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
- 학술저널
- 저자정보
- 발행연도
- 2012.6
- 수록면
- 28 - 34 (7page)
이용수
초록· 키워드
오류제보하기
Structural integrity evaluation is important item in the aircraft certification. Recently, it is designed for limit load, material weakness about fatigue and corrosion, damage by bird strike in flight to evaluate structural integrity of aircraft. And static/fatigue analysis are performed to secure structural integrity, it was verified by static and fatigue tests. To evaluate the structural integrity of small aircraft tail, structural integrity was calculated by the finite element analysis. In the present study, finite element analysis are performed to pick out load cases in flight occurrence, and secure margin of safety to evaluate structural integrity of KC-100 tail unit. The proprieties of finite element analysis results are compared with the static structure test results. The estimation process of structural integrity for small aircraft tail may help the design.
목차
등록된 정보가 없습니다.
참고문헌 (6)
참고문헌 신청
Michael, Chun-yung,N. / 1997 / Airframe - Stress Analysis and Sizing / Hong Kong Conmilit Press LTD :14~26
Campbell, F.C. / 2006 / 'Manufacturing Technology for Aero Structural Materials / Elsevier :495~538
1968 / MIL-HDBK-23A, Structural Snadwich Compo -sites / Department of Defense
Stephen, W. / 1990 / Analysis of Sandwich Structure / ASM Handbook 21:308~320
2005 / AC 23-13A / Federal Aviation Admini stration
Campbell, F.C. / 2006 / 'Manufacturing Technology for Aero Structural Materials / Elsevier :495~538
1968 / MIL-HDBK-23A, Structural Snadwich Compo -sites / Department of Defense
Stephen, W. / 1990 / Analysis of Sandwich Structure / ASM Handbook 21:308~320
2005 / AC 23-13A / Federal Aviation Admini stration
이 논문의 저자 정보
최근 본 자료
댓글(0)
0
UCI(KEPA) : I410-ECN-0101-2022-558-001144102