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액체로켓추진시스템의 가압제 탱크에서 가압제 토출시 온도강하율에 대한 연구 (Ⅱ)
정용갑(Yong-Gahp Chung),김용욱(Yong-Wook Kim),김유(Yoo Kim) 한국항공우주학회 2008 한국항공우주학회지 Vol.36 No.3
액체로켓추진시스템에서 추진제 가압시스템은 추진제가 저장되어 있는 탱크의 얼리지 공간에 가압제인 가스를 제어된 압력으로 공급하는 것이다. 이러한 추진제 가압시스템의 가장 중요한 설계변수는 극저온 추진제 탱크 내에 설치된 가압제 탱크에서 토출되는 가압제의 온도이며, 기체 상태인 가압제의 밀도는 토출되는 가압제의 온도에 따라 민감하게 변한다. 이 전 연구에서는 상온 가압제와 상온 외부유체 간의 온도 상관성에 대한 연구가 수행되었으며, 본 연구에서는 현재 개발 중인 액체로켓추진 발사체의 가압시스템과 통일한 조건인 극저온 가압제(GHe)와 극저온 외부유체(LOX)를 적용하여 가압제 탱크에서 가압제 토출 시 강하되는 온도 변화를 실험 및 해석을 통하여 고찰하였다. Propellant pressurization system in liquid rocket propulsion system plays a role in supplying pressurant gas at a controlled pressure into the ullage space of propellant tanks. The most important design parameter for such propellant pressurization system i the temperature of pressurant gas fed from pressurant tank, which is placed inside 0 cryogenic propellant tank. Such pressurant is gaseous state, of which density is vet; sensitive to the temperature of pressurant. Previous investigation dealt with thermal correlation of pressurant and external fluid at room temperature. This study investigate the temperature variation of cryogenic pressurant (GHe) at the time when the pressurant is coming out of pressurant tank, which is submerged in a liquid oxygen, experimentally as well as numerically.
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액체 로켓 엔진 극저온 LOX 산화제의 충진 및 연소시험시 거동 특성
정용갑(Yong-Gahp Chung),문일윤(Il-Yoon Moon),조남경(Nam-Kyung Cho),한영민(Yeoung-Min Han),이수용(Soo-Yong Lee) 대한기계학회 2001 대한기계학회 춘추학술대회 Vol.2001 No.9
The cryogenic characteristics of propellant is important parameter in the design of liquid rocket engine test facility. Pressure-fed rocket engine test facility with cryogenic propellant should be designed with considering cryogenic characteristics, vaporization should be avoided up to injection point. In this paper, characteristics of cryogenic liquid oxygen was examined during cold flow and combustion test of KSR-Ⅲ main engine at each stage. The effect of venting was examined at the stage of cooling and at the pressurization stage the interaction between nitrogen gas and liquid oxygen was also examined. The characteristic of liquid oxygen in the engine manifold was analyzed. To meet the pressure requirements during propellant outflow, the pressure in the upstream of engine was diminished rapidly, the effect of liquid oxygen was examined at rapid expansion. The results showed that venting was the primary role at the cooling process and the interaction of nitrogen gas and liquid oxygen in the run tank is limited at the surface area and the tests showed that the fluctuation of liquid oxygen flow was diminished at the combustion test and the expansion of liquid oxygen was contributed to the temperature rise of liquid oxygen.
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정용갑(Yong-Gahp Chung),한상엽(Sang-Yeop Han),조남경(Nam-Kyung Cho),권오성(Oh-Sung Kwon) 한국항공우주연구원 2006 항공우주기술 Vol.5 No.1
액체로켓 추진시스템에서 가압시스템은 발사체 추진제 탱크의 얼리지 공간에 제어된 가스를 공급하는 것이다. 가압시스템에서 고온 가스 열교환기를 적용하는 데는 가압제의 비체적을 증가시켜 전체 발사체 시스템의 중량을 감소시키는 장점이 있다. 가압시스템 성능에 있어서 주목할 만한 개선점은 극저온 시스템에서 얻어질 수 있다. 이러한 경우 가스 공급은 극저온 탱크 내부에 저장되어 진다. 본 연구에서는 극저온 유체로 액체 산소를 사용하였다. 극저온 가압제의 온도 특성은 가압시스템에서 구성품을 개발하는데 있어서 매우 중요하다. In this study, the pressurization system in a liquid rocket propulsion system provides a controlled gas pressure in the ullage space of the vehicle propellant tanks. It is advantage to employ a hot gas heat exchanger in the pressurization system to increase the specific volume of the pressurant and thereby reduce over-all system weight. A significant improvement in pressurization-system performance can be achieved, particularly in a cryogenic system, where the gas supply is stored inside the cryogenic propellant tank. In this study liquid oxygen was used. The temperature characteristic of cryogenic pressurant is very important to develop some components in pressurization system.
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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.
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조남경(Namkyung Cho),정용갑(Yong-Gahp Chung),신동순(Dong-Soon Shin),조인현(In-Hyun Cho) 한국추진공학회 2009 한국추진공학회지 Vol.13 No.5
Pneumatic system is widely applied to ground facility and launcher on-board system. One of the important aspects of pneumatic system is to meet pressure and flow rate requirements of gas consumers. In this paper, a systematic analytical approach for pneumatic system is proposed, which uses and systematically combines previous studies. The proposed analytical method is that pressure/flow calculation using conservation equations are combined with sonic limit check at vena contracta of the components of pneumatic system, which checks the installed components whether they are merely pressure loss elements or flow limiting element of the system. In this paper, gas consumers are categorized and simulated using the proposed method. The results reveal that the feeding performance of general pneumatic system can be properly estimated using the proposed approach.
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조남경(Nam-kyung Cho),정용갑(Yong-Gahp Chung),조인현(In-Hyun Cho) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.2
For launcher applications, different from other applications, very high flow rate is required which can lead to supply pressure drop against required setting pressure. The supply pressure decrease is closely related to regulator characteristics. In this paper, supply pressure offset is investigated considering regulators as kinds of control systems. Pressure offset of self-operated regulator is analyzed with sensitive parameter defined as the ratio of valve travel to pressure offset. It is shown that pressure offset of self-operating regulator can be improved by incorporating proportional and integral controls and they can be materialized with pilot regulator systems.
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조남경(Nam-kyung Cho),정용갑(Yong-Gahp Chung),남중원(Jung-Won Nam),조인현(In-Hyun Cho) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.11
공압시스템은 지상설비 및 발사체 공급시스템에 광범위하게 활용되고 있다. 공압시스템의 목적은 수요처에서 요구되는 유량 및 압력을 요구조건에 맞게 공급하는 것이다. 발사체 관련 가스공급은 타 분야 가스공급과는 달리 대유량의 가스공급이 일반적으로 요구되며, 이때 공급압력이 감소되어 유량을 공급하는 동안 요구되는 압력을 만족시키지 못하는 현상이 흔히 발생한다. 공급시 압력감소는 레귤레이터의 특성과 직접적으로 연관되어 있다. 본 논문은 대유량 가스공급시 공급압력 감소와 관련된 레귤레이터의 특성을 제어이론의 측면에서 검토하였고 이를 개선시킬 수 있는 방법을 이론적으로 제시하였다. Pneumatic system is widely applied to ground facility and launcher on-board system. The main requirements of pneumatic system is to meet pressure and flow requirements of gas consumers. For launcher related applications, different from other applications, very high flow is required which can leads to supply pressure drop against required setting pressure. The supply pressure decrease is closely related to regulator characteristics. In this paper, the characteristics of pneumatic regulator related to supply pressure decrease and the control methods for reducing the pressure offset are reviewed.
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