Abstract In this preprint, an extensive preliminary study of the design, mathematical modelling and efficiency metrics of an advanced electric plasma propulsion engine suitable for deep space interplanetary missions is presented. Electromagnetic and electrostatic acceleration of plasma provide a high specific impulse option that can provide sustained high efficiency thrust profiles essential for next generation missions to the outer solar system when chemical propellants reach their theoretical thermodynamic limits. Project Scope & Methodology The main research areas are the magnetohydrodynamic (MHD) equations that describe the acceleration and containment of plasma. The study compares the ionization efficiency, magnetic nozzle topology and power to thrust conversion ratios to set the theoretical groundwork for maximizing propellant use with minimizing the thermal degradation of the engine architecture. There is a wide range of calculation and analysis areas of focus: Plasma Ionization Dynamics: Mathematical calculation of gas to plasma phase transition and optimizing electron temperature.Electromagnetic Acceleration Models: Lorentz Force Application in Different Magnetic Field Configurations for the Highest Exhaust Velocity.Efficiency Optimization: Thrust to power curves derived theoretically under simulated deep space conditions. Research Timeline & Status The theoretical framework, mathematical modeling and preliminary manuscript compilation were finished in December 2025. The design baseline is an open-access preprint, which will be used as a physical design guideline and experimental hardware validation for the ongoing design.
Sai Venkata Aadithya Nizampatnam (Mon,) studied this question.
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