小型飛行運輸系統(SATS)的發展在短程的私人飛行扮演相當重要角色，在911之後將用來彌補航空運輸的不足。CAN bus系統為本實驗室專為SATS所使用的小型飛機提供即時資料交換與整合的航電系統，本論文介紹各種不同硬體設計架構的CAN bus系統以及驗證其系統可靠度。本論文以可靠度理論及CAN bus系統性能為主要研究架構，在研究中蒐集各項設計產品資訊，運用美國軍用標準“MIL-HDBK-217F”，以可靠度分析軟體RELEX預估失效率，將兩種電路架構的系統可靠度與平均將系統可靠度與MTBF值依可靠度模式計算出來。其中以選擇器所架構的雙匯流排系統可提供較高的MTBF指數，並且有較簡單和便宜的硬體設計。在系統驗證方面，分別做了錯誤率測試、傳輸延遲時間測試以及匯流排負載測試。三項實驗結果進一步證實以混合資料傳輸介面的CAN bus 韌體設計可以滿足即時資料傳輸協定，提供SATS一套高可靠度的航電系統。

The Small Aircraft Transportation System (SATS) is placed importance on short ranges and private transportations to make up some shortage in air transportation system after 911. A new and brief data bus system, such as CAN (Controller Area Network) bus system, to interconnect and integrate avionics system is required for SATS development. This thesis presents prototype fabrication on different configurations and verifies the reliability of the developing CAN bus system. Based on this study, the reliability theorem and the performance of CAN bus system are concerned. The reliability prediction software “RELEX” is used to predict the failure rate of each new circuit designs. The reliability index value and MTBF of each design products can be calculated with reliability math model using the US Military Standard “MIL-HDBK-217F”. The MTBF of dual bus system is greatly improved by hardware design in bus selector and memory mapping. From this analysis, the bus selector dual CAN system provides high reliability assurance and the cost and complexity of hardware are better than the memory mapping dual CAN system. In system verifications, the analytical experiments on failure rate test, transmitting delay time test and bus load rate test are provided to prove that the firmware design of hybrid data transfer interface (HDTI) in CAN bus system can satisfy the real time transmission protocol and provide a high reliability avionic system on SATS.

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