衛星酬載遙測取像儀用於地表觀測，需承受高真空、高溫差、重力、25 G發射重力加速度、振動等嚴苛環境，因此在取像儀光學系統的設計中，不只考慮光學品質的要求，亦需考慮其機械結構是否能承受惡劣的工作環境，故針對遙測取像儀之主鏡進行最佳化設計。本文利用一口徑550 mm的Zerodur®主鏡，搭配參數最佳化軟體串聯電腦輔助設計、有限元素分析軟體、光機轉換程式，進行主鏡減重與撓性支撐結構最佳化設計，最佳化內容包含: 輕量化、維持剛性、良好光學品質。主鏡經過最佳化設計後減重比達66%；撓性支撐結構經過最佳化設計後，主鏡系統PV值為61 nm，RMS值為12 nm，第一共振頻率為315 Hz。;Remote sensing instrument (RSI, Remote Sensing Instrument), which is used to take images for ground surface observation, will be exposed to harsh environment including vacuum, large temperature difference, high launch acceleration and random vibration. Therefore, both the optical quality and the mechanical strength should be considered when designing the optical system of a RSI. In this study, an optimization method was adopted in the lightweight design of a Zerodur® mirror and its bi-pod flexure. The optimization aims to achieve the lightest mirror while maintaining both structural rigidity and good optical quality. An optimization processing combining computer-aided design, finite element analysis, opto-mechanical analysis and optimization algorithm was successfully performed. Finally, the optimum lightweight mirror and its three optimum bi-pod flexure mounts were attained.
