International Journal of Science, Engineering and TechnologyAuthors: Dr. S. C. Pandey
Abstract: Electric propulsion encompasses a family of propulsion technologies in which electrical energy is used to accelerate charged particles and generate momentum exchange. This paper presents a study of ionic propulsion with particular emphasis on the distinction between vacuum ion thrusters used for spacecraft and atmospheric electrohydrodynamic (EHD), or electroaerodynamic (EAD), propulsion. In addition, the paper describes the design, construction, and experimental observation of a low-cost laboratory-scale atmospheric ionic thruster model developed as the author's final-semester project in 2023. The experimental model employed a high-voltage electrode assembly consisting of copper-tube emitter elements and a fine-wire collector, together with a compact high-voltage multiplier supplied from a low-voltage rechargeable battery. The atmospheric device operates through corona discharge: ions generated near the high-field emitter are accelerated through the surrounding air and transfer momentum to neutral molecules through ion-neutral collisions. The resulting bulk gas motion is commonly referred to as ionic wind. Three electrode arrangements—pointed, lined, and gridded—were investigated qualitatively and comparatively. Directional ionic airflow was confirmed using a candle-flame visualization method and a digital anemometer. Recorded airflow velocities were approximately 0.4–2.1 m/s under the reported experimental conditions, with the gridded arrangement producing the strongest and most spatially uniform observed flow. Variation of the electrode gap demonstrated the expected trade-off between corona stability, discharge current, electric-field strength, and airflow generation. The paper also reviews the development of space ion propulsion, including NASA's NSTAR technology and subsequent electric-propulsion systems, and discusses recent progress in atmospheric EAD propulsion. The successful flight of a solid-state EAD aircraft demonstrated the feasibility of atmospheric electric propulsion, while later multistage ducted EAD research has substantially increased reported thrust density. The present laboratory model does not attempt to reproduce the performance of a flight-qualified propulsion system; rather, its principal value is educational and experimental, providing a comparatively accessible platform for studying corona discharge, ionic wind, electrode geometry, and electrohydrodynamic momentum transfer.
