This paper reports comparative experiments with two novel and one conventional thrust control algorithms for the unsteady (transient) control of thrust generated by conventional bladedpropeller marine thrusters. First, comparative experiments with three different thrust control algorithms over a wide range of unsteady operating conditions suggest that model-based control algorithms offer transi...

The hyperbolic-equation system (HES) approach is applied to the calculation of a Hall thruster using the hybrid particle-in-cell (PIC) method. The HES approach enables accurate computations of magnetized electron fluids in quasi-neutral plasmas with a simple structured mesh. SPT-100 thruster is assumed as the calculation condition. The calculation results indicate that the Bohm criterion is sat...

Related Articles Electric field measurement in microwave discharge ion thruster with electro-optic probe Rev. Sci. Instrum. 83, 124702 (2012) Compact high-speed reciprocating probe system for measurements in a Hall thruster discharge and plume Rev. Sci. Instrum. 83, 123503 (2012) On physical interpretation of two dimensional time-correlations regarding time delay velocities and eddy shaping Phy...

This paper aims to characterize the Hall-thruster plasmadynamics in the framework of multi uidmodel. Effect of the ionization and the recombination has been included in the present model. Based on the experimental data, a third-order polynomial in electron temperature is used to calculate the ionization rate. The neutral dynamics is included only through the neutral continuity equation in the ...

In this paper, a closed-loop switching function for on-off thruster firings is proposed to provide good attitude control performance in the presence of modeling errors for single-axis slew maneuver of a rigid spacecraft and to eliminate double-sided thruster firings. The size of a single-sided deadband in the switching function provides the capability of a tradeoff between maneuver time and fue...

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THERE has been significant work recently in the development of iodine-fed Hall thrusters for in-space propulsion applications.1 The use of iodine as a propellant provides many advantages over present xenon-gas-fed Hall thruster systems. Iodine is a solid at ambient temperature (no pressurization required) and has no special handling requirements, making it safe for secondary flight opportunitie...

Abstract The H2020 MINOTOR project focused on the study and optimization of ECRA thruster, an electric propulsion system for satellites. First, a 30 W prototype this Electron Cyclotron Resonance Thruster (ECRT) is optimized. Then, 200 design based these findings. performances both prototypes were assessed at two different facilities: ONERA in France Justus Liebig University Germany. Significant...