环境C卫星热系统设计与在轨验证

王磊; 文耀普

doi:10.11728/cjss2015.02.224

环境C卫星热系统设计与在轨验证

doi: 10.11728/cjss2015.02.224

王磊,
文耀普

中国空间技术研究院钱学森空间技术实验室北京 100094

基金项目: 国家重大科技专项工程项目资助

详细信息

中图分类号: V474.2;TK124
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出版历程
- 收稿日期: 2014-04-21
- 修回日期: 2015-01-03
- 刊出日期: 2015-03-15

Thermal design and flight validation of HJ-1-C

Wang Lei,
Wen Yaopu

Qian Xuesen Laboratory of Space Technology, China Academy of Space Technology, Beijing 100094

摘要

摘要: 根据环境C卫星的自身特性, 采用以被动式热控制为主和主动热控制为辅的控制方式, 对环境C卫星进行热系统设计. 通过研究环境C卫星的热控设计原则、热设计状态及已解决的关键问题, 对其在轨飞行温度数据进行了分析. 在轨飞行遥测结果表明, 环境C卫星热控系统方案合理, 工作稳定, 性能良好. 星上设备温度环境很好地满足了设计要求.
- 遥感航天器 /
- 热设计 /
- 飞行验证
Abstract: HJ-1-C is a Synthetic Aperture Radar (SAR) satellite of the Chinese Environment and Natural Disaster Monitoring constellation launched on November 19, 2012. The SAR payload uses mesh parabolic reflector antenna and solid-state transmitter to transmit high power in centralized manner. Based on the design concept that passive thermal control would be preferred over active thermal control for its simplicity and inherent reliability, HJ-1-C satellite thermal control system were provided in accordance with the HJ-1-C satellite working characteristics and space thermal environment on its orbit. The presentations about thermal design techniques, scheme and key problems solved are given. Moreover, onboard performance of the satellite on its orbit was analyzed. The flight telemetry data showed that the thermal control design was reasonable and well satisfied with the temperature requirements of the electronic equipments and payloads, which ensured the safety and reliability operation of satellite.
- Remote sensing spacecraft /
- Thermal design /
- Flight Validation

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参考文献(11)

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