Hall Effect Thruster Efficiency Calculator
Spacecraft electric propulsion: Model Hall Effect Thruster ($HET$) electromagnetic performance, thrust ($T$), anode efficiency ($\eta_a$), and propellant mass utilization.
Electrical Discharge Parameters
Standard Hall thruster voltage ~300–400 V
Total power: P_d = V_d · I_d (~4.5 kW)
Propellant Flow & Magnetic Field
Xenon gas flow through porous anode
Traps electrons (180 G = 18 mT)
Plume cosine loss (typically 20°–25°)
Hall Thruster E×B Mechanics
A strong radial magnetic field ($B_r$) traps electrons in an azimuthal drift ring ($E_z \times B_r$). Heavy ions ($r_{L,i} \gg L$) are unaffected by the magnetic field and accelerate axially through the electric field, bypassing space-charge Child-Langmuir limitations.
Thrust & Specific Impulse
Delivered Thrust (T)
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Anode Specific Impulse (I_sp)
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Efficiency & Electrical Power
Anode Efficiency (η_a)
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T² / (2 · ṁ · P_d)
Discharge Power (P_d)
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V_d · I_d (kW)
Plasma & Utilization Factors
Exhaust Velocity (v_e):
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Mass Utilization (η_m):
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Thrust-to-Power Ratio:
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Electron Larmor Radius (r_L,e):
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