인문학
사회과학
자연과학
공학
의약학
농수해양학
예술체육학
복합학
DBpia AI
AI 에이전트
AI 아이디어
AI 리더
AI 뷰어
Citeasy
크롬 서지관리 다운로드
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
- 학술대회자료
- 저자정보
- 발행연도
- 2001.8
- 수록면
- 285 - 292 (8page)
이용수
초록· 키워드
Economical life estimated about aircraft structure should be known to carry out the structure force management of aircraft. Through it schedule and method of inspection, maintenance and repair being used during operation of aircraft are determined.
When the main items of aircraft structure are failed, they may affect directly safety of aircraft and aircraft fracture and the main items of aircraft structure are called Primary Structure Element(PSE) or Fatigue/Fracture Critical Location(FCL).
The selection of FCL of aircraft structure should be carried out through detailed review such as stress analysis, fatigue analysis, fatigue test, service experience and so on. When FCL is selected, they should be considered with minimum margin of safety, location with tension/shear or stress concentration and so on. Therefore the strength, stiffness and the estimation of fatigue life of them should be carried out necessarily.
It was carried out finite element analysis about FCL of small aircraft using MSC.Patran and MSC.Nastran. Also, fatigue analysis and life estimation was performed using the result of stress analysis, material data and load history. For this analysis, MSC.Fatigue was used. In this report, the stress and fatigue analysis of Front Pick_Up Lug connected Main Wing and Fuselage by a rod was shown. Therefore, we can know the static and fatigue safety of design requirements, the technical approach method of load and boundary condition from the results of analysis.
상세정보 수정요청해당 페이지 내 제목·저자·목차·페이지When the main items of aircraft structure are failed, they may affect directly safety of aircraft and aircraft fracture and the main items of aircraft structure are called Primary Structure Element(PSE) or Fatigue/Fracture Critical Location(FCL).
The selection of FCL of aircraft structure should be carried out through detailed review such as stress analysis, fatigue analysis, fatigue test, service experience and so on. When FCL is selected, they should be considered with minimum margin of safety, location with tension/shear or stress concentration and so on. Therefore the strength, stiffness and the estimation of fatigue life of them should be carried out necessarily.
It was carried out finite element analysis about FCL of small aircraft using MSC.Patran and MSC.Nastran. Also, fatigue analysis and life estimation was performed using the result of stress analysis, material data and load history. For this analysis, MSC.Fatigue was used. In this report, the stress and fatigue analysis of Front Pick_Up Lug connected Main Wing and Fuselage by a rod was shown. Therefore, we can know the static and fatigue safety of design requirements, the technical approach method of load and boundary condition from the results of analysis.
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목차
- Abstract
- 1. Introduction
- 2. Problem Definition
- 3. Analysis
- 4. Discussion
- 5. Conclusions
- 6. Reference List Guide
참고문헌
참고문헌 신청최근 본 자료
UCI(KEPA) : I410-ECN-0101-2010-550-002784785
