http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
김동기,하성업,문일윤,문인상,Kim, Dongki,Ha, Seong up,Moon, Il yoon,Moon, Insang 항공우주시스템공학회 2015 항공우주시스템공학회지 Vol.9 No.2
Staged combustion cycle engines are well known to have high combustion efficiencies and specific impulse. In this study, design of mixing head part of combustion chamber for 8tonf class staged combustion cycle rocket engine (ES-08) was performed. Structural stability of the mixing head part of the combustion chamber is very important design factor because it is loaded by high temperature and high pressure of fuel and oxidizer as well as by thrust load simultaneously. Uniformity of flow distributions of the propellants to the injectors is also important factor. First, a basic configuration for the ES-08 mixing head part was designed on the basis of the structural design requirements. And then, the structural analyses were performed on the basic configuration as well as some of reinforced configurations. As the structural analyses results, the most stable configuration was selected for the ES-08 mixing head part. In order to examine the uniformity of the flow distributions of the propellants through the manifold of the mixing head, flow analysis was performed based on the selected configuration. The results of the flow analysis showed that the fuel and the oxidizer were uniformly supplied to the injector.
김동기(Dongki Kim),김원태(Wontae Kim),김기열(Kiyoul Kim),김찬영(Chanyong Kim),강신재(Shinjae Kang) 한국자동차공학회 2009 한국자동차공학회 지부 학술대회 논문집 Vol.2009 No.10
Materials design and processing development proposed in this research, aims at contributing to low price wear resistant automobile diesel engine parts. Dense bonding layer products were fabricated by solid diffusion bonding method. The hardness and TRS values obtained were 88HRA and 120㎏/㎟, respectively. Finally, teamwork consisting of company, university and research center will give them a chance of learning, processing, theory and applications in machine parts and will help domestic automobile industries internationally competitive.
8톤급 다단연소사이클 로켓엔진 주요구성품 연계 연소시험 설비구축
김동기(Dongki Kim),하성업(Seong up Ha),문일윤(Il yoon Moon),문인상(Insang Moon),이수용(Sooyong Lee),지상연(Sangyeon Ji),서종원(Jongwon Seo) 한국추진공학회 2015 한국추진공학회 학술대회논문집 Vol.2015 No.5
다단연소사이클 로켓엔진은 높은 연소효율과 비추력을 내는 엔진으로 잘 알려져 있다. 항공우주연구원에서는 다단연소사이클 로켓엔진 개발을 위해 주요구성품인 예연소기와 연소기 개발을 진행해왔다. 본 논문은 8톤급 다단연소사이클 로켓엔진 주요구성품 연계 연소시험을 위한 시험설비의 개발현황을 기술하였다. 엔진 규격과 설계 요구조건을 바탕으로 유공압 시스템, 제어계측 시스템, 시험스탠드 시스템, 기타 부대설비를 설계 및 구축하였다. Staged combustion cycle engines are well known to have high combustion efficiencies and specific impulse. In Korea Aerospace Research Institute (KARI), major components of the rocket engine such as a preburner, a turbopump, and a combustion chamber have been developing for the staged combustion cycle engines. This paper describes the construction and development status of firing test facility for the major components of the 8tonf class staged combustion cycle rocket engine. The test facility such as phuemo-hydraulic system, control/measurement system, test stand system, and other service systems were designed and constructed on the basis of the design requirements.
8톤급 다단연소 사이클 로켓엔진 혼합헤드 구조설계 및 해석
김동기(Dongki Kim),문일윤(Ilyoon Moon),조원국(Wonkook Cho),이수용(Sooyoug Lee) 한국추진공학회 2014 한국추진공학회 학술대회논문집 Vol.2014 No.12
8톤급 다단연소 사이클 로켓엔진 연소기 혼합헤드에 대한 구조설계를 수행하였다. 연소기 혼합헤드는 추진제로 사용되는 산화제와 연료에 의하여 고온 고압의 하중을 받는 동시에 추력에 의한 하중을 받기 때문에 구조적으로 안정해야 한다. 구조설계 요구조건을 바탕으로 8톤급 다단연소 사이클 로켓엔진 연소기 혼합헤드의 기본형상을 설계하였다. 설계된 기본형상을 바탕으로 구조해석을 수행하여 보강이 필요한 구조 취약 부위를 선정하였다. 구조 취약 부위를 보강 설계 후 기본형상을 포함하여 보강모델 총 4 종류의 해석모델에 대하여 구조해석을 수행하고 구조적으로 가장 안정한 설계형상을 선정하였다. Structural design of a mixing head part for a 8tonf class staged combustion cycle rocket engine was preformed. Structural stability of the mixing head part is a very important factor because it is loaded by high temperature and high pressure of oxidizer and fuel in addition to thrust load. A basic configuration for the mixing head part of the 8tonf class staged combustion cycle rocket engine was designed on the basis of the structural design requirements. The structural analysis was performed based on the designed basic configuration, and the structural weakness points was reinforced on the basis of the analysis results. Four reinforced design configurations including the basic configuration were analyzed to select structurally the most stable design configuration.
한국형발사체 추진기관시스템 시험설비(PSTC) 통합제어시스템
김동기(Dongki Kim),이정호(Jungho Lee),조기주(Kiejoo Cho),심주영(Juyoung Shim) 한국추진공학회 2017 한국추진공학회 학술대회논문집 Vol.2017 No.5
한국형발사체 각 단 추진기관시스템의 성능 검증을 위해 나로우주센터에 추진기관시스템 시험설비(PSTC, Propulsion System Test Complex)가 구축되었다. 본 논문은 PSTC 지상설비와 발사체 운용 및 제어를 위해 개발된 통합제어시스템(MCS, Main Control System)의 설계, 개발 현황, 시운전 결과에 관한 내용이다. MCS는 시험대상체와 지상시스템의 인터페이스에 활용될 예정이며, 시험책임자에 의한 시험운용 및 시퀀스 처리를 수행하게 된다. 또한 시험책임자 모의시험운용에도 활용될 예정이다. The Propulsion System Test Complex(PSTC) was constructed for the verification test of each stage’s propulsion system of KSLV-Ⅱ. Main Control System(MCS) is the system to operate the onboard equipment and the ground equipment of the PSTC simultaneously. This paper describes the critical design, the development status, and test results of Main Control System. The MCS will be used for the interface connection between ground control systems and onboard equipment. Test sequence and operation process of the Work Manager will be conducted by MCS.