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회전익 항공기용 복합재 내추락 하부동체 구조 개발 및 검증
박일경(Ill Kyung Park),임주섭(Joo Sup Lim),김성준(Sung Joon Kim),김태욱(Tae-Uk Kim) 한국항공우주학회 2018 韓國航空宇宙學會誌 Vol.46 No.1
회전익 항공기는 수직이착륙, 제자리비행 특성으로 일반적으로 고정익 항공기에 비해 높은 내추락 기준이 적용된다. 최근 고효율 친환경 운송시스템에 대한 요구의 증가와 더불어 항공기 구조재료로 복합재료의 적용이 증가하는 추세이다. 그러나 외부 충격, 충돌에 취약한 복합재료의 특성으로 인해 복합재 구조의 내추락 안전성 입증에 대한 요구 또한 증가하고 있다. 본 연구는 회전익항공기 적용을 위한 복합재 내추락 하부동체 구조 개념을 도출하고 이에 대한 검증을 목적으로 수행되었다. 내추락 하부동체 구조 개념 생성을 위해 기술 실증용 헬리콥터 개념설계 및 충돌에너지 흡수 요구도 산출을 수행하였으며, 복합재 충돌에너지 흡수 구조 설계 및 성능 검증을 수행하였다. 최종적으로 복합재 내추락 하부동체구조 시제 제작 및 자유낙하시험을 수행하였다. 시험 결과 분석을 통해 탑승자 생존성 확보를 위한 내추락 안전성 기준에 부합하는 결과를 확인할 수 있었다. Rotorcrafts have more severe crashworthiness conditions than fixed wing aircraft owing to VTOL and hovering. Recently, with the increasing demand for highly efficient transportation system, application of composite materials to aircraft structures is increasing. However, due to the characteristics of composite materials that are susceptible to impact and crash, demand to prove the crashworthiness of composite structures is also increasing. The purpose of present study is to derive the structural concept of composite subfloor for rotorcrafts and verify it. In order to design a crashworthy composite subfloor, the conceptual design of the testbed helicopter for the demonstration and the derivation of energy absorbing requirement were carried out, and the composite energy absorber was designed and verified. Finally, the testbed for the demonstration of a crashworthy composite structure was fabricated, and performed free drop test. It was confirmed that the test results meet the criteria for ensuring occupant survivability.
우대현(Dae-Hyun Woo),임주섭(Joo-Sup Lim),김성찬(Sung-Chan Kim),신정우(Jeong-Woo Shin),김태욱(Tae-Uk Kim),김승호(Seung-Ho Kim) 대한기계학회 2014 대한기계학회 춘추학술대회 Vol.2014 No.11
Human Powered Aircraft (HPA) should be light in weight and have high efficiency because power source of propulsion is human muscles. Airframe structure takes up most of empty weight of aircraft, so weight reduction of structure is very important issue for HPA. In this paper, design/analysis for ultra light weight structure of the HPA developed by Korea Aerospace Research Institute (KARI) is explained briefly. Structural analysis is conducted for main wing sizing.
신정우 ( Jeong Woo Shin ),우대현 ( Dae Hyun Woo ),박일경 ( Ill Kyung Park ),이무형 ( Mu Hyoung Lee ),임주섭 ( Joo Sup Lim ),박상욱 ( Sang Wook Park ),김성준 ( Sung Joon Kim ),안석민 ( Seok Min Ahn ) 한국항공운항학회 2013 한국항공운항학회지 Vol.21 No.1
Human Powered Aircraft (HPA) should be light in weight and have high efficiency because power source of propulsion is human muscles. Airframe structure takes up most of empty weight of aircraft, so weight reduction of structure is very important issue for HPA. In this paper, design/analysis/test procedures for ultra light weight structure of the HPA developed by Korea Aerospace Research Institute (KARI) are explained briefly. Structural design is conducted through case studies on HPA in the USA and Japan. Loads analysis is performed to calculate design loads which is needed for structural design and analysis. Structural analysis is conducted for structure sizing. Static strength test of main wing spar which is primary structure of wing is performed to verify structural integrity.