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文章名稱:
太空熱環境變化對人造衛星表面結構之溫度分佈研究
The Effect of Space Environment on Spacecraft Temperature Distribution
作者名稱:
蘇艾(Ay Su) ； 盧盈庄(In-Chung Lu)
資料來源:
中國航空太空學會學刊 ； 29 卷 2 期 (1997 / 06 / 01) ， P171 - 180
內容摘要:
人造衛星的溫度控制一直是設計上的一大問題，通常衛星熱控系統的研發必須考慮到輻射與傳導，用以設計此系統來決定整個衛星的溫度分佈，熱輻射與熱傳導的交互作用對任何一枚衛星系統而言皆可使用微分型態的統御方程式來描述並將其相互關係一併考慮。
衛星的數值分析不祇要能成功的模擬衛星本體結構而且要能模擬太空環境，運用網絡法來考慮輻射與傳導交互作用下的能量傳遞方式，本研究的目的在於使用數值方法來預測熱效應以減少對實體測試的需求。
本研究分成兩大主要部分撰寫程式，第一先求得輻射熱通量（此爲太空環境性質，與衛星位置、姿態有關），第二求溫度分布（此與輻射熱通量、材料性質皆有關）。目的爲計算衛星繞行軌道時周期性的溫度變化，探討外太空熱力環境在絕大溫差下之實際熱能傳遞模擬，以提供衛星材料機械性質選擇與熱彈力學的參考。
The Space environment affects space system's survivability, reliability, performance and cost. The thermal environment varies significantly throughout because of changes in attitude, altitude, power dissipation and operating modes. Thus, the design of satellite structure must consider the thermal environment effect from the stage of build up to the end of mission. The mathematical and numerical model are developed and applicable for spacecraft alloy materials as well as composite materials, to calculate structure thermal properties, such as emission, absorptivity, and transmission, surface temperature distributions and allowable temperature margin in the boundary. Numerical modelling of the spacecraft not only of the vehicle but modelling of the space environment as well. Predictions from the use of thermal network correction techniques which include radiation and conduction coupling considerations, reveds that the major difference between transient and steady state is during the coming and out of the shadow area.
太空熱環境變化對人造衛星表面結構之溫度分佈研究
The Effect of Space Environment on Spacecraft Temperature Distribution
作者名稱:
蘇艾(Ay Su) ； 盧盈庄(In-Chung Lu)
資料來源:
中國航空太空學會學刊 ； 29 卷 2 期 (1997 / 06 / 01) ， P171 - 180
內容摘要:
人造衛星的溫度控制一直是設計上的一大問題，通常衛星熱控系統的研發必須考慮到輻射與傳導，用以設計此系統來決定整個衛星的溫度分佈，熱輻射與熱傳導的交互作用對任何一枚衛星系統而言皆可使用微分型態的統御方程式來描述並將其相互關係一併考慮。
衛星的數值分析不祇要能成功的模擬衛星本體結構而且要能模擬太空環境，運用網絡法來考慮輻射與傳導交互作用下的能量傳遞方式，本研究的目的在於使用數值方法來預測熱效應以減少對實體測試的需求。
本研究分成兩大主要部分撰寫程式，第一先求得輻射熱通量（此爲太空環境性質，與衛星位置、姿態有關），第二求溫度分布（此與輻射熱通量、材料性質皆有關）。目的爲計算衛星繞行軌道時周期性的溫度變化，探討外太空熱力環境在絕大溫差下之實際熱能傳遞模擬，以提供衛星材料機械性質選擇與熱彈力學的參考。
The Space environment affects space system's survivability, reliability, performance and cost. The thermal environment varies significantly throughout because of changes in attitude, altitude, power dissipation and operating modes. Thus, the design of satellite structure must consider the thermal environment effect from the stage of build up to the end of mission. The mathematical and numerical model are developed and applicable for spacecraft alloy materials as well as composite materials, to calculate structure thermal properties, such as emission, absorptivity, and transmission, surface temperature distributions and allowable temperature margin in the boundary. Numerical modelling of the spacecraft not only of the vehicle but modelling of the space environment as well. Predictions from the use of thermal network correction techniques which include radiation and conduction coupling considerations, reveds that the major difference between transient and steady state is during the coming and out of the shadow area.
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