Thermal control system design and on-orbit verification of hyperspectral greenhouse gas monitor on FY-3D satellite
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摘要:
FY-3D卫星高光谱温室气体监测结构布局紧凑,在较小尺寸空间内布置有8个镜头组件、12台电子设备和3台电机。内热源数量众多,光学镜头控温精度要求高,热控功耗及散热面资源紧张,使热控系统设计难度较大。基于热管理、辐射间接热控、辐射冷却及结构热控协同优化设计等多种思路对监测仪热控系统进行设计,有效解决热控难题。入轨后监测仪历经了多个工况模式切换,在轨温度数据表明,所有工况模式下各部组件温度都满足指标要求,且光学镜头温度稳定度较高,在正常工作模式下,干涉仪关键件最大温度波动在±0.15℃以内,其他光学镜头组件最大温度波动在±0.45℃以内,且无论整轨待机模式还是正常工作模式,基于热管理的2组电子设备散热系统都无需消耗热控功耗,实现了多热源复杂机制下高精度控温及节能热设计。
Abstract:The structure layout of hyperspectral greenhouse gas monitor on FY-3D satellite is very compact. There are eight optical lens, twelve electronic devices and three motors in the small-scale space. There are so many optical lens with high-precision temperature control requirement and so many heat source equipment. And thermal control resources such as heating power and radiator layout space are limited. These above characteristics make thermal control system design of hyperspectral greenhouse gas monitor a challenge. Thermal control system was designed based on multiple design methods including thermal management, indirect radiation thermal control, radiation cooling and collaborative optimization design of integrated structural and thermal control. Thermal control difficult problems were solved effectively. Hyperspectral greenhouse gas monitor experienced multiple operating modes after entering orbit. On-orbit temperature data show that all components' temperatures meet the requirements, and optical lens have high temperature stability under all the experienced operating modes. The maximum temperature fluctuation of interferometer is within ±0.15℃ under normal operating mode, and it is within ±0.45℃ for other optical lens. Furthermore, no matter under standby mode in a whole orbit period or normal operating mode, the heat dissipation systems of two sets of electronic device designed based on thermal management do not need to consume thermal control power resources. High-precision thermal control and energy saving thermal design are realized under the condition of multiple heat sources and complex working mechanism.
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表 1 入轨后监测仪经历的工况模式
Table 1. Summary of operating modes experienced by monitor after entering orbit
在轨开始时刻 模式名称 模式描述 2017-11-15T04:30 生存模式 入轨初期,卫星平台进行姿态调整、太阳帆板展开等飞行调试工作,监测仪进入生存模式 2017-11-25T20:13 整轨关机模式 监测仪管理控制器和温度控制器(都放置在卫星舱内)开机,监测仪进入整轨关机模式 2017-11-26T09:53 整轨待机模式 监测仪内部计量激光器和探测器半导体制冷控制器开机,监测仪进入整轨待机模式 2017-11-26T11:34 正常工作模式 监测仪进入“待机模式→观测模式→定标模式→待机模式”的正常工作流程 表 2 正常工作模式下监测仪内部热源工作热耗及工作时间
Table 2. Heat consumption and operating time of calorigenic equipment in monitor under normal operating mode
部组件名称 热耗/W 工作时间/(min·轨-1) 待机 观测 定标 半导体制冷控制器 11 11 11 102 激光信号处理器 0 3 3 68 谱段1探测器电路盒 0 0.3 0.3 63 谱段2探测器电路盒 0.9 1.2 1.2 102 谱段3探测器电路盒 0.9 1.2 1.2 102 谱段4探测器电路盒 0.9 1.2 1.2 102 定标控制器 0 0 4 3 红外信息处理器 0 20 20 63 定标控制器DCDC 0 0 21.1 3 计量激光器 8 8 8 102 监视相机 0 4 4 52 激光探测器 0 0.21 0.21 68 二维指向镜步进电机 0 1.6 1.6 51 二维指向镜音圈电机 0 2.0 2.0 51 干涉仪摆臂音圈电机 0 1.0 1.0 58.2 表 3 监测仪各部组件控温指标要求
Table 3. Temperature control requirements of monitor components
部组件名称 温度/℃ 生存模式 正常工作模式 主镜、次镜、谱段1~谱段4透镜 0~40 20±2 二维指向镜镜体 0~40 19±3 干涉仪 0~40 20±1,摆臂左右分支温差≤0.5℃ 探测器组件电路盒 -20~40 0~20 其他电子设备 -15~55 -10~45 二维指向镜步进电机 -10~80 -10~80 二维指向镜音圈电机 0~85 0~85 干涉仪摆臂音圈电机 0~75 0~75 表 4 监测仪生存加热回路
Table 4. Summary of survival heating circuits of monitor
加热区域 回路路数 功率/W 备注 底板4端面 4 4.0 由卫星平台直接控制,常开 外罩内表面 7 16.7 半导体制冷控制器盒体 1 6.8 红外信息处理器盒体 1 7.0 计量激光器散热热管表面 1 5.0 监视相机散热热管表面 1 2.0 探测器电路盒散热热管表面 1 4.0 辐射冷屏散热热管表面 1 5.0 表 5 监测仪主动控温加热回路
Table 5. Summary of active temperature control heating circuits of monitor
加热区域 回路路数 功率/W 控温阈值/℃ 备注 底板上、下表面 5 15.9 [19.8,20.2] 由监测仪温度控制器控制主动控温 外罩外表面 11 31.4 [19.8,20.2] 分色汇聚组件镜筒 2 4.4 [19.8,20.2] 激光信号处理器盒体 1 7.0 [8.8,9.2] 探测器电路盒 1 7.0 [9.8,10.2] 计量激光器电路盒 1 7.9 [7.3,7.7] 监视相机电路盒 1 3.0 [7.1,7.5] 辐射冷屏 1 6.0 [9.8,10.2] 表 6 生存模式稳定状态下监测仪遥测温度
Table 6. Summary of monitor telemetered temperature under steady survival mode
部组件名称 温度/℃ 温度波动/℃ 控温指标/℃ 半导体制冷控制器 5.2~10.3 5.1 -15~55 红外信息处理器 8.1~10.7 2.6 -15~55 计量激光器 9.9~12.9 3.0 -15~55 监视相机 9.6~12.9 3.3 -15~55 谱段4探测器电路盒 8.3~12.3 4.0 -20~40 二维指向镜 16.6~18.6 2.0 0~40 干涉仪基座 19.3~19.7 0.4 0~40 主镜 19.8~20.2 0.4 0~40 表 7 不同模式状态下监测仪遥测温度
Table 7. Summary of monitor telemetered temperature under different operating modes
部组件名称 遥测温度/℃ 控温指标 整轨关机模式 整轨待机模式 正常工作模式 主镜 19.8~20.2 19.8~20.2 20.6 20±2 谱段4透镜 19.7~19.9 19.3~19.8 19.5~19.9 20±2 谱段3透镜 19.8~19.9 19.3~19.8 19.4~19.9 20±2 谱段2透镜 19.8~20.2 19.8~20.2 19.8~20.1 20±2 次镜 20.4~21.1 20.4~21.0 20.6~21.5 20±2 二维指向镜 17.7~18.6 17.7~18.6 19.0~20.5 19±3 干涉仪摆臂端部1 20.1~20.3 20.1~20.3 20.2~20.4 20±1,摆臂 干涉仪摆臂端部2 20.1~20.2 20.1~20.2 20.1~20.2 左右分支 干涉仪摆臂中部 19.7~19.8 19.7~19.8 20.1~20.2 温差 干涉仪基座 19.6~19.7 19.6~19.7 20.1~20.2 ≤0.5 谱段4探测器电路盒 7.6~10.1 9.7~11.2 9.2~10.8 0~20 谱段3探测器电路盒 7.6~10.2 8.9~10.2 9.2~10.9 0~20 谱段2探测器电路盒 7.6~10.1 8.9~10.1 9.1~10.9 0~20 谱段1探测器电路盒 7.6~10.3 8.8~10.4 9.1~11.0 0~20 半导体制冷控制器 -2.2~2.6 -0.3~7.0 9.5~14.3 -10~45 激光信号处理器 9.1~9.2 9.2~13.2 21.1~22.4 -10~45 红外信息处理器 4.2~5.9 4.5~7.0 18.2~21.7 -10~45 计量激光器 6.2~7.5 7.1~11.4 19.2~21.4 -10~45 监视相机 6.9~7.7 7.3~9.9 15.7~20.0 -10~45 二维指向镜步进电机 18.6~18.7 18.6~18.7 25.6~33.4 -10~80 摆臂音圈电机磁缸及线圈铝骨架 17.1~17.7 17.1~17.7 19.8~22.8 0~75 -
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