隨著微型衛星任務複雜度與日俱增，姿態控制系統 ( ADCS ) 於入軌初期 ( LEOP ) 階段之穩定性與快速應變能力，對任務之存活至關重要。本研究以 SCION-X 12U 衛星任務為背景，旨在解決微型衛星於此關鍵階段所面臨之高風險系統整合挑戰。在星載電腦 ( OBC ) 與商規 ADCS 模組之整合過程中，本研究指出地面的硬體在環 ( HIL ) 測試雖具重要性，但受限於物理設備極限，無法完全復現真實太空之複雜環境與干擾。儘管如此，透過嚴謹的 Flat-Sat 與介面通聯測試，團隊仍成功發掘並防堵數項危及任務存活之關鍵硬體與通訊隱患。 基於對地面驗證侷限性的深刻認知，為此，本研究直接於狀態機之應用層中導入容錯保底邏輯，利用區間比例容錯機制動態過濾異常雜訊，並設定上限次數退守機制執行系統停損。此設計確保了衛星在面臨無法預測之擾動時，能及時中斷惡性循環並退回安全姿態，優先確保系統基礎生存能力與正電力平衡。;As the complexity of microsatellite missions continues to grow， the stability and rapid response capabilities of the Attitude Determination and Control System ( ADCS ) during the Launch and Early Orbit Phase ( LEOP ) become paramount to mission survival. Set against the background of the SCION-X 12U satellite mission， this study aims to address the high-risk system integration challenges faced by microsatellites during this critical stage. During the integration of the On-Board Computer ( OBC ) and commercial-off-the-shelf ( COTS ) ADCS modules， this study notes that while ground-based Hardware-in-the-Loop ( HIL ) testing is critical， physical equipment limitations prevent it from fully replicating the complex environments and disturbances of actual space. Nevertheless， through rigorous Flat-Sat and interface communication testing， the team successfully identified and mitigated several critical hardware and communication vulnerabilities that could jeopardize mission survival. Driven by a profound awareness of these ground validation limitations， this study directly implements fault-tolerant failsafe logic within the application layer of the state machine. It utilizes an interval-proportional fault-tolerance mechanism to dynamically filter anomalous noise， while establishing a maximum-retry fallback mechanism to mitigate system losses. This design ensures that when facing unpredictable disturbances， the satellite can promptly interrupt adverse cycles and retreat to a safe attitude， prioritizing basic system survivability and a positive power balance.
