System Analysis and Test-Bed for an Atmosphere-Breathing Electric Propulsion System using an Inductive Plasma Thruster

TL;DR

This paper explores an atmosphere-breathing electric propulsion system using an inductive plasma thruster, aiming to enable long-duration space missions without onboard propellant by utilizing atmospheric particles as fuel.

Contribution

It introduces a novel system analysis and experimental assessment of an inductive plasma thruster for atmosphere-breathing propulsion, addressing efficiency and plasma characteristics.

Findings

High electric-to-thermal coupling efficiency with O2 and CO2

Assessment of plasma plume energy and exhaust velocities

Potential for continuous operation in low Earth orbit

Abstract

Challenging space mission scenarios include those in low altitude orbits, where the atmosphere creates significant drag to the S/C and forces their orbit to an early decay. For drag compensation, propulsion systems are needed, requiring propellant to be carried on-board. An atmosphere-breathing electric propulsion system (ABEP) ingests the residual atmosphere particles through an intake and uses them as propellant for an electric thruster. Theoretically applicable to any planet with atmosphere, the system might allow to orbit for unlimited time without carrying propellant. A new range of altitudes for continuous operation would become accessible, enabling new scientific missions while reducing costs. Preliminary studies have shown that the collectible propellant flow for an ion thruster (in LEO) might not be enough, and that electrode erosion due to aggressive gases, such as atomic oxygen, will limit the thruster lifetime. In this paper an inductive plasma thruster (IPT) is considered for the ABEP system. The starting point is a small scale inductively heated plasma generator IPG6-S. These devices are electrodeless and have already shown high electric-to-thermal coupling efficiencies using O2 and CO2. The system analysis is integrated with IPG6-S tests to assess mean mass-specific energies of the plasma plume and estimate exhaust velocities.