The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene
作者: Yang-Suk LEE Jun Hwan JANG
作者单位: 1Koreaaero Industry, Sacheon-si, Gyeongsangnam-do, Korea
2Mechanical Design Major Department of Mechanical Engineering, Yuhan University, Gyeonggi-do, Korea
刊名: INCAS BULLETIN, 2019, Vol.11 (3)
来源数据库: National Institute of Aerospace Research
DOI: 10.13111/2066-8201.2019.11.3.9
关键词: Green PropellantHydrogen PeroxideRCS (Reaction Control System)Space Launcher
原始语种摘要: Mono-propellant thrusters are widely utilized in satellites and space launchers. In many cases, they are using hydrazine as a propellant. However, hydrazine has high toxicity and high risks in using for launch campaign. Recently, low-toxic (green) propellant is being highlighted as a replacement for hydrazine. In this paper, 200N bi-propellant engine using hydrogen peroxide/kerosene was designed/manufactured, and the spray or atomization characteristic and inflation pressure were determined by cold flow test, and combustion and pulse tests in a single cycle same as previous methods were conducted. As uniformly supplying hydrogen peroxide through plate-type orifice to a catalyst bed, the hot gas was created as a reaction with hydrogen and catalyst. And then, it was confirmed that the...
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  • propellant 推进剂
  • rocket 火箭
  • engine 发动机
  • kerosene 煤油
  • hydrazine 联氨
  • performance 性能
  • decomposed 已分解的
  • injector 注射器
  • catalyst 催化剂
  • hydrogen