Numerical Simulation of One Dimensional Pulsed Plasma Thruster with Solid Propellant

The pulsed plasma Thruster has been the first thruster in the space mission. In the thrusters, based on discharging electrical capacitor and passing high current between the anode and cathode, fuel is isolated, then by using self-field magnetic and applying Lorentz force to the plasma particles and with accelerating them the thrust force is generated. In the research a one dimensional Pulsed Plasma Thruster has been investigated. The applied numerical solution is based on Einfeldt, Harten, Lax, Van Leer, (HLLE) numerical method which has the adequate accuracy. In the simulation Hall effects, ionization process, heat transfer, and viscosity have been neglected. Governing equation for a magnetic accelerator has been solved. The represented solution results include distribution of density, velocity, pressure, and magnetic field during the magnetic accelerator which compared with similar numerical results was satisfactory. A Pulse Plasma Thruster has been numerically analyzed. The results related to density, pressure, magnetic field, and velocity curves have been compared with the desire physical behavior, which were satisfactory. Also graph of distribution of Teflon temperature after reaching to the ablation temperature, by applying heat energy from plasma area, has adequate compatibility with reference.