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Seo, Mansu,Park, Hana,Yoo, DonGyu,Jung, Youngsuk,Jeong, Sangkwon The Korea Institute of Applied Superconductivity a 2014 한국초전도저온공학회논문지 Vol.16 No.2
Measuring an exact amount of remaining cryogenic liquid propellant under microgravity condition is one of the important issues of rocket vehicle. A Pressure-Volume-Temperature (PVT) gauging method is attractive due to its minimal additional hardware and simple gauging process. In this paper, PVT gauging method using liquid nitrogen is investigated under microgravity condition with parabolic flight. A 9.2 litre metal cryogenic liquid storage tank containing approximately 30% of liquid nitrogen is pressurized by ambient temperature helium gas. During microgravity condition, the inside of the liquid tank becomes near-isothermal condition within 1 K difference indicated by 6 silicon diode sensors vertically distributed in the middle of the liquid tank. Helium injection with higher mass flow rate after 10 seconds of the waiting time results in successful measurements of helium partial pressure in the tank. Average liquid volume measurement error is within 11% of the whole liquid tank volume and standard deviation of errors is 11.9. As a result, the applicability of PVT gauging method to liquid propellant stored in space is proven with good measurement accuracy.
한국형발사체 발사대시스템 산화제공급계 충전 운용 설계의 검증을 위한 나로호 비행시험 실증 자료 분석
서만수(Mansu Seo),이재준(Jae Jun Lee),홍일구(Ilgu Hong),강선일(Sunil Kang) 한국추진공학회 2018 한국추진공학회지 Vol.22 No.5
Korea Space Launch Vehicle (KSLV)-I flight test data and the modified 1-dimensional steady state modeling data from the critical design results of the KSLV-II liquid oxygen filling system operation are compared to validate the reliability of critical design modeling. A comparison of major flow rates and pressure values between test data and calculation results are conducted. The relative errors relative to maximum total flow rate for each cooling, filling, and replenishment mode are determined within 6.7%. Calculated pressure values at the outlet of the pump and the inlet of flow control valves are within 5.1%. The pressure at the inlet of the launch vehicle for each operation mode are within the measured pressure range.
한국형발사체 (KSLV-II) 발사대시스템 추진제 공급설비의 산화제 3단 동시 충전 운용 분석
서만수(Mansu Seo),이재준(Jae Jun Lee),강선일(Sunil Kang) 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.12
본 논문은 한국형발사체(KSLV-II) 발사대시스템 상세설계 단계 중 수행된 수력학적 관점의 한국형 발사체 산화제 3단 동시 충전 과정의 유동 해석 결과를 소개한다. 한국형발사체 발사대시스템 상세 설계 결과물을 바탕으로 1-D 유동해석 모델링 및 계산을 수행하였으며, 이를 이용하여 충전모드에 따른 유량조절밸브 개도, 구동절차와 충전완료 시간 등을 선정하였다. In this paper, 1-D calculation results of the liquid oxygen filling system (LOXFS) of the launch complex system of Korea Space Launch Vehicle-II (KSLV-II) is introduced from critical design result The characteristic of pressure drop of all components of LOXFS are considered in 1-D flow model. Simultaneous filling operation of three stages of KSLV-II is calculated with hydraulic flow model. Filling scenario, detailed process of liquid oxygen filling process, and opening ratio of the end valves are considered with calculation.
한국형발사체 발사대시스템 산화제공급계 충전 운용 설계의 검증을 위한 나로호 비행시험 실증 자료 분석
서만수(Mansu Seo),이재준(Jae Jun Lee),홍일구(Il-gu Hong),강선일(Sunil Kang) 한국추진공학회 2017 한국추진공학회 학술대회논문집 Vol.2017 No.5
본 논문은 한국형발사체(KSLV-II) 발사대시스템 상세설계 단계 중 수행된 산화제 충전 운용 설계를 검증하고자, 나로호 1차 비행 시험 실증 자료과 해당 설계 모델링 유동 해석 결과를 비교하였다. 나로호 비행 시험에 적용되었던 공급 조건과 충전모드에 따른 유량조절밸브 개도와 구동 절차 조건을 한국형발사체 발사대시스템 상세설계 모델링에 적용하여, 실증 자료와 모델링의 산화제 공급 유량값과 주요 압력값을 비교하였다. In this paper, KSLV-I flight test data and critical design results of filling operation for liquid oxygen filling system are compared to validate the reliability of the critical design modeling. Applying the filling and operation conditions on the critical design modeling, comparison of major flow rates and pressure values between test data and calculation results are conducted.
서만수(Mansu Seo),고민호 (Min-Ho Ko),선정운(Jeong-Woon Sun),서현민(Hyun-Min Suh),이재준(Jae Jun Lee),강선일(Sunil Kang) 한국추진공학회 2017 한국추진공학회지 Vol.21 No.2
In this paper, the liquid oxygen filling system (LOXFS) of the launch complex system of Korea Space Launch Vehicle-II (KSLV-II) is introduced based on critical design result by KARI in 2015 to 2016. The function and specification of the main systems of the liquid oxygen filling system, such as the storage tank, the drainage tank, the supply pumping system, the curved heat exchanger with liquid nitrogen, end valve block system, and umbilical connection, are presented.