Design and analysis of rocket engine system with electric pump as subsystem

Abstract

Electric pump feed systems use the high-speed and high-performance motor to replace the traditional turbine as the driving machine of pumps. A new feed system scheme is proposed in which a small-flow electric pump pressurizes hydrogen peroxide to the gas generator. The system keeps the performance of the engine at a high level, while being able to achieve continuous regulation and depth regulation. The balance calculation method and reliability allocation method are used. The results show that, the power of the electric pump for fuel path and oxidizer path is 600.0 W and 1732.6 W, respectively. The total mass of the engine is 69.76 kg, and the mass percentage of the electric pump system is small, less than 3.2% of the overall system mass. The effect of the electric pump system on the engine mass is small, but it improves the engine regulation capability. The reliability of this engine system is calculated to be 0.9802, which is not less than the target value of 0.98 with a certain margin, according to the reliability assigned to each combined part.