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상단 추진 시스템에 적용을 위한 전기펌프 사이클의 국외 연구 동향
기원근(Wonkeun Ki),이재청(Jaecheong Lee),이형진(Hyoungjin Lee),노태성(Tae-Seong Roh),허환일(Hwanil Huh) 한국추진공학회 2020 한국추진공학회지 Vol.24 No.1
An electric-pump cycle, which is a propellant supply system for driving pumps of a liquid rocket engine using an electric motor, has the advantages of simple system configuration and easy control of supply flow rate and pressure. This paper investigates and analyzes the overseas research trends of the electric-pump cycle. In addition, the research and development country, performing organization, application, engine thrust, pump pressure increase, motor power, and rotation speed are summarized. Among them, the design variables of the overseas research that applied the upper-stage propulsion system with the thrust range of 0.445~2.2 kN could be used in the study of a similar electric-pump cycle in Korea.
전기펌프 사이클의 추진제 공급 시스템 모사용 수류 시험 연구
기원근(Wonkeun Ki),황기영(Ki-Young Hwang),이재청(Jaecheong Lee),최준섭(Junsub Choi),허환일(Hwanil Huh),김건영(Geon Young Kim) 대한기계학회 2021 大韓機械學會論文集B Vol.45 No.2
전기펌프 사이클의 추진제 공급 특성을 실험적으로 파악하기 위해 공급 모사 수류 시험 장치를 구성해야 한다. 본 연구에서는 0.2 kW급 원심 펌프를 이용하여 모사 수류 시험 장치를 구성하고 수류시험을 수행하였다. 인젝터와 연소실은 수류 시험에서 연소과정 만큼의 차압을 나타낼 수 없으므로 니들 밸브를 설치해 차압 요소로 모사하였다. 실험의 신뢰성을 검증하기 위해 측정 불확도 평가를 수행하였다. 실험결과, 니들 밸브 개도 변화에 따른 압력, 유량을 측정하고 펌프의 유량–압력상승 선도를 구해 실험 장치의 정상 작동을 확인하였다. 그리고 인젝터와 연소실을 니들 밸브를 통해 차압 요소로 모사가능함을 확인하였다. In order to understand the characteristics of the propellant supply in the electric pump cycle, water flow test equipment must be constructed. In this study, water flow test equipment was constructed using a 0.2 kW-class centrifugal pump, and water flow tests were performed. Because the injector and combustion chamber cannot show differential pressure as much as the combustion process in the water flow test, needle valves were installed to simulate the differential pressure. Uncertainty analysis was performed to validate the reliability of the experiment. The pressure and flow rate according to the change in the needle valve opening were measured, and a graph of the pump flow rate vs. pressure rise was obtained to confirm normal operation of the test equipment. Furthermore, it was confirmed that the injector and combustion chamber can be simulated as differential pressure elements with needle valves.
이주연(Juyeon Lee),기원근(Wonkeun Ki),허환일(Hwanil Huh),노태성(Tae-seong Roh),이형진(Hyoung Jin Lee) 한국추진공학회 2020 한국추진공학회지 Vol.24 No.6
The mathematical modeling applying experimental coefficients to a conventional model was validated through the hydraulic test for the components and the full system of a small-sized liquid rocket engine’s propellant supply system. According to the simulations, pressures difference for the fluid resistance components and the pump were mainly predicted. In order to improve the modeling accuracy, the loss coefficients obtained by the empirical method were applied to the modeling. Based on the governing equation of the flow or the well known empirical equation, the method of deriving the empirical coefficients was summarized and the coefficients were presented for the commercial products used in this study. The prediction results by modeling were in good agreement with the experimental data. Through the comparison with the experimental data, the factors affecting the accuracy of the simulation were analyzed and improving methods of the accuracy was proposed.
최준섭(Junsub Choi),허환일(Hwanil Huh),기원근(Wonkeun Ki) 한국추진공학회 2020 한국추진공학회지 Vol.24 No.5
Recently, a new space era has evolved in which commercial companies’ led space development has begun. In this era, commercial companies actively participate in space development as the size of the small satellite market and small launch vehicle market is expanding. Through space development, developed countries are making efforts to reduce development, production, and operation costs to secure the competitiveness of small launch vehicles. In this study, the development trend of small launch vehicles and required technologies for space development were analyzed and summarized. Thus, research and development is urgently needed so that spin-on technologies, such as electric pumps and additive manufacturing, can be utilized for space development.