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우대현,이영신,김흥태,전상배,이규섭,강국정,Woo, Dae-Hyun,Lee, Young-Shin,Kim, Heung-Tae,Jun, Sang-Bae,Lee, Kyu-Sub,Kang, Kuk-Jeong 한국군사과학기술학회 2012 한국군사과학기술학회지 Vol.15 No.4
In the soft recoil system, the recoiling parts are initially accelerated to the forward direction. These parts are returned to original position by the firing with intial acceleration speed. The latch of the soft recoil system keeps the high impact load when the recoil parts were recuperated to the forward direction. In this study, the latch of soft recoil system using the ADAMS program was analyzed. The optimal operation parameters were found that max. angle and expansion length of latch was $50^{\circ}$, 180 mm respectively. Dynamic structural analyses of model cases were performed using finite element model. The max. stress and deflection of latch was 230 MPa and 0.45 mm respectively.
우대현,신정우,박일경,이무형,임주섭,박상욱,김성준,안석민 한국항공우주학회 2013 한국항공우주학회 학술발표회 논문집 Vol.2013 No.4
인간동력항공기는 사람의 힘을 동력으로 하기 때문에 경량화 및 고효율이어야 한다. 항공기의 중량의 가장 많은 부분은 구조부분이며, 인력항공기의 구조 경량화는 매우 중요한 문제이다. 본 논문에서는 한국항공우주연구원에서 개발한 인간동력항공기의 경량구조에 대한 설계/해석에 대해 간락하게 설명하고 있다. 인간동력항공기의 구조 설계는 미국과 일본의 사례를 참고하여 수행하였다. 하중해석을 통해 구조설계 및 해석에 필요한 설계하중을 계산하였다. 구조해석을 통해 구조형상을 결정하였다. 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 design is conducted through cases 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.
우대현,이영신,Woo, Dae-Hyun,Lee, Young-Shin 한국군사과학기술학회 2012 한국군사과학기술학회지 Vol.15 No.3
The velocity response of stiffened rectangular plate under high velocity impact was studied. Numerical simulation was conducted on the stiffened plate with four stiffeners under various impact positions. Considered stiffener types were rib, I, hat and T stiffener. For the center impact position of I stiffened plate, the simulated residual velocity was 365.6 m/s with the initial projectile velocity 500 m/s. The reinforcing characteristic of I stiffened plate was excellent among four stiffeners.
우대현,박일경,신정우,박상욱,김성준,안석민 한국항공우주학회 2012 한국항공우주학회 학술발표회 논문집 Vol.2012 No.11
본 연구에서는 전기동력무인기의 프로펠러 블레이드에 대한 구조해석을 수행하였다. 전기동력무인기의 프로펠러 블레이드는 순항조건에서 구조 안정성을 만족하여야 한다. 또한, 경량화를 위해 카본/글라스 복합재료가 적용되었으며, 스킨 샌드위치 구조로 이루어지는 형태를 채택하였다. 구조 안전성을 평가하기 위하여 상용 유한 요소 해석 코드인 나스트란을 활용하여 구조해석을 수행하였다. In this study, structural analysis of the propeller blade for electric powered UAV. Propeller blade of electric powered UAV at cruise conditions shall meet the structural stability. The carbon/glass composite material was used for the skin sandwich structural type was adopted for improvement of lightness. In order to investigate the structural safety and stability, stress analysis was performed by finite element analysis code MSC. NASTRAN.
우대현,박일경,임주섭,김성준,김태욱 한국항공우주학회 2015 한국항공우주학회 학술발표회 논문집 Vol.2015 No.11
항공기 비상 착륙 시 충돌에너지의 효과적인 흡수는 탑승자의 생존 및 내추락 성능 향상을 위해 매우 주요한 요소이다. 비상 착륙시에 탑승자에게 전달되는 충돌에너지는 착륙장치, 동체, 좌석등에 의해 흡수 된다. 동체 하부 내추락성 설계를 위해 대표적인 기준문서는 MIL-STD-1290A가 있다. 본 연구를 통해 복합재 헬리콥터 동체 구조 내추락성 향상을 위한 Subfloor Tesbed의 구조 설계 및 시험 검증을 수행하였다. The effective energy absorbing is very important characteristic of aircraft for the enhancement of the survivability of occupant and aircraft crashworthiness when aircraft is under the emergency landing condition. The impact energy transmitted to occupants when the emergency landing condition is absorbed within a landing gear, airframe and seats. Representative crushworthiness requirement documents for airframe subfloor are MIL-STD-1290. This study was performed with structural design and test verification of the Subfloor Testbed for the development of a crashworthy composite helicopter fuselage structures.
우대현,박일경,임주섭,김성준,김태욱 한국항공우주학회 2015 한국항공우주학회 학술발표회 논문집 Vol.2015 No.4
항공기 비상 착륙 시 충돌에너지의 효과적인 흡수는 탑승자의 생존 및 내추락 성능 향상을 위해 매우 주요한 요소이다. 비상 착륙시에 탑승자에게 전달되는 충돌에너지는 착륙장치, 동체, 좌석등에 의해 흡수 된다. 동체 하부 내추락성 설계를 위해 대표적인 기준문서는 MIL-STD-1290가 있다. 본 연구는 동체 하부 구조물의 비상 착륙 수직방향 충돌 조건에 대한 설계를 수행하였다. 또, 주요 구조물인 Crush web과 Crucifrom Bracket을 기술하였다. The effective energy absorbing is very important characteristic of aircraft for the enhancement of the survivability of occupant and aircraft crashworthiness when aircraft is under the emergency landing condition. The impact energy transmitted to occupants when the emergency landing condition is absorbed within a landing gear, airframe and seats. Representative crushworthiness requirement documents for airframe subfloor are MIL-STD-1290. This study was designed to perform the emergency landing vertical crash condition of the fuselage structure. Also, describe the Crush web and Crucifrom Bracket of main structure.
우대현,임주섭,김성찬,이무형,신정우,김태욱,김승호 한국항공우주학회 2014 한국항공우주학회 학술발표회 논문집 Vol.2014 No.11
인간동력항공기는 사람의 힘을 동력으로 하기 때문에 경량화 및 고효율이어야 한다. 항공기의 중량의 가장 많은 부분은 구조부분이며, 인간동력항공기의 구조 경량화는 매우 중요한 문제이다. 본 논문에서는 한국항공우주연구원에서 개발한 인간동력항공기의 경량구조에 대한 설계/시험에 대해 간략하게 설명하고 있다. 주익 구조의 건정성을 검증하기 위해 주 스파의 정적구조시험을 수행하였다. 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/test for ultra light weight structure of the HPA developed by Korea Aerospace Research Institute (KARI) is explained briefly. Static strength test of main wing spar which is primary structure of wing is performed to verify structural integrity.
우대현(Dae-Hyun Woo),이영신(Young-Shin Lee),김흥태(Heung-Tae Kim),전상배(Sang-Bae Jun),이규섭(Kyu-Sub Lee),강국정(Kuk-Jeong Kang) 대한기계학회 2011 대한기계학회 춘추학술대회 Vol.2011 No.10
In the soft recoil system, the recoiling parts are initially accelerated to the forward direction and these return the original position by the firing when these reached the required level. The recoil force accelerated recoil part rearward, recuperator force return recoil part to the initial ratch position. The latch of the soft recoil system keeps the high impact load when the recoil parts were recuperated to the forward direction. In this study, The latch of soft recoil system using the ADAMS program was analyzed the operating mechanism and the values is that the Max. angle and expansion length is α = 50°, R = 180 mm respectively. After the latch was released to be recuperated, the dynamic analysis results against the impact load using LS-Dyna program were that the Max. stress and deflection of latch is 230MPa, 0.45mm respectively.
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.