Characterization of Atmosphere-Breathing Electric Propulsion Intake Performance

Abstract

Satellite deployment at lower altitudes is increasing due to the benefits of payload operation. The payload performances, such as optical resolution, communication latency, and transmission power efficiency, are inversely proportional to the altitude [1]. In Very-Low-Earth-Orbit (VLEO), which indicates an altitude of less than 500 km, deorbit of the satellite is intensified by the drag of the rarefied atmosphere [2]. Atmosphere-Breathing-Electric-Propulsion (ABEP) has been proposed for continuous drag compensation maneuvers without onboard propellants [3]. The ABEP system is designed to intake and compress the upper atmosphere as a propellant of electric propulsion. The captured atmosphere is ionized and accelerated by the electromagnetic field to obtain thrust. Mechanisms of the ABEP system consist of four stages; intake, ionization, acceleration, and plume. The intake device is a component that sets it apart from conventional electric propulsion. As intake performance is directly rel