卷期 : 12 /
出版年 : 2016/01/01
基於衛星用電子元件模組自主設計發展,其擁有符合太空環境需求的結構強度至為重要。有鑑於此,本文以福衛五號(FORMOSAT-5)上的遙測酬載電子單元(Remote Sensing Instrument/Electronic Unit, RSI/EU)為例,說明如何在設計階段透過有限元素分析(Finite Element Analysis, FEA)來進行元件結構強度的驗證,其驗證項目為福衛五號元件環境規範中所定義的各種負荷類型,包含自然頻率、靜態(慣性力、吊掛力與挫曲)與動態(正弦、隨機振與衝擊)負荷等。最後本文利用結構安全裕度(Margins of Safety, MoS)的計算,研判RSI/EU關鍵元件的結構強度是否符合設計需求。Based on the development of the won design ability for electronic units in satellites, it is important for these units to meet the environmental requirements of satellite system with qualified structural design. In this paper, the Remote Sensing Instrument/Electronic Unit, RSI/EU, in FORMOSAT-5 is used as an example to show how to use the Finite Element Analysis, FEA, to verify its structural strength in design stage under the loads of FORMOSAT-5 component environmental specification, and these verifications include natural frequencies, static (inertia, hoist and buckling) and dynamic (sine, random vibration and shock) loads. Finally, the structural safety requirements of the critical components of the RSI/EU for FORMOSAT-5 specification can be distinctly verified by calculating their Margins of safety, MoS.
關鍵詞 : 電子元件模組、有限元素分析、結構安全裕度 Key words:Electronic Units; Finite Element Analysis; Margins of Safety