국내개발 군용항공기 MIL-HDBK-516C의 CS&S 안전필수소프트웨어 감항인증 연구 = Study on the CS&S Safety Critical Software Airworthiness Certification of Domestic Developed Military Aircraft MIL-HDBK-516C

다국어 초록 (Multilingual Abstract)

Along with the exponential development of the information communication technology, increasing number of advanced aircraft‘s including F-35 are adopting software.
Main function of systems, ranging from flight control, mission, and weapon management to aviation, communication, sensor and engine are all controlled by software.
As the integrity of software is directly related with the safety, compliance to the verified development process and military standard is strictly required from the planning stage.
If there's an issue with aircraft software, it might lead to a loss of both aircraft and life.
Therefore securing safety of software is significant.
Thus, the SCF(safety critical function) related software which are adopted on military aircraft like fighters to assure safety, is designated as SSE(safety support element), and are applied to more stringent development process.
Therefore, it is essential to clearly identify software's safety support element at the early stage of aircraft development, and this is critical part in airworthiness certification.
The standard for airworthiness certification of domestically developed military aircraft software is DAPA's Airworthiness Certification Standard Part I, which is drafted based on US's MIL-HDBK-516C.
However, there are unclear part as the introduction of standards was relatively recent, and the specific identification standard is not standardized yet.
Hence, lack of past cases is becoming an issue during airworthiness certification process.
Following paper researched analysis model of aircraft-adopted software's safety critical function through an analysis of US Airworthiness Circular AC-17-01.
Thus, based on the relevant studies, the paper verified the suitability of the analysis model by adopting it to an actual development project of a military aircraft system.
The paper produced the certifying evidence that proves airworthiness and developed airworthiness certification methodology of aircraft‘s that will be developed in future.

목차 (Table of Contents)

• I. 서 론 1
• 1. 연구배경 1
• 2. 논문의 구성 4
• II. CS&S 감항인증 개요 5
• 1. 군용항공기의 항공 소프트웨어 개발 프로세스 5
• 2. 방위사업청 무기체계 소프트웨어 개발 및 관리 매뉴얼 11
• 3. 민·군 감항인증의 역사 및 표준감항인증기준(MIL-HDBK-516C) 15
• 4. CS&S (컴퓨터시스템과 소프트웨어) 24
• 5. 미 공군 감항성 회람 AC-17-01 31
• 6. RTCA DO-178 37
• 7. RTCA DO-254 40
• 8. MIL-HDBK-516C CS&S 충족을 위한 시스템안전 프로세스 43
• Ⅲ. MIL-HDBK-516C CS&S 감항인증 49
• 1. 국내 개발항공기에 대한 MIL-HDBK-516C CS&S 적용시 문제점 고찰 49
• 2. MIL-HDBK-516C CS&S의 안전지원요소 개념 및 기준 분석 51
• 3. 미 공군 감항성 회람(AC-17-01) 분석 54
• Ⅳ. MIL-HDBK-516C CS&S SSE 식별 56
• 1. 안전지원요소 식별을 위한 상세 기준 및 Worksheet 개발 56
• 2. 분석 모델을 이용한 안전지원요소 식별 과정 62
• 1) 안전필수기능의 분석 단계 62
• 2) 안전필수기능경로분석 단계 66
• 3) 안전필수기능스레드분석 Worksheet 분석 단계 73
• Ⅴ. 안전지원요소 식별방법에 대한 타당성검증 75
• 1. 안전지원요소 식별 방법에 대한 실제 검증 75
• 2. 감항인증을 위한 입증 결과 75
• Ⅵ. 결론 82
• 1. 연구결과요약 82
• 2. 연구의 한계와 추후 연구를 위한 시사점 83
• 참고문헌 84
• 부 록 89