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고강명(Kangmyung Ko),조수형(Su-Hyeocncng Cho),안철주(Chuljoo Ahn),이복원(Bokwon Lee) 한국추진공학회 2021 한국추진공학회 학술대회논문집 Vol.2021 No.5
항공기에 사용되는 터보샤프트엔진은 항공기 운용에 필요한 출력, 연료소모량과 같은 성능 요구도와 항공기 장착에 따른 크기 및 중량과 같은 형상 요구도를 충족시켜야 한다. 이를 위해 엔진 기본설계 단계에서 성능 요구도에 맞춘 최적의 설계점을 선정하여 사이클 해석을 수행하고, 엔진 성능 및 구성품 설계에 따른 해석결과와 연계하여 엔진 레이아웃을 구성한다. 본 연구에서는 엔진 기본설계 절차에 따른 1,000 마력급 터보샤프트엔진의 요구도 도출, 사이클 설계 및 레이아웃 설계 과정을 소개한다. Aero turbo-shaft engine should meet the requirement of performance and installation for aircraft, and the requirement contains power, fuel consumption, size and weight of the engine. In preliminary engine design process, design point definition and thermodynamic cycle design should be done, and engine layout also should be designed in consideration of engine performance and component design. In this study, the process of cycle and layout design as the preliminary design of 1000 shp class turbo-shaft engine is introduced.
고강명(KangMyung Ko),강승온(SeungOn Kang),김상훈(SangHun Kim),이동호(DongHo Lee),장용진(YongJin Chang),최원(Won Choi),황유상(YuSang Hwang),김철호(CheolHo Kim) 대한기계학회 2007 대한기계학회 춘추학술대회 Vol.2007 No.5
It is necessary a simple helicopter design and performance analysis program for a stage of helicopter conceptual design. To meet that needs, we have developed a program which is simply used to estimate helicopter configuration and performance. The program developed by this study is composed of Requirement, Mission profile Analysis, Size, Aerodynamic, Trim, Propulsion, Weight, and Performance modules, and each modules carry out operations for a given flight condition. In this study, we validate this analysis program in 9,500 lbs and 22,000 lbs helicopters and estimate design configuration and performance of 16,000 lb helicopter. And We can use this program to optimization process for Helicopter MDO framework.
P.I.A.n.O.를 이용한 개념설계 단계의 헬리콥터 신뢰성 기반 최적 설계
김상훈(Sanghun Kim),고강명(Kangmyung Ko),이동호(Dong-Ho Lee),최원(Won Choi),황유상(YuSang Hwang),김철호(CheolHo Kim) 대한기계학회 2008 대한기계학회 춘추학술대회 Vol.2008 No.5
There are many demands of helicopter for emergency transportation and forest fire suppression in Korea where has many mountains and islands. For this reason, many helicopters are used in Korea, and various situations are occurred in flight of helicopter. Therefore, it is important to optimize helicopter in the conceptual design simultaneously to consider operation uncertainties. In this study, robust design optimization was performed with helicopter conceptual design and performance analysis tool which used simple analysis methods and empirical equations. For the operational uncertainties, temperature of atmosphere and poor maintenance and drag increase by change of airfoil characteristics.