http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
추진기관 탱크내 극저온 추진제의 온도 상승에 대한 연구
임석희(Seok-Hee Lim),베르샤드스키(Bershadskiy. V. A.),정영석(Young-Suk Jung),조기주(Kie-Joo Cho),오승협(Seung-Hyub Oh) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.6
This study has considered the definition of temperature increase in the cryogenic propellant at the development stage of propulsion system. From the analysis of known theoretical model for calculation and the consideration of possible heat and mass transfer mechanism on the full-scale tank, methodical characteristics of calculation-experimental for estimation of key parameters of temperature rise and thermal stratification have been formulated with application of sub-scale tank modeling and imitation of operation environment of propellant supplying system.
이기주(Keejoo Lee),임석희(Seok Hee Lim),고주용(Ju Yoeng Ko),박순영(Soon Young Park),박광근(Kwangkun Park),박재성(?Jaesung Park),안재명(Jaemyung Ahn) 한국추진공학회 2018 한국추진공학회 학술대회논문집 Vol.2018 No.12
전 세계 저궤도 발사시장의 10%를 점유하자는 우주 비전을 마련해서 소형위성 발사서비스를 육성해서 향후 10년간 200억원 이하 년 3회 발사를 목표로 총 30회 발사한다는 전략을 세우고 한국형발사체 개발사업에서 구축한 기존 인프라를 활용하여 소형위성 발사체를 민간 주도로 조속히 확보할 수 있으면 한국의 우주산업이 급격히 성장할 것으로 전망한다. 개념연구를 통해서 2단형 소형위성 발사체의 기술적인 타당성을 검토할 필요가 있다. A grand vision of taking up 10 percent of non-GSO satellite launch market in the next ten years could be realized if a long-term space strategy of promoting a small satellite launch service in cadence of three launches per year and a total of thirty launches at a price lower than 20M USD per launch were to be adopted on a firm foundation of the existing ground and vehicle infrastructure that had been developed for the KSLV-II program, and if a consortium of private enterprises were to invest in the development of small launch vehicles in prospect for a boom of the space industry in Korea. A conceptual study to examine the technical feasibility of TSTO small satellite launch vehicles is an appropriate next step.
헬륨 버블링 방법을 이용한 액체 추진제 로켓 추진제 탱크의 가압 시스템 분석
정영석(Young Suk Jung),임석희(Seok Hee Lim),조기주(Kie Joo Cho),베르샤드스키(V. A. Bershadskiy) 대한기계학회 2005 대한기계학회 춘추학술대회 Vol.2005 No.11
This paper presents an analysis method to predict the temperature of LOX(liquid oxygen) and He(helium) contents in LOX at prepressurization and main pressurization stages using GHe(Gas He) bubbling method for propellants feeding system in rocket. With presented analytical method in this paper, variation of temperature and He contents in LOX are predicted at prepressurization and main pressurization stages in case that GHe bubbling method is used in pressurization system of the 2nd stage. Computer simulations are accompanied in conditions of temperature(288K) and mass flowrate(0.02㎏/sec) of injected GHe at prepressurization stage and in conditions of controlled pressure of tank(4bar) and fixed mass flowrate of fed LOX to engine at main pressurization stage.
Optimal Conditions for Thermal Control of LOX using GHe Bubbling Method
Young-Suk Jung(정영석),Seok-Hee Lim(임석희),Gyu-Sik Cho(조규식),Kie-Joo Cho(조기주),V.A. Bershadskiy(베르샤드스키),Seung-Hyub Oh(오승협) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.6
In this paper, the algorithm for calculating the thermophysical parameters of LOX in tank at the step of LOX thermal conditioning system using GHe bubbling during pre-launch operation is presented. The algorithm is based on a physical-mathematical models which integrally consider the characteristics and intensity of heat and mass transfer in LOX of the propellant tank and the experimental models which are used for the description of intensity of heat and mass transfer and the change of composition of gas and liquid phases in LOX. With the developed algorithm, the transient analysis of thermal conditioning system is executed on each condition as a temperature of injected GHe and pressure of tank, and the optimal conditions are proposed for an efficient thermal conditioning system using GHe bubbling.