本研究旨在探討珍珠號（Propagation Experiment using Kurz-Above-band Radio in Low Earth Orbit， PEARL）系列立方衛星之結構設計、分析、製造與組裝流程。此次研製之系 列型號包含 PEARL-1A 與 PEARL-1B 兩枚立方衛星。兩者皆搭載由瑞安電資股份有 限公司（RAiTEK）與工業技術研究院（Industrial Technology Research Institute， ITRI）共 同研發之 K/Ka 頻段通訊實驗酬載（K/Ka-band Communication Payload， ISL）、國立中央 大學太空酬載實驗室研製之小型電漿體層探測儀（Compact Ionosphere Probe， CIP）科學 酬載，以及由國家原子能研究院（National Atomic Research Institute， NARI）與鋐泰光電 股份有限公司（ET SPACE POWER INC）共同開發之太陽能電池實驗模組（Payload Solar Cell， PSC）。此外，本系列衛星搭載整合式相機模組。 由於本系列衛星採用 EXO Launch 所開發之 NovaPODS 作為發射彈射筒，因此在 設計階段必須符合 EXO Launch NovaPODS 之介面尺寸、外型限制與相關規範。另一方 面，立方衛星內部空間有限，為提升配置效率並最佳化整體結構整合度，設計階段也需 同時考量空間使用率、重心位置與組裝可行性等因素。在製造方面，工程體加工階段使 用 Autodesk Fusion 360 CAM 進行加工路徑編寫，並以 Datron Neo 三軸 CNC 進行加 工。工程體製作完成後，經三次元量床量測確認尺寸無誤，再進一步製造飛行體，飛行 體工件需進行表面處理。針對上述需求，本研究後續配合應力分析與震動分析，以驗證 結構可靠性。 在組裝方面，由於立方衛星體積較小且內部配置緊湊，因此在線材尺寸、材料、接 頭形式與線長規劃上皆需進行完整考量，以確保系統整合、維修性與可靠度。同時，組 裝流程須依據前期多次測試與修正所累積之經驗，建立最佳化組裝步驟，以提升組裝效 率與品質。;This study aims to explore the structural design， analysis， fabrication， and assembly of the PEARL (Propagation Experiment using Kurz-Above-band Radio in Low Earth Orbit) CubeSat series. The series developed in this work comprises two CubeSats， PEARL-1A and PEARL-1B. Both satellites are equipped with the K/Ka-band Communication Payload Inter Satellite Link (ISL)， developed by RAiTEK Co.， Ltd. and the Industrial Technology Research Institute (ITRI); the Compact Ionosphere Probe (CIP)， a scientific payload developed by the Space Payload Laboratory of National Central University; and the Payload Solar Cell (PSC) experimental module， jointly developed with the National Atomic Research Institute (NARI) and ET SPACE POWER INC. In addition， the satellite series carries an integrated camera module. Because this satellite series uses the EXO Launch NovaPODS deployer， the design phase must comply with the EXO Launch NovaPODS interface dimensions， external geometry constraints， and related specifications. Given the limited internal volume of CubeSats， the design process must also account for space utilization， center of gravity (CG)， and assembly feasibility to improve layout efficiency and optimize overall structural integration. In manufacturing， the engineering model was programmed in Autodesk Fusion 360 CAM and machined on a Datron Neo three-axis CNC machine. After the engineering model was completed and verified， the flight model was manufactured， and surface treatment was applied to the flight components. To meet the requirements， subsequent stress and vibration analyses will be conducted to verify structural reliability. Regarding assembly， because CubeSats are compact and their internal configurations are highly constrained， comprehensive planning of wire sizes， materials， connectors， and cable lengths is required to ensure system integration， maintainability， and reliability. Furthermore， the assembly process must follow an optimized procedure established through repeated testing and iterative modifications during the early development stages to improve both assembly efficiency and quality.
