Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster
AbstractLiquid propellants are fast becoming attractive for pulsed plasma thrusters due to their high efficiency and low contamination issues. However, the complete plasma interaction and acceleration processes are still not very clear. Present paper develops a multi-layer numerical model for liquid propellant PPTs (pulsed plasma thrusters). The model is based on a quasi-steady flow assumption. The model proposes a possible acceleration mechanism for liquid-fed pulsed plasma thrusters and accurately predicts the propellant utilization capabilities and estimations for the fraction of propellant gas that is completely ionized and accelerated to high exit velocities. Validation of the numerical model and the assumptions on which the model is based on is achieved by comparing the experimental results and the simulation results for two different liquid-fed thrusters developed at the University of Tokyo. Simulation results shows that up-to
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Misra, K. Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster. Aerospace 2018, 5, 13.
Misra K. Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster. Aerospace. 2018; 5(1):13.Chicago/Turabian Style
Misra, Kaartikey. 2018. "Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster." Aerospace 5, no. 1: 13.
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