Air-breathing electric propulsion: mission characterization and design analysis

Abstract Air breathing electric propulsion (atmosphere-breathing propulsion) (ABEP) has attracted significant interest as an enabling technology for long duration space missions in very low Earth orbit (VLEO) altitudes below about 300 km. The ABEP spacecraft and mission analysis model developed allows parametric characterization of key geometry thruster performance parameters such length-to-diameter, the ratio solar array span to diameter, thrust-to-power, effective exhaust velocity, inlet efficiency. For analyzed generally outperforms conventional (EP) 250 km altitude. Using a 6U architecture shows that 220 is only viable option desirable lifetimes. Parametric evaluations characteristics show most technological improvements range applicability VLEO will come from advancements efficiency, drag materials, thrust-to-power.