Abstract
Electric pump-fed liquid propellant rocket engine is an engine that uses electric pumps for propellant supply and cooling cycle. The engine breaks through the traditional pressurization mode of using inert gas to squeeze the propellant or gas-driven turbo pump, and has the advantages of simple system, light structure, high reliability and easy implementation of thrust adjustment. This study introduces the composition, working principle and technical advantages of the electric pump-fed liquid propellant rocket engine, evaluates the factors affecting the mass of the supply system with sensitivity analysis method, and analyses the key technologies of the electric pump-fed rocket engine.
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