本研究針對太空中心現有兩種不同之平面反射鏡撓性支撐結構設計進行實驗與有限元素模擬，藉以了解兩者在溫度變化(22 °C~40°C)下對反射鏡造成的影響差異，並且進一步針對撓性支撐結構進行最佳化。實驗共分為兩個部份，包含光彈儀量測與干涉儀量測，兩種實驗皆以有限元素模擬進行比對驗證。光彈儀量測實驗主要觀察溫度變化下兩種撓性支撐機構設計將應力傳遞至反射鏡之影響程度；干涉儀實驗則觀察溫度變化下，兩種撓性支撐設計對平面反射鏡光學面形變化之影響。最佳化設計分析部份則是使用多島基因演算法將兩種設計中干涉儀實驗結果較佳之設計進行尺寸最佳化，期望能進一步降低溫度差對反射鏡造成的影響。最終結果為保有較多切向自由度撓性設計，於所搭接之介面溫度變化(22 °C~40°C)下較能維持反射鏡之光學品質。在底板溫度為40 °C下，有限元素模擬之最佳化結果成功將鏡面面形變形量峰谷值(Peak-to-Valley)由34.42 nm下降至16.00 nm。;In this study, two optical measurements were adopted to compare the opto-mechanical performance of two flexure designs for a flat mirror in the NSPO (National Space Organiztion). In order to obtain the stress effect and optical performance of the mirror under temperature fluctuation, the photoelasticity and the interferometric measurement were conducted in this study, and both of them will be validated by using finite element analysis. Furthermore, the optimization of one of the flexure mount design has been accomplished by using the Multi-Island Genetic Algorithm. The result of interferometric measurement shows that flexure design which retains more tangential freedom can maintain better optical quality of the flat mirror under temperature fluctuation. And after optimization, its optical PV (peak-to-valley) value under 40 °C reduced from 34.42 nm to 16.00 nm.
