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지상연(Sangyeon Ji),이성민(Seongmin Lee),전유림(Yulim Jeon),한상두(Sangdu Han),김광원(Kwangwon Kim),유지성(Jisung Yoo),이종덕(Jongdeok Lee),이범석(Beomseok Lee),고민호(Minho Ko),이준성(Junseong Lee),김철웅(Cheulwoong Kim),임석희(Seokhee 한국추진공학회 2023 한국추진공학회 학술대회논문집 Vol.2023 No.5
This paper introduces the development of a 1tonf-class vertical take-off and vertical landing(VTVL) demonstrator designed to verify the core technology of reusable launch vehicles. The VTVL demonstrator has a pressure-fed engine system and uses liquid oxygen and liquid methane as propellants. Major autonomous tests of its subsystems and components have been completed. Hot fire tests and tethered flight tests will be conducted on the VTVL demonstrator to verify the functionality and performance.
도정환(Jeonghwan Do),이성민(Seong-Min Lee),전유림(Yurim Jeon),최형준(Hyungjoon Choi),정희원(Heewon Jeong),지상연(Sangyeon Ji),김철웅(Cheulwoong Kim),임석희(Seokhee Lim) 한국추진공학회 2023 한국추진공학회 학술대회논문집 Vol.2023 No.5
In this paper, the configuration of the propulsion system of the vertical take-off and landing demonstrator(VTVL) and the pressure control concept and design method applied to the VTVL are introduced, and the results of the cold flow test using liquid nitrogen are analyzed. The propulsion system of the VTVL uses liquid oxygen and liquid natural gas as propellants, and a gaseous nitrogen pressurization system is applied. When the propellant is supplied, an appropriate amount of pressurized gas is supplied to maintain the pressure in the propellant tank at a certain required pressure. To control the supply rate of pressurized gas, an assembly block composed of solenoid valves and orifices was developed, and its effectiveness was confirmed through analysis of the liquid nitrogen flow test results.
문근환(Keunhwan Moon),김재선(Jaesun Kim),고민호(Minho Ko),전유림(Yulim Jeon),이종덕(Jongdeok Lee),이범석(Beomseok Lee),지상연(Sangyeon Ji),이준성(Junseong Lee),김철웅(Cheulwoong Kim),임석희(Seokhee Lim) 한국추진공학회 2023 한국추진공학회 학술대회논문집 Vol.2023 No.5
This paper introduces the test plan of a 1tonf-class vertical take-off and vertical landing(VTVL) demonstrator. The test facility for the VTVL demonstrator performance tests was constructed. The test facility was composed of a vertical test bed, propellant and pressurizing gas supply/drain system, and a control room. The test plan is to conduct leak and cold flow tests, vertical hot fire tests, and tethered flight tests. And free flight test will be conducted for verification of VTVL demonstrator.
이성민(Seong-Min Lee),도정환(Jeong-Hwan),지상연(Sang-Yeon Ji),김철웅(CheulWoong Kim),이준성(Junseong Lee),임석희(Seokhee Lim) 한국추진공학회 2022 한국추진공학회 학술대회논문집 Vol.2022 No.5
본 논문에서는 미래 발사체 재사용 요소기술 선행연구를 위해 제작 중인 1톤급 수직이착륙 시연체의 압력제어를 통한 가압성능시험을 수행하였다. 개발 중인 시연체는 가압제어를 위하여 매니폴드형 솔레노이드 밸브를 이용하여 가압제어를 하는 시스템으로 구성하였다. 탱크 후단에서 배출되는 유량에 따라 추진제 탱크 내부의 압력을 일정하게 유지하는 가압 성능시험 방법을 수행하였다. 결과적으로 추진제 탱크 내부의 일정한 가압을 위한 압력제어 성능은 확인하였으며, 이후 시스템별 성능 검증을 위한 단계별 시스템 검증을 수행할 계획이다. In this paper, the performance test of the pressure control pressurization system of the 1 ton class vertical take-off and landing demonstrator being manufactured for the prior research on the element technology for the reuse of the future launch vehicle was performed. The demonstrator under development is composed of a system that controls pressure using a manifold-type solenoid valve for pressure control. A pressurization performance test method was performed to keep the pressure inside the propellant tank constant according to the flow rate discharged from the rear end of the tank. As a result, pressure control performance for constant pressurization inside the propellant tank was confirmed, and thereafter, step-by-step system verification is planned to verify the performance of each system.