本論文以 SCION-X 鯨鯊號 12U 立方衛星電力次系統（Electrical Power Subsystem，EPS） 為研究對象，系統性地記錄並論述從需求制定、系統架構設計、電路實作、功能測試 驗證到系統整合與環境測試的完整工程過程。 SCION-X 為國立中央大學太空科學與工程學系（NCU-SSE）研製之 12U 立方衛星， 承繼前代 IDEASSat（3U）任務之工程積累，並針對在軌異常教訓進行改良設計。EPS 以多匯流排架構為核心，同時維護 3.3 V、5 V_1、5 V_2、7 V 及 12 V 五條獨立匯流排， 以滿足通訊、姿態控制、資料處理與科學酬載等各次系統之差異化電力需求。 電力來源方面，五片太陽能板（機體一片、可展開四片）共安裝 53 顆太陽能電 池，理論最大發電功率達 56.43 W；電池組採用 12 顆 NCR18650GA 鋰電池，標稱容 量 10.05 Ah（144.72 Wh）。電源調節端採用最大功率點追蹤（MPPT）充電電路，搭配 DC-DC 降壓與升降壓轉換器實現多電壓穩壓輸出。整體 EPS 共由 14 塊印刷電路板組 成，各板透過標準化連接器互連，構成具完整功能分工的多板模組化架構。 針對 IDEASSat 在軌期間因單粒子效應（SEE）導致反向 Schmitt 觸發器失效、重啟 功能喪失之教訓，SCION-X EPS 改採純被動 RC 延遲電路實現重啟功能。實測結果顯 示，在輸入電壓 16.8 V 條件下延遲 3.299 s、在 12.0 V 條件下延遲 5.759 s，均超過需求 下限 2.5 s，從根本上消除了 SEE 導致主動元件失效之風險，提升 EPS 在輻射環境下的 長期可靠性。 EPS 飛行模型（FM）共執行 14 項測試，涵蓋 11 項功能測試與 3 項環境測試（輻射 測試、熱真空測試、振動測試），全數通過。SCION-X 鯨鯊號目前已完成所有地面驗證 測試並遞交火箭發射商，等待入軌部署。;This thesis presents the engineering development of the Electrical Power Subsystem (EPS) for SCION-X， a 12U CubeSat developed by the Department of Space Science and Engineering， National Central University (NCU-SSE). The work systematically documents the complete engineering process， from requirement definition and system architecture design， through circuit implementation and functional verification testing， to system integration and environmental testing. SCION-X builds upon the engineering heritage of the earlier IDEASSat (3U) mission and incorporates design improvements derived from lessons learned during its on-orbit operation. The EPS adopts a multi-bus architecture， simultaneously maintaining five independent power buses at 3.3 V， 5 V_1， 5 V_2， 7 V， and 12 V to satisfy the differentiated power demands of the communication， attitude determination and control， data handling， and payload subsystems. On the power generation side， five solar panels (one body-mounted and four deployable) accommodate a total of 53 solar cells， providing a theoretical maximum generation power of 56.43 W. The battery pack consists of twelve NCR18650GA lithium-ion cells with a nominal capacity of 10.05 Ah (144.72 Wh). Power conditioning is achieved through a Maximum Power Point Tracking (MPPT) charging circuit， combined with buck and buck-boost DC-DC converters to provide regulated multi-voltage outputs. The complete EPS comprises 14 printed circuit boards interconnected through standardized connectors， forming a modular architecture with clearly delineated functional partitioning. To address the lesson learned from IDEASSat， whose on-orbit Single Event Effect (SEE)induced inverting Schmitt trigger failure resulted in loss of the reset function， the SCION-X EPS adopts a purely passive RC-delay circuit to implement the reset function. Test results show reset delays of 3.299 s at an input voltage of 16.8 V and 5.759 s at 12.0 V， both exceeding the required minimum of 2.5 s， fundamentally eliminating the risk of active-component failure caused by SEE and improving the long-term reliability of the EPS in the radiation environment. The EPS Flight Model (FM) underwent a total of 14 tests， comprising 11 functional tests and 3 environmental tests (radiation， thermal vacuum， and vibration testing)， all of which were passed successfully. The SCION-X CubeSat has completed all ground verification testing and has been delivered to the launch provider， awaiting deployment into orbit.
