지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- 박재현
- 발행연도
- 2021
- 저작권
- 경상대학교 논문은 저작권에 의해 보호받습니다.
이용수3
이 논문의 연구 히스토리 (2)
- 이 논문의 후속연구가 궁금하신가요?
- 연관 학술논문 또는 학술발표를 통해 보다 발전된 연구결과를 확인하실 수 있습니다.
- 이 논문의 연구 히스토리 확인하기
초록· 키워드
오류제보하기
Fatigue is a major issue in the operational safety of aircraft. Some of the accidents occurring in the world are due to the loss of aircraft function due to fatigue accumulation in the Principal Structural Element (PSE). Especially, unexpected initial flaw causes aircraft accidents, and the issue has been steadily emerging in
recent years. To prevent this accidents, the Federal Aviation Administration (FAA) has established §29.571.
In this paper, we introduce a process of research processes that performed fatigue evaluation in order to apply the component to rotorcraft under development in Korea, and introduce results of fatigue evaluation through analysis and test. Fatigue analysis and test were performed to verify the fatigue tolerance mentioned
in the FAR §29.571 requirements, and test were performed after artificially forming initial defects. A method of performing a spectrum fatigue test with the initial defect formed was devised and performed. Through this, the service life of the component of the rotorcraft was verified. These processes and results were reviewed by airworthiness agency in Korea, and as a result, it was confirmed that the devised method was appropriate as a fatigue evaluation method.
recent years. To prevent this accidents, the Federal Aviation Administration (FAA) has established §29.571.
In this paper, we introduce a process of research processes that performed fatigue evaluation in order to apply the component to rotorcraft under development in Korea, and introduce results of fatigue evaluation through analysis and test. Fatigue analysis and test were performed to verify the fatigue tolerance mentioned
in the FAR §29.571 requirements, and test were performed after artificially forming initial defects. A method of performing a spectrum fatigue test with the initial defect formed was devised and performed. Through this, the service life of the component of the rotorcraft was verified. These processes and results were reviewed by airworthiness agency in Korea, and as a result, it was confirmed that the devised method was appropriate as a fatigue evaluation method.
목차
I. 서 론 61.1. 소개 61.2. 회전익 항공기 피로 감항인증 (29.571) 61.3. 적용 사례 101.4. 연구배경 11II. 본 론 122.1. 적용 개념 122.2. 피로 평가 대상 구성품 132.2.1. 구성품 형상 132.2.2. 구성품 초기 결함 (Initial Flaw) 142.2.3. 구성품 하중 스펙트럼 152.3. 피로 평가 방안 연구 152.3.1. 기존 평가 방법 152.3.2. 피로시험 평가방안 도출 172.3.3. 평가 방법 비교 172.4. 해석 192.4.1. 응력확대계수 해석 192.5. 시험 222.5.1. 초기 결함 도입 222.5.2. 시험 준비 242.5.3. 시험 수행 242.5.4. 시험 중 결함 성장 확인 252.5.5. 시험 결과 282.6. 구성품 피로 감항요건 충족확인 28III. 결 론 35
최근 본 자료
댓글(0)
0