星载低温光学系统热控设计与飞行验证

刘庆志; 易桦; 江海; 刘银年

doi:10.37188/CO.2022-0200

星载低温光学系统热控设计与飞行验证

doi: 10.37188/CO.2022-0200

刘庆志^1, ,,
易桦¹,
江海¹,
刘银年²

1.
北京空间飞行器总体设计部空间热控技术北京市重点实验室, 北京 100094
2.
中国科学院上海技术物理研究所, 上海 200083

基金项目: 实践九号卫星国家重大科技专项工程

详细信息

作者简介:
刘庆志（1975—），男，黑龙江牡丹江人，博士，高级工程师，1997年、2002年于北京航空航天大学分别获得学士、硕士学位，2005年于中国空间技术研究院获得博士学位，主要从事航天器热设计、热分析及热试验工作。E-mail：looup@sina.com

中图分类号: TK124
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- 被引次数: 0
出版历程
- 收稿日期: 2022-09-24
- 修回日期: 2022-10-11
- 网络出版日期: 2023-02-06

Thermal control design and flight test of a satellite-borne cryogenic optical system

1.
Beijing Institute of Spacecraft System Engineering, Beijing Key Laboratory of Space Thermal Control Technology, Beijing 100094, China
2.
Shanghai Institute of Technical Physics, Chinese Academy of Sciences, Shanghai 200083, China

Funds: Supported by National Major Science and Technology Project of SJ-9 Satellite

More Information

Corresponding author: looup@sina.com

摘要

摘要:
星载长波红外相机工作时需要将整个光学系统的温度降低至−20 °C以下，以减少背景红外辐射的影响。在弱导热连接结构设计的基础上，研制了Ω型柔性遮阳装置，通过直接辐冷方式实现了光学系统的低温设计；研制了鸟笼式三维导热带，实现了主镜筒的均温设计。作为国内首个在空间领域应用的低温光学系统随实践九号B星进行了在轨飞行试验，结果表明，整个光学系统温度可长期保持在−35 °C～−20 °C，主镜筒圆周温度差小于4 °C。该热控设计方法简单有效，可以为类似星载红外光学系统的热设计提供参考。
- 低温光学系统 /
- 弱导热 /
- 柔性遮阳装置 /
- 鸟笼式导热带 /
- 飞行验证
Abstract:
In order to reduce influence of background infrared radiation, the temperature of the whole optical system should be below −20 °C for satellite-borne long-wave infrared imagers working in orbit. On the base of the weak heat conduction structure, a Ω type flexible sunshield made of MLI was developed and a cryogenic optical system was achieved through direct radiation cooling. Cage-like three-dimensional heat conduction straps made of copper were developed and an isothermal design for the body tube was realized. The cryogenic optical system applied to space remote sensing was used for the first time in China when it was tested in orbit with SJ-9B satellite. The results showed the temperature of the whole optical system could be maintained at −35 °C~−20 °C all the time, and the temperature difference in the body tube was no more than 4 °C. All flight test data met the temperature requirement of the long-wave infrared imager. This thermal control method is simple and effective, which can provide a reference for the thermal design of similar satellite-borne infrared optical systems.
- cryogenic optical system /
- weak conduction /
- flexible sunshield /
- cage-like thermal conduction strap /
- flight test

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图 1 SJ-9B卫星构型图

Figure 1. Configuration of the SJ-9B satellite

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图 2 长波红外相机构型图

Figure 2. Configuration of the long-wave infrared imager

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图 3 相机内部热量传递图

Figure 3. Schematic diagram of heat transfer of the imager

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图 4 长波红外相机热控状态示意图

Figure 4. Schematic diagram of thermal control of the imager

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图 5 阳光遮挡情况示意图

Figure 5. Schematic diagram of the sunshield

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图 6 隔热垫片安装位置

Figure 6. Position of the insulation pads

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图 7 隔热垫片安装方式

Figure 7. Installation mode of the insulation pads

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图 8 鸟笼式导热带安装示意图

Figure 8. Schematic diagram of the cage-like straps

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图 9 鸟笼式导热带结构示意图

Figure 9. Configuration of the cage-like straps

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图 10 光学系统主要温度测点布置图

Figure 10. Temperature sensor layout of the optical system

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图 11 实践九号B星照片

Figure 11. Photograph of the SJ-9B satellite

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图 12 主镜筒和主反射镜温度曲线

Figure 12. Temperature curve of the body tube and the primary reflector

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图 13 后光学透镜温度曲线

Figure 13. Temperature curve of the rear lens

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图 14 次反射镜温度曲线

Figure 14. Temperature curve of the secondary reflector

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图 15 相机支架温度曲线

Figure 15. Temperature curve of the imager’s bracket

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表 1 长波红外相机各部分材料以及控温需求

Table 1. Materials and temperature requirements of the imager’s components

零件名称	温度水平( °C)	温度均匀性( °C)	材料
次反射镜	−35～−20	/	石英玻璃
主镜筒	−35～−20	圆周温差≤5	殷钢
主反射镜	−35～−20	/	石英玻璃
后光学透镜	−35～−20	/	Ge晶体
相机支架	−20～0	/	铝合金
制冷机	−20～20	/	/

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表 2 地面热平衡试验光学系统温度测试结果

Table 2. Temperatures in different positions (shown in Fig.10) of the optical system in the thermal balance test

温度测点位置	温度测点代号	温度水平( °C)	温度均匀性( °C)
主镜筒	T1	−31.9～−28.5	圆周温差：4.3
	T2	−31.9～−28.5
	T3	−27.6～−26.6
主反射镜	T4	−27.6～−26.6	/
后光学透镜	T5	−25.6～−22.7	/
后光学透镜	T6	−26.6～−23.7	/
次反射镜	T7	−32.3～−31.9	/

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