Liquid and solid propellant 🔥 #rocket engines feature low mass efficiency due to the thermodynamic limitations and extremely low efficiency at small thrust. The electric 🔋 thrusters do not pose limits on the propellant exhaust velocity and the propellant mass consumption may be very low https://www.nature.com/articles/s41467-017-02269-7

#ElectricPropulsion #PlasmaThruster #IonThruster #HallThruster