Performance of decoupled electroaerodynamic thrusters

Solid-state aerodynamic devices, which use electroaerodynamics (EAD) to produce a propulsive force, have the potential make drones and airplanes significantly quieter may provide benefits in sustainability manufacturability. In these ions are accelerated between two electrodes by an electric field, colliding with neutral air molecules producing ionic wind thrust force. The authors' previous work showed that “decoupled” device architecture, separates ionization ion acceleration processes, can increase density thrust-to-power compared prevailing corona-discharge-based EAD uses single DC for both processes. However, discharge characteristics of this decoupled architecture not been previously determined. Here, we experimentally characterize thruster wire-to-wire dielectric barrier (DBD) source: AC voltage drives DBD, ionizes at emitting electrode, while separate accelerates toward collecting electrode. We determine (i.e., DC-current-to-DC-voltage relationship) as well model interaction stages: find former takes same functional form analytical solution space-charge limited current thin collisional channel, whereas latter is determined primarily power draw DBD stage. present complete thrusters, enabling their quantitative design optimization aircraft propulsion other applications.