Hot-Firing Test of Methane-Fueled Rocket Engine under High Altitude Condition

Abstract

Fundamental research activities have been conducted on LOX/Methane rocket engine to achieve higher performance for upper stage system of a middle class launch vehicle. The effects of combustion chamber pressure and mixture ratio on engine performance were demonstrated using a subscale engine test model in the High Altitude Test Stand. Highly expanded nozzle, area ratio of 71 was used in the HATS test to obtain thrust increment generated in the nozzle part. The combustion chamber pressure was changed as a parameter from 1 MPa to 3 MPa, mixture ratio was changed as a parameter from 2.8 to 3.6. Test results shows that specific impulse and thrust performance are increasing with combustion chamber pressure. On the other hand, effects of mixture ratio were small within the test condition.