Atmospheric EAD grid thruster performance: a theoretical–experimental approach on geometry and pressure effects

In this work, a wire-to-grid electroaerodynamic thruster is experimentally investigated in a low-pressure environment. The study explores the influence of electrode gap d and ambient pressure p on thrust density T/A, thrust-to-power ratio T/P, and corona current ic. A dedicated test rig is designed to operate within a low-pressure chamber, which is equipped with diagnostics for thrust and electrical measurements. Experimental results are compared with a revised physical model. The findings validate the theoretical framework and reveal that thruster performance is highly sensitive to both pressure and electrode spacing. Overall performance degrades with decreasing pressure, while optimal values of T/A and T/P require a trade-off in the selection of gap. Measurements of ignition and breakdown voltages further define the operational envelope, showing an expansion with increasing pressure.