
A plasma chemistry study on global model for argon gas as a propellant to electrostatic gridded ion thruster
accounting the effects of metastable species and implementing new terms in the gas power balanceBy Bernardo Vieira MagaldiLength2h 14m
About this audiobook
Electric propulsion optimizes propellant mass and meets new propulsion device demands. These devices adjust satellite orbits and enable long missions. Among various thrusters, electrostatic ones have well-defined physics, simplifying operational parameter optimization. This study developed a global model for an Inductively Coupled Plasma (ICP) cylindrical ion thruster with an output polarized grid system. Argon propellant is injected into the chamber, and ICP plasma is generated by a radiofrequency current. Neutral and excited species are accelerated out by diffusion, while ionized species are accelerated via the polarized grids' electric field. The polarized grid system was optimized for better plasma sheath use. The model considers single and multi-step ionization, the Electron Energy Distribution Function (EEDF), neutral gas, and electron power balance equations. Excited species influence ionization energy, but not ionic density. However, the ion substitution rate increases, essential for thrust and specific impulse. The model determines the neutral gas temperature by considering the power balance and interactions with other species.
Audiobook details
GenreBusiness and Economics
Length2 hrs 14 mins
Narrated byListen with 1,000+ voices
FormateBook with Audio
Publish dateJul 31, 2024
LanguageEnglish
Table of contents
1Introduction
283.2 COLLISIONAL PROCESSES AND PLASMA CHEMISTRY
21 INTRODUCTION
293.3 ELECTRON ENERGY DISTRIBUTION FUNCTION (EEDF)
32 INTRODUCTION TO ELECTRIC PROPULSION
303.4 SHEATH REGION
42.1 SPACE PROPULSION SYSTEMS
314 GLOBAL MODEL
52.1.1 Electrothermal Thrusters
324.1 GENERAL THEORY
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62.1.1.1 Resistojet
334.2 DESCRIPTION OF THE GLOBAL MODEL
72.1.1.2 Arcjet
344.2.1 Thruster Chamber Geometry
82.1.2 Electromagnetic Thrusters
354.2.2 Particle Balance
92.1.2.1 Pulsed Plasma Thruster (PPT)
364.2.3 Neutralization of Positive Ions on Chamber Walls
102.1.2.2 Magnetoplasmadynamic Thruster (MPD)
374.2.4 Neutral Recombination and Metastable Extinction on Chamber Walls
112.1.3 Electrostatic Thrusters
384.2.5 Neutral Gas Power Balance
122.1.3.1 Hall Effect Thruster (HET)
394.2.6 Electron Power Balance
132.1.3.2 Field Emission Electric Propulsion and Electrospray Thruster
404.2.7 Coil Analysis
142.1.3.3 Gridded ion Thruster
414.2.8 Ar Plasma Modeling Reactions
152.2 EQUATIONS AND BASIC CONCEPTS OF PROPULSION
424.3 THRUSTER THEORY
162.2.1 Thrust
434.3.1 Thrust and Power of the jet ( and )
172.2.2 Specific Impulse
444.3.2 Specific Impulse
182.2.3 Rocket Equation and Delta –
454.3.3 Efficiencies and Thrust-to-Power Ratio and
192.2.4 Power of the jet
465 RESULTS AND DISCUSSION
202.2.5 Mass Utilization Efficiency
475.1 CHILD-LANGMUIR LIMIT
212.2.6 Electrical Efficiency
485.2 PLASMA CHEMISTRY’S ANALYSIS
222.2.7 Inductive Coupling Power Transfer Efficiency
495.3 PROPULSION PARAMETERS ANALYSIS
232.2.8 Thrust-to-power Ratio
505.4 INPUT FLOW’S CONSIDERATIONS
242.2.9 Total Efficiency
515.5 GRID PARAMETERS CONSIDERATIONS
252.3 SOME THRUSTER COMPONENTS: 2.3.1 Propellants
526 CONCLUSION
263 BASIC CONCEPTS OF PHYSICS OF PLASMA
537 FUTURE WORKS
273.1 WHAT IS PLASMA