Helicon thruster plasma modeling: Two-dimensional fluid-dynamics and propulsive performances

Journal Article · Mon Apr 15 04:00:00 EDT 2013 · Physics of Plasmas

DOI:https://doi.org/10.1063/1.4798409· OSTI ID:22130482

Ahedo, Eduardo; Navarro-Cavalle, Jaume ^[1]

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1. ETS Ingenieros Aeronauticos, Universidad Politecnica de Madrid, Madrid 28040 (Spain)

An axisymmetric macroscopic model of the magnetized plasma flow inside the helicon thruster chamber is derived, assuming that the power absorbed from the helicon antenna emission is known. Ionization, confinement, subsonic flows, and production efficiency are discussed in terms of design and operation parameters. Analytical solutions and simple scaling laws for ideal plasma conditions are obtained. The chamber model is then matched with a model of the external magnetic nozzle in order to characterize the whole plasma flow and assess thruster performances. Thermal, electric, and magnetic contributions to thrust are evaluated. The energy balance provides the power conversion between ions and electrons in chamber and nozzle, and the power distribution among beam power, ionization losses, and wall losses. Thruster efficiency is assessed, and the main causes of inefficiency are identified. The thermodynamic behavior of the collisionless electron population in the nozzle is acknowledged to be poorly known and crucial for a complete plasma expansion and good thrust efficiency.

• OSTI ID: 22130482
• Journal Information: Physics of Plasmas, Journal Name: Physics of Plasmas Journal Issue: 4 Vol. 20; ISSN PHPAEN; ISSN 1070-664X
• Country of Publication: United States
• Language: English

Related Subjects

70 PLASMA PHYSICS AND FUSION TECHNOLOGY
ANALYTICAL SOLUTION
ANTENNAS
AXIAL SYMMETRY
EFFICIENCY
ELECTRONS
ENERGY BALANCE
FLUID MECHANICS
IONIZATION
NOZZLES
PERFORMANCE
PLASMA
PLASMA CONFINEMENT
PLASMA EXPANSION
PLASMA SIMULATION
POWER DISTRIBUTION
SCALING LAWS
SUBSONIC FLOW
THRUSTERS
TWO-DIMENSIONAL CALCULATIONS