An electrically driven pump-fed cycle for a hybrid rocket engine is proposed and compared to a simpler gas-pressurized feed system. A liquid-oxygen/paraffin-based fuel hybrid rocket engine which powers the third stage of a Vega-like launcher is considered. Third-stage ignition conditions are assigned. and engine design and payload mass are defined by a proper set of parameters. https://cosmeticssquadets.shop/product-category/antiseptics/