액체로켓엔진용 파이로시동기 추진제 그레인 설계

In present study, solid propellant grain of the pryostarter is designed for liquid rocket engines. To prevent the turbopump RPM overshoot, regressive mass flow rate profile is required. Sudden decrease of the mass flow rate at the end of the propellant burning is reflected to the design requirements as well. The performance of the designed pyrostarter is predicted to satisfy the design requirements from the internal ballistics analysis. Firing test results are similar to the design requirements of the mass flow rate except the initial period with high peak pressure. Ignition pressure will be reduced by the variation study of the ignition materials.