This thesis investigates the feasibility of an electric pump-fed (EPF) engine cycle for a two-stage small satellite launch vehicle using liquid methane and liquid oxygen. Emphasis is placed on the development of the liquid methane pump, which operates in a dual-shaft EPF configuration and achieves a theoretical efficiency of 57 % at a specific speed of 20.
Both stages utilize battery-powered radial flux permanent magnet motors driving cryogenic centrifugal pumps, with leakage flow used for cooling and autogenous tank pressurization. The vehicle architecture aims to reduce system complexity while maintaining performance margins and scalability.
