Electron temperature effects on pulsed plasma thruster plume expansion

Gatsonis, Nikolaos A.; Gagne, Michael

doi:10.2514/6.2000-3428

Search citation statements

Order By: Relevance

Paper Sections

Select...

Numerical Simulation Of the 3-d Unsteady Neutral Partic1

Citation Types

Supporting

Mentioning

Contrasting

Year Published

2001

2024

Publication Types

Select...

Article2

Book1

Relationship

Self Cite0

Independent3

Authors

Journals

Cited by 3 publications

(1 citation statement)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The electric potential of the reference point at the inlet is set to 0 Volts, so the values of the electric potential solved by the Boltzmann relation are negative. Since both the electric potential and the electron number density in (4) are based on the mesh nodes, the area weighting method [18]- [19] needs to be used so that the electric charges of the ions can be distributed to the mesh nodes. The variable hard sphere (VHS) model [9] is used for the collisions between neutral particles.…”

Section: Numerical Simulation Of the 3-d Unsteady Neutral Particmentioning

confidence: 99%

Numerical Simulation of the Chemical Combination and Dissociation Reactions of Neutral Particles in a Rarefied Plasma Arc Jet

Ingham

et al. 2017

IEEE Trans. Plasma Sci.

View full text Add to dashboard Cite

Section: Numerical Simulation Of the 3-d Unsteady Neutral Particmentioning

confidence: 99%

Numerical Simulation of the Chemical Combination and Dissociation Reactions of Neutral Particles in a Rarefied Plasma Arc Jet

Ingham

et al. 2017

IEEE Trans. Plasma Sci.

View full text Add to dashboard Cite

Introduction

Wu,

Li,

Zhao

et al. 2024

Numerical Simulation of Pulsed Plasma Thruster

View full text Add to dashboard Cite

The advantages of pulsed plasma thrusters (PPTs), the first type of electric propulsion system for space applications, include their low-power consumption, fast response, simple structure, easy integration, convenient control, and precise and controllable thrust, making them especially suitable for tasks such as microsatellite attitude control, position keeping, orbit raising, and formation flying. In recent years, with the increase in microsatellite applications, the demand for advanced on-orbit propulsion technologies for use in microsatellites has increased. Therefore, PPT research and applications have received widespread attention, becoming a hot topic and an important research direction in microsatellite propulsion technologies (Yang et al. in J Rocket Propul 32:32–36, 2006).

show abstract