1단 발사체 성능해석 프로그램 개발

초록

To suggest launch vehicle design basis for liquid rocket engine, a performance analysis of the liquid rocket using a gas-generator cycle has been implemented. With combustion chamber pressure, nozzle expansion ratio, and thrust-to-weight ratio as input variables, burning time, mass flow rate, altitude, and velocity have been obtained. As a result, arrival altitude and velocity increase at the end of burning time when combustion chamber pressure decreases and nozzle expansion ratio increases. When the thrust-to-weight ratio increases, however, the velocity increases but the arrival altitude decreases. Therefore, it is important to select the adequate thrust-to-weight ratio of the launch vehicle according to the user's target altitude and velocity.