地球静止轨道运行的OSR太阳吸收比变化分析

文佳佳; 谢荣建; 钟思源; 程锦铭; 陈凡胜

doi:10.13700/j.bh.1001-5965.2024.0334

地球静止轨道运行的OSR太阳吸收比变化分析

doi: 10.13700/j.bh.1001-5965.2024.0334

文佳佳¹,
谢荣建^1, ,,
钟思源¹,
程锦铭^{1, 2},
陈凡胜¹

1.
中国科学院上海技术物理研究所，上海 200083
2.
上海理工大学能源与动力工程学院，上海 200093

详细信息

通讯作者:
E-mail：xierongjian@mail.sitp.ac.cn

中图分类号: V443；TK124
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出版历程
- 收稿日期: 2024-05-17
- 录用日期: 2024-09-06
- 网络出版日期: 2024-11-07
- 整期出版日期: 2026-07-31

Analysis of solar absorptance degradation of OSR in geostationary orbit

1.
Shanghai Institute of Technical Physics Chinese Academy of Sciences，Shanghai 200083, China
2.
School of Energy and Power Engineering, University of Shanghai for Science and Technology，Shanghai 200093, China

More Information

Corresponding author: E-mail：xierongjian@mail.sitp.ac.cn

摘要

摘要:
光学太阳反射镜（OSR）也称二次表面镜，具有很低的吸收发射比，空间应用稳定高，粘贴于辐射散热板外表面时，能够起到良好的散热或制冷效果。OSR空间环境的影响及热控性能退化机理是热控长寿命设计的重要课题。通过对地球静止轨道工作的4颗卫星载荷相机在轨7年、4年、3年及2.5年温度数据分析，结合热仿真分析模型，得到OSR的太阳吸收比退化模型。结果显示，发射第1年OSR的太阳吸收比为0.125，在轨2年后OSR的太阳吸收比退化为0.134，7年后变化为0.175，退化曲线呈线性特征，每年退化率约为0.74%。同时，根据该退化模型预测10年后的太阳吸收比为0.195， OSR空间适应性及稳定性较高，计算结果为后续在轨温控及新热控系统设计提供指导。
- 地球静止轨道 /
- 空间环境效应 /
- 光学太阳反射镜 /
- 太阳吸收比 /
- 退化率
Abstract:
Objective Optical solar reflector (OSR) exhibit a very low absorptance-emittance ratio, ensuring stability and high performance in space applications. They efficiently aid in cooling or heat dissipation when attached to the exterior of radiative cooling panels. Understanding the impact of space environment on the OSR and the degradation mechanisms of their thermal control properties is crucial for designing long-lasting thermal control systems. Through analysis of temperature data from cameras onboard four satellites operating in geostationary orbit for 7 years, 4 years, 3 years, and 2.5 years, coupled with thermal simulation analysis models, the degradation model of the OSR solar absorptance solar absorptance is obtained. The deterioration model of the OSR solar absorptance solar absorptance is derived by analyzing temperature data from cameras on four satellites that have been in geostationary orbit for seven, four, three, and two and a half years. This data is combined with thermal simulation analysis models. The results reveal that the solar absorptance of the OSR were 0.125 in the first year of operation, degraded to 0.134 after 2 years in orbit, and changed to 0.175 after 7 years, with the degradation curve exhibiting linear characteristics and an annual degradation rate of approximately 0.74%. Additionally, based on this degradation model, the solar absorptance is predicted to be 0.195 after 10 years. OSR has strong spatial adaptability and stability and the results of this article offering guidance for subsequent in-orbit temperature control and new thermal control system designs.
- geostationary orbit /
- space environment effects /
- optical solar reflector /
- solar absorptance /
- degradation rate

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图 1 散热板模型及其温度测点

Figure 1. Model and temperature measurement points

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图 2 不同节气下OSR吸收的外热流

Figure 2. External heat flux absorbed by OSR under different solar terms

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图 3 OSR的太阳吸收比随在轨时间的变化

Figure 3. OSR solar absorption ratio as a function of time in orbit

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图 4 Sensor01～Sensor04相机上散热面在冬至最高温度随在轨时间的变化及预测

Figure 4. Maximum temperature and future prediction of heat sink temperature with on-orbit time

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表 1 内部热源功耗

Table 1. Internal heat sources power consumption meter

部件	发热量/W	部件数量
电路箱1	9.3	1
电路箱2	60.0	1
制冷机	160.0	2

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表 2 Sensor01相机冬至散热板温度变化

Table 2. Temperature change of Sensor01 radiant heat sink during Winter Solstice

日期	T₁/℃	T₂/℃	T₃/℃	T₄/℃	T₅/℃
2017-12-22	−46.6～−38.5	−45.6～−37.5	−45.8～−36.7	−45.4～−37.6	−25.9～0.4
2018-12-22	−46.1～−36.1	−45.1～−35.5	−44.8～−35.2	−44.5～−35.6	−25.3～2.7
2019-12-22	−44.6～34.1	−44.1～33.5	−43.7～−33.2	−43.5～−34.1	−24.8～5.2
2020-12-22	−45.1～−32.9	−44.1～−31.4	−42.7～−31.7	−43～−32.5	−24.7～6.9
2021-12-22	−45.5～−30.9	−45～−29.1	−42.2～−31.1	−41.5～−31.5	−24.2～8.6
2022-12-22	−46.1～−27.9	−45～−27.3	−42.7～−27.6	−43.5～−28.4	−24.2～12.3

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表 3 Sensor02相机冬至散热板温度变化

Table 3. Temperature change of Sensor02 radiant heat sink during Winter Solstice

日期	T₁/℃	T₂/℃	T₃/℃	T₄/℃	T₅/℃
2020-12-22	−46.88～−37.3	−46.82～−38.1	−46.26～−34.5	−46.9～−38.6	−24.3～0.1
2021-12-22	−45.0～−35.35	−45.4～−35.65	−45.3～−35.5	−45.9～−36.7	−22.7～2.43
2022-12-22	−42.6～−33.4	−43.4～−33.7	−43.8～−33.5	−44.6～−34.7	−22.3～4.9

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表 4 Sensor03相机冬至散热板温度变化

Table 4. Temperature change of Sensor03 radiant heat sink during Winter Solstice

日期	T₁/℃	T₂/℃	T₃/℃	T₄/℃	T₅/℃
2021-12-22	−43.9～−37.0	−44.3～−37.1	−47.4～−38.0	−46.8～−38.0	−28.7～−0.4
2022-12-22	−43.8～−34.9	−44.1～−35.0	−47.3～−37.0	−46.5～−36.2	−28.5～1.3

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表 5 Sensor04相机冬至散热板温度变化

Table 5. Temperature change of Sensor04 radiant heat sink during Winter Solstice

日期	T₁/℃	T₂/℃	T₃/℃	T₄/℃	T₅/℃
2022-12-22	−42.6～−34.4	−43.9～−35.1	−43.9～−36.2	−44.1～−35.9	−20.9～−3.5
2023-12-22	−42.5～−32.4	−43.7～−33.2	−43.7～−35.1	−44.0～−34.6	−20.7～−2.8

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表 6 材料物理属性

Table 6. Physical properties of material

材料	部件	热导率/ (W·(m·K)⁻¹)	比热容/ (J·(kg·K)⁻¹)	密度/ (kg·m⁻³)
铝合金	散热板蒙皮	167.0	960	2700
铝蜂窝	散热板芯	5.0	900	100
玻璃钢G10	隔热垫	0.2	700	2500

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表 7 涂层表面辐射特性

Table 7. Surface radiation characteristics of coating surface

材料	部件	α_S（地面测试）	ε_h
聚酰亚胺二次表面镜	多层外部	0.35	0.67
OSR	散热板外立面	0.10	0.79
白漆	遮光罩外表面	0.27	0.92

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表 8 仿真结果与热平衡试验及入轨一年飞行温度数据对比

Table 8. Simulation results of components compared with thermal equilibrium experiment and one-year flight temperature data in orbit

部件名称	仿真温度/℃	热平衡实验温度/℃		在轨一年温度/℃	温度判定是否正常
部件名称	仿真温度/℃	转移轨道	地球静止轨道	在轨一年温度/℃	温度判定是否正常
电路箱1	−10.4～−0.6	−16.1	−16.1～0.1	−12.3～−1	正常
电路箱2	−0.2～11.7	−2.3	10.3～10.3	3.8～11	正常
制冷机压缩机	−34.4～−29.8	−34.6	−30.5～−30.7	−34.9～−28.2	正常
制冷机脉管	−35.5～−18.4	−28.9	−43～−19.7	−43.2～−19.9	正常

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