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- W2335384148 abstract "In the framework of the ”Helicon Plasma Thruster for Space Missions AO7048” research program, a zero-dimensional numerical model is developed in order to assess the propulsive performances of the plasma thruster when fed with different molecular gases as propellants. The zero-dimensional model developed consists of detailed kinetic schemes for bulk plasma reactions and surface processes; particle in cell simulations are performed to properly describe the behaviour of the charged particles at the exhaust plume so to obtain exhaust parameters for the global model. Given a set of input parameters, such as geometry and mass flow rate, the model is able to follow the time evolution of plasma main physical quantities, such as neutral and charge densities and the electron temperature, and to calculate thruster performances. The model is then linked to the genetic algorithm optimization toolbox in Matlab environment in order to obtain high performance configurations. Propellants considered are H2, O2, N2 and N2O." @default.
- W2335384148 created "2016-06-24" @default.
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- W2335384148 date "2014-07-28" @default.
- W2335384148 modified "2023-09-25" @default.
- W2335384148 title "Modelling and Optimization of Electrode-less Helicon Plasma Thruster with Different Propellants" @default.
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- W2335384148 doi "https://doi.org/10.2514/6.2014-3404" @default.
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