Ion Thruster
Course Instructor
Venkittaraman Pallipuram Krishnamani
Abstract
Propulsion systems for long-duration aerospace missions are fundamentally constrained by fuel mass and engine longevity. Ionic propulsion offers a promising alternative by utilizing high-voltage electrostatic ionization to generate thrust with minimal propellant usage. This project presents the design, simulation, and construction of an ion wind propulsion demonstrator, integrated with a microcontroller-based control system for thrust vectoring and performance telemetry.
The propulsion architecture is driven by a multistage high-voltage system designed to achieve a potential difference of approximately 50 kV. The full power stage was modeled in PSpice, beginning with a 5 V DC input stepped up through a DC-DC boost converter feeding a single-transistor self-oscillating flyback resonant driver (informally known as Slayer Circuit), followed by a multi-stage Cockcroft–Walton voltage multiplier. For the physical prototype, a commercial high-voltage module with comparable output characteristics was integrated to comply with campus safety protocols while validating the electrodynamic ionization behavior predicted by simulation. The resulting high-voltage field is applied across a custom emitter–collector grid, stripping electrons from atmospheric gas and accelerating ions to produce ionic wind without moving mechanical components.
A key contribution of this project is the integration of a digital control layer. An Arduino-based microcontroller serves as the primary computing unit, coordinating airflow sensors, electromagnetic field monitoring, and system-status telemetry. The controller implements a closed-loop logic scheme to regulate a servo-actuated vent, enabling adjustable thrust direction. All structural components - including electrode supports, dielectric housing, and vent assemblies - were designed in CAD software and fabricated using 3D printing to ensure precise electrode alignment and safe containment of high-voltage circuitry.
Experimental testing confirmed consistent ionic airflow exceeding 4 m/s, demonstrating the viability of a compact, solid-state propulsion system that merges high-voltage physics with embedded control. The resulting platform provides both a functional thrust demonstrator and a foundation for future research in high-altitude endurance drones, autonomous electrostatic propulsion systems, and next-generation ion wind technologies.
Ion Thruster
Propulsion systems for long-duration aerospace missions are fundamentally constrained by fuel mass and engine longevity. Ionic propulsion offers a promising alternative by utilizing high-voltage electrostatic ionization to generate thrust with minimal propellant usage. This project presents the design, simulation, and construction of an ion wind propulsion demonstrator, integrated with a microcontroller-based control system for thrust vectoring and performance telemetry.
The propulsion architecture is driven by a multistage high-voltage system designed to achieve a potential difference of approximately 50 kV. The full power stage was modeled in PSpice, beginning with a 5 V DC input stepped up through a DC-DC boost converter feeding a single-transistor self-oscillating flyback resonant driver (informally known as Slayer Circuit), followed by a multi-stage Cockcroft–Walton voltage multiplier. For the physical prototype, a commercial high-voltage module with comparable output characteristics was integrated to comply with campus safety protocols while validating the electrodynamic ionization behavior predicted by simulation. The resulting high-voltage field is applied across a custom emitter–collector grid, stripping electrons from atmospheric gas and accelerating ions to produce ionic wind without moving mechanical components.
A key contribution of this project is the integration of a digital control layer. An Arduino-based microcontroller serves as the primary computing unit, coordinating airflow sensors, electromagnetic field monitoring, and system-status telemetry. The controller implements a closed-loop logic scheme to regulate a servo-actuated vent, enabling adjustable thrust direction. All structural components - including electrode supports, dielectric housing, and vent assemblies - were designed in CAD software and fabricated using 3D printing to ensure precise electrode alignment and safe containment of high-voltage circuitry.
Experimental testing confirmed consistent ionic airflow exceeding 4 m/s, demonstrating the viability of a compact, solid-state propulsion system that merges high-voltage physics with embedded control. The resulting platform provides both a functional thrust demonstrator and a foundation for future research in high-altitude endurance drones, autonomous electrostatic propulsion systems, and next-generation ion wind technologies.
