本文首先對立方衛星結構與設計規格進行探討，而後對應用於立方衛星的展開機構酬載進行文獻回顧與設計規格探討，最終決定研發適用於立方衛星1.2U空間之無動力展開機構酬載，並選擇使用SolidWorks設計此酬載。此酬載的功能為增加衛星的阻力面積，使衛星在任務結束後，能更快速地返回大氣層燒毀，減少近地軌道（LEO）區域中太空碎片的數量，達成太空環境的永續發展。完成酬載設計後，使用法國國家太空研究中心研發之STELA軟體進行立方衛星軌道分析，以驗證此酬載的可行性與功能性，最終也會把使用SolidWorks繪製設計出來的零件交由加工廠進行加工並實際組裝，在組裝後也會分別對工程體與飛行體進行數次環境測試（振動測試與真空熱循環測試），並且在環境測試結束後也對酬載進行了功能性測試，為實務導向之研究。此研究範圍涵蓋甚廣，從機械設計、模擬分析、尋找適用於航太產業與真空環境使用之零件、金屬加工與複合材料加工至環境測試與整合組裝，最終成功將此酬載遞交至智探太空公司，並由智探太空公司將此酬載組裝進Lilium-3立方衛星中。

With the flourishing development of the CubeSat industry, an increasing number of small CubeSats are being launched into space. Following the completion of their missions, these satellites often require decades to gradually decrease their orbital altitude due to atmospheric drag and earth gravity, eventually burning up in the atmosphere. Consequently, how to manage the amount of space debris in the Low Earth Orbit (LEO) region in the coming decades has become a challenging issue. Against the backdrop of increasing space debris, it is imperative to develop methods that enable these satellites to deorbit and re-enter the atmosphere more rapidly for incineration. This has led numerous researches of drag deorbit devices. These devices, deployed at the end of a satellite's mission, increase the drag area to achieve faster deorbit and atmospheric burn-up, thereby reducing space debris.
This paper explores the design of an unpowered deployable mechanism　payload utilizing deployable CFRP boom, applicable within a 1.2U CubeSat volume. In practice, this payload is intended for use in the Lilium-3 CubeSat for deorbiting. This unpowered deployable mechanism does not require any motor or control to deploy, which can reduce system complexity. Once fully deployed, the mechanism provides the CubeSat with a larger drag area, enabling satellites to deorbit more quickly, thereby reducing space debris and contributing to the sustainable development of the space environment.

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