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 Magaldi
Length2h 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
21 INTRODUCTION
32 INTRODUCTION TO ELECTRIC PROPULSION
42.1 SPACE PROPULSION SYSTEMS
52.1.1 Electrothermal Thrusters
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62.1.1.1 Resistojet
72.1.1.2 Arcjet
82.1.2 Electromagnetic Thrusters
92.1.2.1 Pulsed Plasma Thruster (PPT)
102.1.2.2 Magnetoplasmadynamic Thruster (MPD)
112.1.3 Electrostatic Thrusters
122.1.3.1 Hall Effect Thruster (HET)
132.1.3.2 Field Emission Electric Propulsion and Electrospray Thruster
142.1.3.3 Gridded ion Thruster
152.2 EQUATIONS AND BASIC CONCEPTS OF PROPULSION
162.2.1 Thrust
172.2.2 Specific Impulse
182.2.3 Rocket Equation and Delta –
192.2.4 Power of the jet
202.2.5 Mass Utilization Efficiency
212.2.6 Electrical Efficiency
222.2.7 Inductive Coupling Power Transfer Efficiency
232.2.8 Thrust-to-power Ratio
242.2.9 Total Efficiency
252.3 SOME THRUSTER COMPONENTS: 2.3.1 Propellants
263 BASIC CONCEPTS OF PHYSICS OF PLASMA
273.1 WHAT IS PLASMA
283.2 COLLISIONAL PROCESSES AND PLASMA CHEMISTRY
293.3 ELECTRON ENERGY DISTRIBUTION FUNCTION (EEDF)
303.4 SHEATH REGION
314 GLOBAL MODEL
324.1 GENERAL THEORY
334.2 DESCRIPTION OF THE GLOBAL MODEL
344.2.1 Thruster Chamber Geometry
354.2.2 Particle Balance
364.2.3 Neutralization of Positive Ions on Chamber Walls
374.2.4 Neutral Recombination and Metastable Extinction on Chamber Walls
384.2.5 Neutral Gas Power Balance
394.2.6 Electron Power Balance
404.2.7 Coil Analysis
414.2.8 Ar Plasma Modeling Reactions
424.3 THRUSTER THEORY
434.3.1 Thrust and Power of the jet ( and )
444.3.2 Specific Impulse
454.3.3 Efficiencies and Thrust-to-Power Ratio and
465 RESULTS AND DISCUSSION
475.1 CHILD-LANGMUIR LIMIT
485.2 PLASMA CHEMISTRY’S ANALYSIS
495.3 PROPULSION PARAMETERS ANALYSIS
505.4 INPUT FLOW’S CONSIDERATIONS
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