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KC-100 엔진 마운트 구조물의 정적 구조 해석 및 시험
이무형(Mu-hyoung Lee),박일경(Ill-kyoung Park),김성준(Sung-jun Kim),안석민(Suk-min Ahn) 대한기계학회 2011 대한기계학회 춘추학술대회 Vol.2011 No.10
KC-100 is composite small aircraft which developed for BASA(Bilateral Aviation Safety Agreement) agreement and making inroads into the North America market. Engine Mount Structural(EMS) installed in KC-100 takes charge of supporting the Engine and transmitting the loads of Engine and nose landing gear. For analyzing the EMS, Linear gap elements, RBE 2 elements and MPC are used to realize the bulkhead boundary condition, contact condition between Engine and EMS, and appropriate the load condition. Load analysis FE model is used the EMS design tool, detail FE model reflected the weld joint section is used to analyze the stress distribution. Also, static test is performed to verify the structural analysis results. The comparing the results between the structural analysis results and test results ascertain the high accuracy, the process of EMS structural analysis and test may help the design the small aircraft EMS.
論文(논문) : 소형 항공기 엔진 마운트 구조물의 피로 건전성 평가
이무형 ( Mu Hyoung Lee ),박일경 ( Ill Kyoung Park ),김성준 ( Sung Joon Kim ),안석민 ( Seok Min Ahn ) 한국항공운항학회 2011 한국항공운항학회지 Vol.19 No.4
The estimation of fatigue integrity is very important for aerospace structures such as engine mount strut. The reason is that the fatigue integrity is essential analysis process to establish the structural stability in aerospace field. Therefore, in this paper, the process of fatigue analysis and test was performed for engine mount strut to prove the structural fatigue integrity. First of all, the fatigue load spectrum is constructed by considering the small aircraft operating condition. Fatigue analysis is done for the cluster near the welding zone which may have F.C.L.(fracture critical location). The fatigue life of engine mount strut was estimated by the Miner`s rule which is the damage summation method. Finally, Fatigue test is performed to verify the fatigue integrity. The estimation process of fatigue integrity for engine mount strut of small aircraft may help the design.
헬리콥터 무베이링 메인 로터 허브 시스템의 구조 건전성에 관한 연구
이무형 ( Mu Hyoung Lee ),박일경 ( Ill Kyoung Park ),김성준 ( Sung Joon Kim ),황인희 ( In Hee Hwang ),김태주 ( Tae Joo Kim ) 한국항공운항학회 2012 한국항공운항학회지 Vol.20 No.4
Rotor system is a very important part which produce lift, thrust and control force in helicopter. Component of rotor system must have structural integrity for applied load. The estimation of structural integrity is regarded greatly as important in aerospace field. In this study, the process of structural analysis performed for bearingless main rotor system of helicopter. The composite flexbeam and torque tube of bearingless main rotor are very thick, so 3D layered soild elements of MSC.PATRAN were used to get the finite element analysis results. To estimate structural integrity, non-linear static analysis considering geometric non-linearity is performed. In addition, detailed finete element analysis and non-linear static analysis are performed to consider the stress concentration for fitting effect and contact surface. The estimation process of structural integrity for bearingless main rotor system of helicopter may help the design.