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정영석(Young-Suk Jung),오승협(Seung-Hyub Oh),박정주(Jeong-Joo Park) 대한기계학회 2007 대한기계학회 춘추학술대회 Vol.2007 No.10
The propulsion system of a launch vehicle can be classified with subsystems as propellant tank, pressurization system, propellant fill/drain system, valve operating system, purge system and so on. Among others, Pressurization system is the most important subsystem, because of the only active control part. On conceptual design process, it is the first considerable system. In this paper, the materials of the previously developed pressurization systems were surveyed and the optimumconfiguration was selected with the analysis of advantages and disadvantages of each system and the weight of each system.
정동호(Jung, Dong-Ho),오승협(Oh, Seung-Hyub) (사)한국CDE학회 2010 한국 CAD/CAM 학회 학술발표회 논문집 Vol.2010 No.1
Lunch vehicle‘s propulsion system feeding line are undergone inner pressure, self dropping, acceleration, cryogenic condition during flight. it should be checked margin of safety through structural analysis. In this paper have performed FEM analysis. Analysis results show that KSR-III Propulsion system feeding line have sufficient margin of safety. This research will help KSLV-II propulsion system development.
정동호(Jung, Dong-Ho),오승협(Oh, Seung-Hyub) (사)한국CDE학회 2011 한국 CAD/CAM 학회 학술발표회 논문집 Vol.2011 No.1
Payload transporting launch vehicles are composed two types. One is using single liquid propulsion engine and another is clustered several liquid propulsion engines. Launch vehicle development and composition depend on its own technology. On this report deal with clustering concept for four engines. Clustering concept is considered arrangement of engines and gimbal angle of engines. Important factor of clustering is physical arrangement of four engines without interference in maximum operation condition. Future research will be conducted aerodynamic force and heating of cowl and effect of flume, interface of flume.
조상연(Sang Yeon Cho),오승협(Seung Hyub Oh) 한국추진공학회 2012 한국추진공학회 학술대회논문집 Vol.2012 No.5
한국항공우주연구원에서는 현재 1.5톤급 위성 발사체인 한국형 발사체 KSLV-Ⅱ를 개발중이며 시스템의 설계 리뷰를 앞두고 있다. 또한, 발사체의 개발과정에 있어서 임무 보증 업무의 일환으로 신뢰성과 안전, 품질등을 관리하고 있으며 발사체의 안전 확보를 위해서 기존에 공표된 안전 보장 계획 및 시스템 안전 프로그램 계획에 따라 관련 업무를 수행하고 있다. 본 연구에서는 상기의 계획에 의거하여 수행된 사전 안전 분석의 내용과 방법에 대하여 설명하고 실제 추진기관 시스템에 대하여 도출된 위험요소들을 소개하고자 한다. 도출된 위험 요소들은 향후 개발이 진행되면서 위험 수준을 완화하는 방향으로 관리될 계획이다. KARI is now developing KSLV-Ⅱ which can insert 1.5ton satellite into the orbit, and system design review is close at hand. As a part of mission assurance for space launch vehicle, reliability and safety management is being performed and to assure the safety, KARI has been doing actions on the basis of the safety assurance plan and system safety program plan. In this study, preliminary hazard analysis is reviewed and the result for the propulsion system will be illustrated. The result will be used as a reference for the safety and risk management.
이한주(Han Ju Lee),오승협(Seung Hyub Oh) 한국항공우주연구원 2012 항공우주기술 Vol.11 No.1
발사체에서 요구되는 고추력을 생성하기 위해서는 고추력 엔진 1기 혹은 낮은 추력의 엔진 여러 기를 클러스터링하는 방법을 사용한다. 각각의 장단점이 있지만, 발사체를 구성하는 시점에서 가용한 엔진 혹은 개발 가능한 엔진을 사용하여 요구 추력을 생성하게 된다. 한국형발사체의 1단 추진기관 시스템에 요구되는 추력은 300톤급으로 단일 엔진 시스템으로 구성하기에는 현 수준에선 무리가 있다고 판단되어 75톤급 액체 엔진 4기를 클러스터링하여 구성한다. 본 자료에서는 한국형발사체의 1단 클러스터드 엔진 배치에 대한 개념에 대해 다룬다. Generally, the first stage of a launch vehicle requires high thrust to achieve a mission. We can use one high thrust level engine or a clustered engine system which made of several small thrust level engines to make high thrust. The first stage propulsion system of KSLV-II has 300tf thrust to satisfy the mission. But it is impractical to make high thrust by one engine at this moment in time. So we should cluster four 75tf class engines which can be applied to make a required thrust for the first stage propulsion system. This article deals with the concept of the first stage clustered engine arrangement of KSLV-II.
박정,김용욱,김영한,정용갑,조남경,오승협,Park, Jeong,Kim, Yong-Wook,Kim, Young-Han,Chung, Yong-Gahp,Cho, Nam-Kyung,Oh, Seung-Hyub 대한기계학회 2000 大韓機械學會論文集B Vol.24 No.5
A model for depicting the rocket engine combustion process is presented and several experiments near a design point are provided with a FOOF type of unlike impinging injector for a propellant combination of Jet A-1 fuel and liquid-oxygen. The model is based on the assumption that the vaporization is the rate-controlling combustion process. The effects of initial drop size and initial drop velocity are systematically shown and discussed. It is seen that in the midst of considered parameters the change of initial drop size is more sensitive to the performance. The proposed model describes qualitative trends of combustion process well despite of its simplicity.
이한주(Hanju Lee),이정호(Jung Ho Lee),오승협(Seung Hyub Oh) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.5
KSLV-I 상단 킥모터는 고체 추진기관으로 점화기와 점화안전장치로 구성된 점화구동부, 복합재 케이스부, 추력벡터제어가 가능한 잠입형 노즐부, 그리고 추진제로 구성되어 있다. 킥모터를 구성하는 각 서브시스템들은 비행 임무 달성을 위한 개발 요구조건을 만족시켰으며, 2013년 1월 30일 나로호 3차 비행 시험 결과로부터 성공적으로 개발이 완료되었음을 확인할 수 있었다. 본 논문에서는 킥모터에 대한 요구조건, 요구조건을 만족하기 위한 형상관리, 중량 변화, 추력 축 정렬 결과 및 주요 시험 결과 등에 대해 다루었다. KSLV-I upper stage KM (Kick Motor) is a solid propulsion system which is consist of igniter, SAD (Safety Arming Device), composite case, submerged nozzle capable of TVC (Thrust Vector Control) actuation. Each subsystem of KM fulfilled development requirements for achieving a flight mission successfully. We confirmed that the successful development of KM from the 3rd flight test results of NARO on January 30, 2013. This article deals with the requirements of KM and the results on configuration management, mass variation, thrust axis alignment, and major test results and so on.