人造衛星的熱控系統一直是衛星設計上重視的一環，熱控的設計在太空環境中排除熱對流的熱傳方式，只考慮到熱輻射及熱傳導的部分，由此概念設計出整個系統決定整個衛星的溫度分佈，此外衛星的分析考慮能成功的模擬衛星本體結構而且要考慮能模擬太空環境，藉由軟體模擬分析來預測熱效應以減少對實體測試的需求，本研究的方法用CATIA來建構模型，並以ANSYS來建立網格，設定邊界條件，如材質，輻射量的設定，及熱源的設定，以暫態熱分析來分析衛星的溫度分佈，另外也介紹到衛星在外太空實際會接受到的熱源。為避免衛星受到外太空的高低溫環境影響而對於電子元件所造成的損壞, 並且能符合火箭規範，而達成衛星升空且進行任務，衛星測試及驗證也在本文討論內容，其中包含到熱真空熱浸泡的測試(thermal soak test)，而測試的流程圖依據MIL-STD-810F規範，設計出流程圖，另外實驗中所使用MLI(Multi-layer Insulation)材質，使進行真空實驗時衛星有穩定的熱源供應，及CHO-THERM 1671使用讓熱源能夠快速傳導到衛星本體，本文也討論到EQM(Engineering qualification model)及FM(Flight model) 的實驗數據量測中不同位置與模擬後的數據進行衛星熱控系統之驗證。本論文將以成功大學所研發自製的CKUTEX(Cheng Kung University Technology EXperimental Satellite)微衛星做為熱控制設計對象，由前述的模擬方式與測試實驗作比較以驗證並改善模擬方式，並且比較各個次系統元件的溫度規範，得到溫度控制的範圍，確保元件能存活於嚴峻的太空環境，由實驗前模擬與實驗數據作比較改善以設計出驗證流程。

This paper illustrates the thermal control of CKUTEX (Cheng-Kung University Technology Experiment) satellite, the microsatellite which is developed at National Cheng Kung University. The objective is to effectively control temperature of electrical devices in a reasonable range to avoid thermal failure or thermal damage. Being different from some existing approaches of using special thermal control materials or sophisticated cooling/heating devices, this paper proposes a passive thermal control method by addressing the placement of devices through comprehensive structure design, in addition the verification with thermal analysis and environment test also be discussed. The predicted temperature of each subsystem can be simulated by ANSYS also enter the data which are calculated for considering solar flux, albedo and earth infrared that from the space environment, also concern the satellite structure, material and the heat source from each component . According to these results, the corresponding passive thermal control strategy of CKUTEX is applied. Before the environment test, the simulation of whole system is executed to predict temperature range of each subsystem .The thermal verification test that play an important role in ensuring the mission operation in the space.

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