A Hall thruster ionizes propellant in a crossed E×B field and accelerates ions axially out of an annular ceramic (BN/BN-SiO₂) channel. Some ions strike the channel wall instead of the exit plane, sputtering away ceramic — the dominant wear-out mechanism that ends a thruster's operating life (SPT-100-class units are qualified to roughly 7,000–10,000 hours this way).
The local ion impact energy follows the plasma potential profile, which drops mostly near the exit:
E(u) = V_d · f(u), f(u) = exp( -((u-0.82)/0.14)² )
u = axial position, 0 (anode) → 1 (exit plane)
Sputtering yield uses a Bohdansky-type threshold law — no erosion below a threshold energy E_th, rising smoothly above it:
Y(E) = Y_max · (1 − E_th/E)² for E > E_th, else 0
Local ion current density follows a similar near-exit-peaked profile J(u), scaled by mass flow rate. Erosion depth accumulates as:
dδ/dt = C · Y(E(u)) · J(u) [wall recession, mm/hour]
End of life: δ_max(u) ≥ wall thickness (3.0 mm)
- Discharge Voltage — higher V pushes ion impact energy further above threshold, sharply raising sputtering yield.
- Mass Flow Rate — sets ion current density reaching the wall; erosion rate scales roughly linearly with it.
- Propellant — Xenon sputters BN more efficiently (lower threshold, higher yield) than the lighter Krypton now used on some mega-constellation thrusters, at the cost of a slightly lower Isp.
- Mission Clock Speed — compresses thousands of real operating hours into a watchable session.
This is a simplified engineering model (constants tuned to plausible orders of magnitude, not a specific qualification dataset) meant to show why erosion — not propellant exhaustion — is what typically retires a Hall thruster.