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최원석(Wonseok Choi),이형서(Hyeongseo Lee),박호진(Hojin Park),이시형(Sihyeung Lee),정상엽(Sangyeop Jeong),장은이(Eunei Jang),길유창(Yuchang Gil),고수한(Suhan Ko) 한국추진공학회 2023 한국추진공학회 학술대회논문집 Vol.2023 No.5
The purpose of this study is to design an Ethanol/H₂O₂ small liquid rocket. The target altitude is 100m, the combustion time is 4 seconds, and the target thrust is 450 N, with a combustion chamber pressure of 15 bar and an O/F ratio of 2, and a design I<SUB>sp</SUB> of 290 s. The combustion chamber has an inner diameter of Ø60 and a height of 250 mm, and the characteristic length of the chamber is 3.2 m. A Swirl coaxial injector is used, with oxidizer injected internally and fuel injected externally. The propellant supply method uses a pressurized propellant supply method, with nitrogen used as the pressurizing gas. A torch ignition system is used, with methane and gaseous oxygen used as the fuel and oxidizer, respectively, and flow rate controlled by an orifice. After confirming the engines performance based on the designed values, there are plans to conduct test flights.