First end-to-end technological demonstration of a water electrolysis hall effect thruster operating with a water electrolyser
File(s)
Author(s)
Type
Conference Paper
Abstract
The first end-to-end technological demonstration of a Hall Effect Thruster operating on the products of water electrolysis directly produced by a water electrolyser is presented. Here, the anode (thruster) consumes the oxygen while the cathode is fuelled by hydrogen, produced at the equivalent stoichiometric ratio. The complexity of operating on the potentially explosive ratios of oxygen and hydrogen required significant modifications of the vacuum facilities and the procedures which are typically used for inert propellants. This involved a careful pump selection, implementation of diverse purging systems, and refining the water electrolyser fluidics, all of which are detailed herein. The results of the test demonstrate the independent ignition
capabilities of the cathode using hydrogen, and the operation of the entire system comprising the water electrolyser and the Hall Effect Thruster with the cathode. Notably, the gas wetness from the water electrolyser significantly influenced the discharge’s stability, emphasising the necessity to fuel the anode and the cathode with dry gases for in-orbit technology demonstrations. It is estimated that the water electrolyser power consumption will only account for only 8% of the
total system power considering the worst-case scenario, with the substantial majority of 83% potentially being accounted for by the thruster’s anode discharge.
capabilities of the cathode using hydrogen, and the operation of the entire system comprising the water electrolyser and the Hall Effect Thruster with the cathode. Notably, the gas wetness from the water electrolyser significantly influenced the discharge’s stability, emphasising the necessity to fuel the anode and the cathode with dry gases for in-orbit technology demonstrations. It is estimated that the water electrolyser power consumption will only account for only 8% of the
total system power considering the worst-case scenario, with the substantial majority of 83% potentially being accounted for by the thruster’s anode discharge.
Date Acceptance
2024-06-23
Copyright Statement
© 2024 The Author(s).
Source
The 38th International Electric Propulsion Conference (IEPC)
Publication Status
Published
Start Date
2024-06-23
Finish Date
2024-06-28
Coverage Spatial
Toulouse, France