Abstract This work aims to develop a self-consistent modeling framework for the design of a helicon plasma thruster. A 0D global design model of the thruster is first developed to identify the main operational conditions of the thruster, starting from a targeted performance in terms of specific impulse and thrust. These operational conditions are tested with dedicated simulations on the electromagnetic plasma-wave interaction within the ionization chamber, and on the electrostatic plasma acceleration within the magnetic nozzle. The former are carried out with a finite element electromagnetic code and confirm the technical feasibility of the identified operational RF power with a predefined chamber geometry. The latter are obtained with an electrostatic particle-in-cell code, which allows to estimate more precisely the achieved thruster performance. A sub-optimal thruster with an absorbed plasma power of around 1 kW, a thrust of about 10 mN and a specific impulse higher than 1000 s is successfully simulated, and the accuracy of the simplified 0D model in the prediction of the thruster performance is estimated. The built simulation framework will serve as the basis for the next optimization of the thruster geometry and operational conditions, with the ultimate goal of building and testing a new helicon thruster prototype.
Iannarelli et al. (2025) studied this question.