Hybrid rocket engine using electric motor-driven oxidizer pump

A hybrid rocket engine comprising:

• an oxidizer tank configured to store an oxidizer;
• an oxidizer pump configured to pressurize the oxidizer by being connected to the oxidizer tank through a first oxidizer supply line;
• a drive unit comprising an electric motor configured to drive the oxidizer pump and a battery configured to supply power to the electric motor;
• an auxiliary oxidizer line configured to guide the oxidizer from the oxidizer tank to the electric motor to cool the electric motor of the drive unit;
• an oxidizer recirculation line connected from the drive unit to the oxidizer tank;
• and
• a combustion chamber configured to combust the oxidizer and fuel by being directly connected to the oxidizer pump through a second oxidizer supply line on which a main oxidizer supply valve is disposed,
• wherein a portion of the oxidizer is bled from upstream of the oxidizer pump and supplied to the electric motor and the battery of the drive unit through the auxiliary oxidizer line, is vaporized through heat exchange between the electric motor and the oxidizer, and subsequently exits the drive unit to be returned to the oxidizer tank through the oxidizer recirculation line, thereby recharging the oxidizer tank and pressuring an inner side thereof, and
• wherein the oxidizer pump is driven by the electric motor powered by the battery.