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Experimental research on thermal conductive fillers for CCD module in space borne optical remote sensor

机译:太空光学遥控器中CCD模块导热填料的实验研究

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A space-borne differential optical absorption spectrometer is a high precision aerospace optical remote sensor. It obtains the hyper-spectral, high spatial resolution radiation information by using the spectrometer with CCD (Charge Coupled Device) array detectors. Since a few CCDs are used as the key detector, the performance of the entire instrument is greatly affected by working condition of CCDs. The temperature of CCD modules has a great impact on the instrument measurement accuracy. It requires strict temperature control. The selection of the thermal conductive filler sticking CCD to the radiator is important in the CCD thermal design. Besides, due tothe complex and compact structure, it needs to take into account the anti-pollution of the optical system. Therefore, it puts forward high requirements on the selection of the conductive filler. In this paper, according to the structure characteristics of the CCD modules and the distribution of heat consumption, the thermal analysis tool I-DEAS/TMG is utilized to compute and simulate the temperature level of the CCD modules, while filling in thermal grease and thermal pad respectively. The temperature distribution of CCD heat dissipation in typical operating conditions is obtained. In addition, the heat balance test was carried out under the condition of two kinds of thermal conductive fillers. The thermal control of CCD was tested under various conditions, and the results were compared with the results of thermal analysis. The results show that there are some differences in thermal performance between the two kinds of thermal conductive fillers. Although they both can meet the thermal performance requirements of the instrument, either would be chosen taking account of other conditions and requirements such as anti-pollution and insulation. The content and results of this paper will be a good reference for the thermal design of the CCD in the aerospace optical payload.
机译:空间传播的差动光学吸收光谱仪是一款高精度航空航天光学遥控器。它通过使用具有CCD(电荷耦合器件)阵列检测器的光谱仪获得超频,高空间分辨率辐射信息。由于使用几个CCD作为关键探测器,因此整个仪器的性能受到CCD的工作条件的大大影响。 CCD模块的温度对仪器测量精度产生很大影响。它需要严格的温度控制。将CCD粘附到散热器的热导体填料的选择在CCD热设计中很重要。此外,由于复杂和紧凑的结构,需要考虑光学系统的抗污染。因此,它对导电填料的选择提出了高要求。本文根据CCD模块的结构特性和热量分布,热分析工具I-DEAS / TMG用于计算和模拟CCD模块的温度水平,同时填充热油脂和热量垫分别。获得了典型操作条件下CCD散热的温度分布。此外,在两种导热填料的条件下进行热平衡测试。在各种条件下测试CCD的热控制,并将结果与​​热分析结果进行比较。结果表明,两种导热填料之间的热性能存在一些差异。虽然它们都可以满足仪器的热性能要求,但是选择考虑到抗污染和绝缘等其他条件和要求。本文的内容和结果将是航空航天光学有效载荷中CCD的热设计的良好参考。

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