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박일경(Illkyung Park),이승규(Seunggyu Lee),기영중(Youngjung Kee) 대한기계학회 2023 대한기계학회 춘추학술대회 Vol.2023 No.11
The eVTOL aircraft is a next-generation transportation system that is being developed into manned/unmanned aircraft of various configurations with electric powered vertical take-off and landing capability presently. It has not only vertical take-off and landing, but also fixed-wing horizontal flight maneuver performance by applying distributed propulstion system, so it is possible to be operated in verical take-off and landing port and move to the destination in a short time. For eVTOL aircraft with such various flight performance, the load acting on the airframe during vertical take-off and landing and horizontal flight must be properly considered and applied on the development process. This study was carried out for load analysis of a lift-cruise type eVTOL aircraft for numanned cargo transportation. This proceeding presented a method to effectively calculate the flight loads for vertical take-off and landing and fixed wing horizontal flight mode, and the ground load during landing procedure through the landing gear.
후륜형 삼 점식 복합재 착륙장치가 적용된 무인헬기 착륙하중 및 착륙장치 사이징 연구
박일경(Illkyung Park),김덕관(Deogkan Kim),김승호(Seungho Kim) 항공우주시스템공학회 2019 항공우주시스템공학회 학술대회 발표집 Vol.2019 No.5
본 연구에서는 후륜 착륙장치를 갖는 삼 점식 착륙장치가 적용된 소형 무인헬기의 착륙하중 산출을 위한 규정 검토 및 적용과 이를 기반으로 착륙장치 구조 사이징 해석이 수행되었다. 무인헬기 착륙하중 산출에는 CS-LURS 및 FAR 27.497 규정을 적용하였다. 본 연구에 적용된 착륙장치는 복합재 구조로 구성되었으며, Structural spring 방식의 완충장치가 적용되었으며, 기하학적 비선형 효과를 고려하기 위한 비선형 유한요소해석 기법을 적용한 착륙장치 구조 사이징을 수행하였다.
주름진 복합재 충돌에너지 흡수 부재 압축파손 해석 기법 연구
박일경(Illkyung Park),김성준(Sungjoon Kim),김태욱(Tae-uk Kim) 대한기계학회 2017 대한기계학회 춘추학술대회 Vol.2017 No.11
This paper presents a precise and cost effective numerical simulation approach of a corrugated composite crush web axial crushing that can be used in the design phase. Intra-laminar and inter-laminar failures of composite laminates were considered to improve the accuracy of a simulation and the complete laminate properties of laminate was adopted to reduce computation time. To validate the proposed simulation approach, specimens were fabricated and experimental study was carried out. The results of the simulation showed that very good agreement with the experimental data quantitatively and qualitatively and a significant decrease in the computation time.
이무형,박일경,김성준,안석민,Lee, Muhyoung,Park, Illkyung,Kim, Sungjoon,Ahn, Sukmin 항공우주시스템공학회 2012 항공우주시스템공학회지 Vol.6 No.2
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.