The development status of a 2,500 N H2O2/kerosene bipropellant thruster is described in this paper. The autoiginition of the kerosene was varified by the hot firing test without film cooling. The chamber pressure was sustained consistently during the operation. The characteristic velocity efficiency and the chamber pressure fluctuation were 90.5%, and 0.80 %, respectively. A film cooling is applied to protect the chamber and nozzle material from the combustion gas using hydrogen peroxide as a coolant. Four experimental cases were conducted by varying the proportion of the coolant with respect to total amount of fed hydrogen peroxide between 13.4% to 25.6%. The temperature at the nozzle throat reached steady state when the coolant was 25.6%. From the test results, cooling performance was supposed to sufficient to cool down the coolant rate supplied between 22.2% and 25.6%.