衛星發射到太空中面臨到的環境是極為嚴苛的，在缺少熱對流的效應之下，內部元件容易因為極端的溫度而故障無法操作，而熱控分析、熱控設計以及測試的目的就是為了確保衛星能夠在安全的溫度範圍內工作。本論文一部分探討由成功大學微衛星團隊自主研發的PACE衛星的熱分析，以先前的熱分析技術為基礎利用Catia建立衛星模型，STK、MATLAB以及Excel建立熱通量參數，ANSYS Workbench進行熱分析，進一步加入視角因子的計算以改良外部熱源的計算方式，並且與先前的分析方法做比較，另外探討不同材料以及軌道對衛星溫度分布的影響。論文另一部分則是探討熱真空抽氣設備的建立，以所需的要求為前提下，建立自主的環測設備，確保設備能夠達到測試的規範。

The environment in the space is very critical for satellites. In the environment which has no thermal convection, the devices in the satellite might failed due to the extreme temperature. The purpose of thermal design, thermal analysis and thermal vacuum test is to demonstrate that satellites can keep within the operating temperature in space. The first part of this thesis is to do the thermal analysis of the PACE satellite which developed by NCKU small satellite team. Based on the previous technic in which built CAD model by CATIA and created the external heat source by STK and MATLAB, this thesis improve the calculation in the view factor for external heat flux. Make cases to compare the simulation with which simulated by previous parameters. Moreover, compare the difference among different materials which used in satellite. The second part of this thesis is to discuss about setting up the facility for thermal vacuum test which could be satisfied the requirement of CubeSat Standard.

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