On-orbit Thermal Analysis for Verification of Thermal Design of 6 U Nano-Satellite with Multiple Payloads
On-orbit Thermal Analysis for Verification of Thermal Design of 6 U Nano-Satellite with Multiple Payloads
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用于验证多有效载荷 6 U 纳米卫星热设计的在轨热分析
DOI：
10.5139/jksas.2020.48.6.455
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发表时间：
2020
期刊：
影响因子：
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通讯作者：
Kim Hae
中科院分区：
文献类型：
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作者：
Ji;H. Kim;Min;Kim Hae
在本研究中，我们为担负近地空间环境科学测量任务的SNIPE 6U纳米卫星建立了热模型，并描述了基于该热模型的热设计。并通过在轨热分析验证了热设计的有效性。针对纳米卫星的特点，主要对表面涂层、绝缘层、导热材料等被动热控制技术进行了热设计。然而，工作温度范围较窄且直接暴露在轨道热环境中的部件，如电池和推进器，需要配备加热器来满足温度要求。在轨热分析条件是基于卫星的基本轨道条件，根据任务场景对正常模式、发射和轨道早期阶段(LEOP)、安全模式和机动模式进行了热分析，这些模式根据卫星的功耗和姿态进行了分类。对各工况的分析结果表明，各部件均满足温度要求。此外，根据安全模式的分析结果，计算了电池和推进器的加热器容量和占空比。
In this study, we built a thermal model for SNIPE 6U nano-satellite which has scientific mission for measuring science data in near Earth space environment and described thermal design based on the thermal model. And the validity of the thermal design was verified through the on-orbit thermal analysis. The thermal design was carried out mainly on the passive thermal control techniques such as surface finishes, insulators, and thermal conductors in consideration of the characteristics of the nano-satellite. However, the components with narrow operating temperature range and directly exposed to the orbital thermal environments, such as a battery and thrusters, are accomodated with heaters to satisfy the temperature requirements. On-orbit thermal analysis conditions are based on the basic orbital conditions of the satellite, and thermal analysis was performed for Normal mode, Launch & Early Orbit Phase (LEOP), Safehold mode, and Maneuver mode which are classified by the power consumption and the attitude of the satellite according to the mission scenario. The analysis results for each mode confirmed that every component satisfies the temperature requirement. In addition, the heater capacity and duty cycle of the battery and thruster were calculated through the analysis results of the Safehold mode.