基板 0.88 0.86
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表 3 不同位置点处的方位角、俯仰角和距离
Table 3. Azimuth, elevation, and range at different positions
序号 方位角 / （°） 俯仰角 / （°） 距离 / km 升轨弧段 1 165.9 20.0 1886.5 2 266.8 87.4 867.0 3 344.9 20.0 1888.2 降轨弧段 4 40.7 20.0 1870.5 5 97.0 38.1 1270.2 6 153.9 20.0 1860.6
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