本文以阿爾法磁譜儀（AMS）電子設(shè)備熱控制系統(tǒng)為研究對(duì)象,基于實(shí)際飛行數(shù)據(jù),論證了熱控系統(tǒng)設(shè)計(jì)思路的正確性和有效性,分析了阿爾法磁譜儀探測(cè)器熱控制系統(tǒng)在軌運(yùn)行的基本規(guī)律,研究了國(guó)際空間站（ISS）的操作對(duì)阿爾法磁譜儀熱控制系統(tǒng)的影響,分析了在運(yùn)行過(guò)程中出現(xiàn)的溫度預(yù)警現(xiàn)象規(guī)律和原因,并提出了基于調(diào)節(jié)熱環(huán)境的熱控制建議。本文首先介紹了AMS實(shí)驗(yàn)的目的、意義以及已經(jīng)獲得的物理學(xué)結(jié)果。本文分析了國(guó)際空間站上的外部熱環(huán)境、AMS自身內(nèi)部熱負(fù)荷情況以及熱要求,介紹了AMS熱控制系統(tǒng)的方案。由于例子探測(cè)需要以及與國(guó)際空間站相配合,AMS熱控制系統(tǒng)設(shè)計(jì)思路與以往航天器的“完全包覆式”熱控制不同,AMS熱控制設(shè)計(jì)使用了大熱容材料應(yīng)對(duì)近地軌道熱環(huán)境的周期性劇烈變化。電子設(shè)備熱控制系統(tǒng)實(shí)際運(yùn)行數(shù)據(jù)表明,電子設(shè)備成功啟動(dòng),啟動(dòng)過(guò)程溫度曲線與模擬結(jié)果吻合；斷電時(shí)各電子箱均能保持在最低存活溫度以上；熱工況中各電子箱溫度低于最高存活溫度；軌道周期內(nèi)溫度波動(dòng)處于允許的范圍內(nèi)。長(zhǎng)時(shí)間飛行數(shù)據(jù)證明了熱控制系統(tǒng)設(shè)計(jì)思路的正確性以及熱控制系統(tǒng)的有效性。AMS在國(guó)際空間站上運(yùn)行后,在監(jiān)控過(guò)程中發(fā)現(xiàn),AMS熱控制系統(tǒng)運(yùn)行狀態(tài)受到... 

【文章來(lái)源】：山東大學(xué)山東省 211工程院校 985工程院校 教育部直屬院校

【文章頁(yè)數(shù)】：138 頁(yè)

【學(xué)位級(jí)別】：博士

【文章目錄】：
Acronyms and Abbreviations
摘要
Abstract
1. Introduction
    1.1 Introduction to the AMS project
    1.2 Thermal control
    1.3 Thermal analysis
    1.4 Objectives
2. The thermal control system of the AMS electronics
    2.1 AMS electronics
    2.2 Thermal environment
    2.3 Thermal Requirement
    2.4 The TCS scheme
        2.4.1 Radiators
        2.4.2 Heat pipes
        2.4.3 Heaters and thermostats
        2.4.4 MLI and optical-thermo painting
    2.5 On-Orbit operation of TCS
        2.5.1 AMS activation
        2.5.2 AMS in power outage
        2.5.3 AMS electronics in hot case
    Summary
3. Investigations on the operation regularity of the TCS for the AMS electronics
    3.1 The β angle of the ISS
    3.2 Temperature dependence on β
        3.2.1 Methods
        3.2.2 Results and discussions
    3.3 Temperature anomalies at specific β
    3.4 Data fit
    3.5 Analysis of temperature field of main radiators
        3.5.1 The data in use
        3.5.2 Method
        3.5.3 Temperature fields
        3.5.4 Discussions
    Summary
4. Investigations on the impacts of the ISS manoeuvres on the TCS for the AMS electronics
    4.1 Introduction to the peculiar manoeuvres of the ISS
        4.1.1 Locking the solar arrays
        4.1.2 Changing the flying attitude
        4.1.3 Adjusting the position of the ISS starboard radiator
    4.2 The influences of locking solar arrays
        4.2.1 Temperature-drop dependence on β
        4.2.2 Analysis of the normal-β cases
        4.2.3 Analysis of the extreme-β cases
    4.3 The influences of attitude change
        4.3.1 +XVV&+ZLV to +ZVV&-XLV
        4.3.2 +XVV&+ZLV to -XVV&+ZLV
        4.3.3 +XVV&+ZLV to -ZVV&-XLV
        4.3.4 +XVV&+ZLV to +YVV&+ZLV
    4.4 The influences of adjusting γ angle
        4.4.1 The most-effective-reflecting γ angle
        4.4.2 The adjustment of the γ angle affects the WAKE radiator
    Summary
5. Investigations on the temperature warnings of the AMS
    5.1 Components with temperature warnings
    5.2 Regularity of the temperature warnings
        5.2.1 Method
        5.2.2 Results and discussions
    5.3 Impacts of the ISS manoeuvres on the temperature warnings
        5.3.1 Impacts of adjusting the γ angle
        5.3.2 Impacts of locking solar arrays
        5.3.3 Impacts of changing the attitude
        5.3.4 Summary of the impacts
    Summary
6. Prospects
7. Conclusions
References
Acknowledgements
Paper published
附件


【參考文獻(xiàn)】：
期刊論文
[1]Design and experimental study of thermal control system for AMS cryocoolers[J]. WANG NaiHua,JOSEPH Burger,CHENG Lin.  Chinese Science Bulletin. 2013(10)
[2]Operation characteristics of AMS-02 loop heat pipe with bypass valve[J]. Joseph BURGER.  Science China(Technological Sciences). 2011(07)



本文編號(hào)：2936678