本文是以設計TUUSAT-1A微衛星熱控子系統為目的，完成TUUSAT-1A微衛星熱控子系統的程式模擬分析。初步設計是28正立方公分微衛星幾何外形，搭配衛星任務需求，使用被動式磁棒的旋轉方式，並利用節點網格法的分析模式，以數值疊代方法來求解非線性能量方程式中的衛星溫度。且以被動式熱控技術，使衛星內元件能在安全溫度下正當運作。在假設衛星不同beta angle及衛星worse case的狀況下時，計算衛星的內外表面溫度變化情形，並且比較各元件操作溫度，將衛星內部溫度維持在各元件的操作溫度下，使衛星能完成其各項任務。最後根據TUUSAT-1A之熱控設計的方法及模擬的數據，可以作為日後不同任務需求，對衛星溫度的參考。 This paper employed the thermal Network Method to simulate satellite, TUUSAT-1A (28×28×28cm³) which employed the passive thermal control device and discussed the effects of various spin speed, altitude, beta angle and finish of the satellite on the thermal control system. When the TUUSAT-1A Micro-satellite under the different beta angles and different worse case conditions, we simulated and calculated the temperatures of inside and outside surface individually, and compared the component’s operating temperature. The final results show that, for each possible beta angle, the present thermal design is able to maintain each component’s temperature within their allowable ranges with an uncertainty margin of 5℃.
