本文關(guān)鍵詞： 太陽望遠鏡 深空探測 熱設(shè)計 熱分析 熱光學(xué)分析 日冕儀 空間光學(xué)遙感器　出處：《中國科學(xué)院研究生院(長春光學(xué)精密機械與物理研究所)》2013年碩士論文　論文類型：學(xué)位論文

【摘要】：為實現(xiàn)對空間環(huán)境的監(jiān)測，提出了太陽觀測計劃，該計劃擬將太陽觀測望遠鏡發(fā)射到離地球150萬公里的日-地系拉格朗日L1點附近的halo軌道。該相機屬于深空探測任務(wù)，搭載了日冕儀（LACI）和成像儀（LADI）兩臺設(shè)備，由于長期對日定向觀測，且軌道外熱流密度大，，對于熱控設(shè)計來說是個挑戰(zhàn)。 1.本文對國外同類型產(chǎn)品的熱設(shè)計方案進行了研究，通過對比各個熱設(shè)計方案，分析了該軌道太陽觀測望遠鏡熱設(shè)計的特點； 2.介紹該太陽觀測望遠鏡的組成和結(jié)構(gòu)特點，并分析了軌道熱環(huán)境，計算該軌道的太陽外熱流密度； 3.結(jié)合望遠鏡自身的特點制定濾光片組件、電箱組件、CCD組件、LACI反射鏡M2光阱組件和整機的熱設(shè)計方案，通過在向陽面布置集熱板，將主動加熱功耗降低73%，通過多套方案的對比，最終選擇較為合理的熱設(shè)計方案； 4.通過I-DEAS/TMG軟件對三維模型進行網(wǎng)格劃分、仿真分析，計算出各個工況下相機溫度的分布情況，驗證表明各組件均符合溫度指標要求。該熱設(shè)計方案以較低的加熱功耗，解決了太陽觀測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組件與探測器主體間不小于70℃溫差的保障等問題； 5.基于上述方案對相機進行優(yōu)化熱設(shè)計，得到最合理的熱控措施。給出集熱板表面屬性的選擇建議、控溫點的設(shè)置依據(jù)、熱管的安裝方式，對于航天器熱控制技術(shù)提有一定的指導(dǎo)意義。 6.基于PATRAN對該太陽望遠鏡進行熱彈性計算，對反射鏡鏡面各節(jié)點擬合計算，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)計要求進行對比，表明該熱設(shè)計方案滿足光學(xué)指標，驗證了熱控分系統(tǒng)的可行性；最后計算系統(tǒng)的動態(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

本文編號：1476380