本研究針對立方衛星的應用情景，設計並以模擬與實驗驗證一款具備無動力展開功能之展開機構。其管杆設計靈感源自NASA之Deployable Composite Booms（DCB）實驗，主體採用截面為唇形之碳纖維強化聚合物（Carbon Fiber Reinforced Polymer, CFRP）管材，具備高彎曲（Bending）與扭轉（Torsion）剛性。本機構利用儲存於材料內部之彈性能完成展開，無需任何主動驅動元件，藉由燒線機構控制展開時機，實現低功耗、低質量與高可靠度之結構部署。為確保本機構於發射過程中之結構完整性與任務安全性，本研究依據SpaceX所公布之Falcon Payload User's Guide 環境要求，執行模態分析與隨機振動分析兩項模擬，以預測其在動態環境下的結構行為與自然頻率分布。分析模型採用三種不同程度的幾何簡化策略，並針對粗細網格進行比較，探討簡化模型對頻率與加速度響應之影響。模擬結果顯示，本機構於三軸方向第一模態自然頻率均高於下限標準，且隨機振動應力反應均落於材料容許範圍內，結構安全裕度也滿足發射要求。進一步與實際振動實驗數據比對後發現，儘管模擬與實驗結果間存在一定落差，但整體自然頻率與振型分布具有一定程度的關聯性，足以作為設計初期之結構評估依據。本研究最終驗證了無動力展開機構的強度足以滿足發射商需求，也確認了簡化模型於立方衛星結構設計初期的重要性，並針對模態預測與隨機振動行為提供分析流程與誤差探討，為未來發展應用於立方衛星的無動力展開機構提供可行參考。

This study presents the design and validation of a passive deployment mechanism for CubeSats, inspired by NASA's Deployable Composite Booms (DCB). The mechanism uses a CFRP boom with a lip-shaped cross-section to achieve high bending and torsional stiffness. Deployment is triggered via a burn wire system, utilizing stored elastic energy without active actuators, offering a lightweight and reliable solution.
To ensure structural safety under launch conditions, modal and random vibration analyses were performed based on the SpaceX Falcon Payload User's Guide. Six geometric simplification strategies and mesh resolutions were compared. Results showed that the first natural frequencies exceeded the required limits and stress responses were within material tolerance. While some discrepancies with experimental results were noted, key trends aligned, validating the use of simplified models in early design stages.

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