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研究生:張展瑞
研究生(外文):Jhan-RueiChang
論文名稱:CKUTEX微衛星熱控次系統設計分析與驗證
論文名稱(外文):Design, Analysis and Verification of Thermal Control Subsystem for the CKUTEX Microsatellite
指導教授:苗君易苗君易引用關係
指導教授(外文):Jiun-Jih Miau
學位類別:碩士
校院名稱:國立成功大學
系所名稱:航空太空工程學系碩博士班
學門:工程學門
學類:機械工程學類
論文種類:學術論文
論文出版年:2012
畢業學年度:100
語文別:中文
論文頁數:85
中文關鍵詞:熱控次系統熱真空測試熱浸泡
外文關鍵詞:CKUTEXThermal control subsystemThermal vacuum test
相關次數:
  • 被引用被引用:1
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  • 下載下載:42
  • 收藏至我的研究室書目清單書目收藏:0
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.
摘要 II
Abstract IV
致謝 V
目錄 VI
表目錄 IX
圖目錄 XI
符號與縮寫 XIV
第一章序論 1
1-1 前言 1
1-2 文獻回顧 3
1-2-1 熱測試 4
1-3 研究動機 8
1-4 CKUTEX 任務需求 9
1-5 章節安排 9
第二章 衛星參數熱源分析 10
2-1衛星參數分析 10
2-1-1 衛星結構 10
2-1-2衛星座標 11
2-2 熱源分析 11
2-2-1 相對位置 11
2-2-2 外部熱源分析 11
2-2-3 內部熱源分析 11
第三章實驗架構 18
3-1 熱烘烤實驗架構與測試結果 18
3-2熱浸泡實驗測試架構 19
3-2 EQM測試實驗架構 20
3-3 FM 測試實驗架構 21
第四章 真空艙體設計模擬與分析 23
4-1 模擬架構與原理 23
4-2 模組建立與參數分析 28
第五章 實驗與模擬結果驗證與討論 29
第六章 結論與未來展望 35
參考文獻 38
表 44
圖 52
附錄 85
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