本文關(guān)鍵詞： 太陽(yáng)望遠(yuǎn)鏡 深空探測(cè) 熱設(shè)計(jì) 熱分析 熱光學(xué)分析 日冕儀 空間光學(xué)遙感器　出處：《中國(guó)科學(xué)院研究生院(長(zhǎng)春光學(xué)精密機(jī)械與物理研究所)》2013年碩士論文　論文類型：學(xué)位論文

【摘要】：為實(shí)現(xiàn)對(duì)空間環(huán)境的監(jiān)測(cè)，提出了太陽(yáng)觀測(cè)計(jì)劃，該計(jì)劃擬將太陽(yáng)觀測(cè)望遠(yuǎn)鏡發(fā)射到離地球150萬(wàn)公里的日-地系拉格朗日L1點(diǎn)附近的halo軌道。該相機(jī)屬于深空探測(cè)任務(wù)，搭載了日冕儀（LACI）和成像儀（LADI）兩臺(tái)設(shè)備，由于長(zhǎng)期對(duì)日定向觀測(cè)，且軌道外熱流密度大，，對(duì)于熱控設(shè)計(jì)來(lái)說(shuō)是個(gè)挑戰(zhàn)。 1.本文對(duì)國(guó)外同類型產(chǎn)品的熱設(shè)計(jì)方案進(jìn)行了研究，通過(guò)對(duì)比各個(gè)熱設(shè)計(jì)方案，分析了該軌道太陽(yáng)觀測(cè)望遠(yuǎn)鏡熱設(shè)計(jì)的特點(diǎn)； 2.介紹該太陽(yáng)觀測(cè)望遠(yuǎn)鏡的組成和結(jié)構(gòu)特點(diǎn)，并分析了軌道熱環(huán)境，計(jì)算該軌道的太陽(yáng)外熱流密度； 3.結(jié)合望遠(yuǎn)鏡自身的特點(diǎn)制定濾光片組件、電箱組件、CCD組件、LACI反射鏡M2光阱組件和整機(jī)的熱設(shè)計(jì)方案，通過(guò)在向陽(yáng)面布置集熱板，將主動(dòng)加熱功耗降低73%，通過(guò)多套方案的對(duì)比，最終選擇較為合理的熱設(shè)計(jì)方案； 4.通過(guò)I-DEAS/TMG軟件對(duì)三維模型進(jìn)行網(wǎng)格劃分、仿真分析，計(jì)算出各個(gè)工況下相機(jī)溫度的分布情況，驗(yàn)證表明各組件均符合溫度指標(biāo)要求。該熱設(shè)計(jì)方案以較低的加熱功耗，解決了太陽(yáng)觀測(cè)器在軌工作階段的散熱、軌道轉(zhuǎn)移階段的保溫、工作狀態(tài)下CCD組件與探測(cè)器主體間不小于70℃溫差的保障等問(wèn)題； 5.基于上述方案對(duì)相機(jī)進(jìn)行優(yōu)化熱設(shè)計(jì)，得到最合理的熱控措施。給出集熱板表面屬性的選擇建議、控溫點(diǎn)的設(shè)置依據(jù)、熱管的安裝方式，對(duì)于航天器熱控制技術(shù)提有一定的指導(dǎo)意義。 6.基于PATRAN對(duì)該太陽(yáng)望遠(yuǎn)鏡進(jìn)行熱彈性計(jì)算，對(duì)反射鏡鏡面各節(jié)點(diǎn)擬合計(jì)算，得到6面反射鏡各自的面形結(jié)果，將面形結(jié)果與光學(xué)設(shè)計(jì)要求進(jìn)行對(duì)比，表明該熱設(shè)計(jì)方案滿足光學(xué)指標(biāo)，驗(yàn)證了熱控分系統(tǒng)的可行性；最后計(jì)算系統(tǒng)的動(dòng)態(tài)剛度得到一階固有頻率為73.3Hz，滿足發(fā)射和在軌要求。
[Abstract]:In order to realize the monitoring of the space environment, a solar observation plan was put forward. The plan is to launch the Solar Telescope into halo orbit 1.5 million kilometers from Earth near the Lagrangian L1 point. The camera is a deep space exploration mission. It is a challenge to the design of thermal control because of the long term directional observation of the sun and the high heat flux outside the orbit. 1. The thermal design schemes of the same type of products abroad are studied in this paper. The characteristics of the thermal design of the orbiting solar observation telescope are analyzed by comparing the various thermal design schemes; 2. The composition and structural characteristics of the solar telescope are introduced. The thermal environment of the orbit is analyzed and the heat flux outside the orbit is calculated. 3. According to the characteristics of the telescope, the thermal design scheme of the filter assembly, the CCD component of the electric box and the M2 optical trap assembly of the LACI reflector and the whole machine are made, and the collection plates are arranged on the positive side. The power consumption of active heating is reduced by 73, and through the comparison of multiple schemes, a more reasonable thermal design scheme is finally selected. 4. The 3D model is meshed by I-DEAS-TMG software, and the temperature distribution of the camera is calculated by simulation and analysis. The verification shows that all the components meet the requirements of the temperature index. The thermal design scheme solves the heat dissipation of the solar observer in orbit operation phase and the thermal insulation in the orbit transfer phase with lower heating power consumption. The protection of temperature difference between the CCD module and the detector body is not less than 70 鈩

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