케로신/액체산소 액체로켓엔진의 지상/고공 환경에서의 추력 특성에 관한 연구

In this study, thrust was measured through the ground and high altitude simulation hot firing test with a liquid rocket engine using kerosene/liquid oxygen at the horizontal combustion test stand. There were from 4% to 11% errors between the measured thrust calibrated by TMS calibration test equations and the theoretical thrust calculated by experimental data under the two combustion conditions. And, high altitude thrust coefficient was increased 35% than ground thrust coefficient by combustion tests.