Cold Flow and Ignition Tests for a 75-tonf Kerosene-Cooled Liquid Rocket Engine Thrust Chamber

75톤급 액체로켓엔진 케로신 냉각 연소실 수류시험 및 점화시험

The Cold flow and ignition tests have been performed for a technology demonstration model of 75-tonf liquid rocket engine thrust chamber which was designed and manufactured on the basis of the previous development experience of a 30-tonf liquid rocket engine thrust chamber. The hydrodynamic characteristics of the facility supply pipelines and the filling time of the cooling kerosene were obtained through the cold flow tests. The ignition cyclogram was determinded using the results and the ignition test was successfully carried out. The acquired data and test technique of present ignition test will be used in hot firing tests.

한국항공우주연구원에서는 30톤급 액체로켓엔진 연소기 개발 기술을 바탕으로 설계 제작된 75톤급 기술검증시제의 수류시험 및 점화시험을 수행하였다. 수류시험을 통해 시험설비 공급라인의 수력학적 특성 및 냉각 케로신 충전시간을 파악하였다. 수류시험 결과로 점화절차를 결정하여, 점화시험을 성공적으로 수행하였다. 점화시험을 통해 획득한 자료와 시험 기법은 향 후 연소시험을 위해 활용될 것이다.