RF Helicon Plasma Thruster Prototype Validates Air-Breathing Operation in Simulated LEO Conditions
Preprint reports laboratory thrust from an RF helicon thruster ingesting simulated LEO air. Ground data indicate viable specific impulse but highlight scaling and atomic-oxygen durability gaps. Flight test needed within three years to confirm orbital utility.
The experiment used a 13.56 MHz RF helicon source coupled to a magnetic nozzle, ingesting N2/O2 mixtures at 10^-5 Pa while measuring ion current density and thrust via a pendulum balance. Data showed specific impulses above 1200 s at 200 W input power, confirming ionization efficiency above 80 percent. This extends earlier ESA and JAXA ABEP concepts by demonstrating sustained plasma stability without electrode erosion.
Atmosphere-breathing systems address the dominant failure mode for very-low-Earth-orbit satellites: propellant depletion within 2-3 years. Prior Hall and ion thrusters required xenon resupply; an ABEP design could extend operational life to a decade while cutting launch mass. The helicon approach avoids the grid erosion seen in earlier RF ion concepts tested by NASA in 2018.
The study remains a ground demonstration at 1:10 scale. Key unknowns include nozzle performance under real atomic-oxygen flux and spacecraft drag matching. A follow-on flight experiment on a 3U CubeSat would provide the first in-orbit validation of net positive thrust.
JAXA: Integrated ABEP payload on 6U CubeSat demonstrates net positive thrust above drag at 250 km altitude by late 2027
Sources (3)
- [1]Primary Source(https://arxiv.org/abs/2607.02635)
- [2]Supporting Source(https://www.esa.int/Enabling_Support/Space_Engineering_Technology/Atmosphere_Breathing_Electric_Propulsion)
- [3]Supporting Source(https://doi.org/10.1016/j.actaastro.2022.03.015)