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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 balance
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 balance
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 balance
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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 balance

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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.
LanguageEnglish
PublisherEditora Dialética
Release dateJul 31, 2024
ISBN9786527011767
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 balance

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    A plasma chemistry study on global model for argon gas as a propellant to electrostatic gridded ion thruster - Bernardo Vieira Magaldi

    capaExpedienteRostoCréditos

    Ad maiorem Dei gloriam

    ACKNOWLEDGMENTS

    Em primeiro lugar, à Deus, o fim último do ser humano, que por Sua vontade divina que me concedeu a vida, para alegria de meus pais, Francisco José Brum Magaldi e a Rosana Margareth Vieira Magaldi. A quem agradeço o amor e a presença durante toda minha vida, onde sempre encontro boas conversas, memórias, aconchego e paz; à Cristiane da Silva Correa que na minha ausência de casa é quem recebe a culpa pelas coisas erradas de casa; à Tamires Vogel por fazer cada vez mais parte da minha vida, a você o meu eterno amor e admiração.

    Ao meu orientador, professor Argemiro Soares da Silva Sobrinho, e ao meu coorientador, professor Rodrigo Sávio Pessoa, pela amizade, orientação e confiança depositada na realização deste trabalho de mestrado. Ao professor Rodrigo Sávio Pessoa, devo ainda a gratidão por me apresentar a área de simulação da química de plasmas frios, desde a disciplina de Descargas Elétricas e Plasmas.

    Ao professor do INPE e amigo, Rodrigo Intini Marques, grande entusiasta da propulsão elétrica, que por meio de seu convite para o primeiro Workshop de Propulsão Eletrica do Brasil, em 2019, pude conhecer os dois gigantes da propulsão elétrica no Brasil, o Professor Gilberto Marrega Sandonato e o Professor Jose Leonardo Ferreira; ao Alexandre Martins, que também conheci no Workshop, e foi o responsável pelo contato com o Professor Leonardo.

    Aos amigos do ITA que, de forma direta ou indireta, auxiliaram-me na realização deste trabalho: Dr. Jonas Bianchini Fulindi, Dr. Luis Eduardo Vergueiro Loures da Costa, Dr. Gilberto Petraconi Filho, Dr. Douglas Marcel Gonçalves Leite, Dr. Roberson José da Silva, Dr. Felipe de Souza Miranda, Dr. Cristian Paterniani, Dr. Eduardo Sant’Ana Petraconi Prado, MSc. Júlia Karnopp, Tenente Amós Gonçalves Muricy e Silva, Dr. William Chiappim Junior, Dr. Homero Santiago Maciel, Dr. Armstrong Godoy Junior, Suboficial Newton Adriano Santos Gomes, Dr. Aleandro Ribeiro Marquesi, Dr. Marco Antonio Ridenti, Dr. Renata Guimaraes Ribas, Dr. Tiago Moreira Bastos Campos, MSc. André William Pereira Menezes, Dr. Vanessa Modelski Schatkoski, Dr. Gilmar Patrocínio Thim, Dr. André Luis de Jesus Pereira, MSc. Hebert de Amorim Folli, Dr. Raissa Monteiro Pereira e Paulo Cesar Ultramari Júnior.

    À agência de fomento da CAPES pelos 22 meses de suporte financeiro. E, por fim, gostaria de agradecer todas as pessoas que de alguma forma contribuíram para a finalização deste trabalho.

    dixit autem Maria ecce ancilla Domini fiat mihi secundum verbum tuum et discessit ab illa angelus.

    Lc 1,38

    ABBREVIATIONS AND ACRONYMS LIST

    SYMBOL LIST

    SUMMARY

    Capa

    Folha de Rosto

    Créditos

    1 INTRODUCTION

    2 INTRODUCTION TO ELECTRIC PROPULSION

    2.1 SPACE PROPULSION SYSTEMS

    2.1.1 Electrothermal Thrusters

    2.1.1.1 Resistojet

    2.1.1.2 Arcjet

    2.1.2 Electromagnetic Thrusters

    2.1.2.1 Pulsed Plasma Thruster (PPT)

    2.1.2.2 Magnetoplasmadynamic Thruster (MPD)

    2.1.3 Electrostatic Thrusters

    2.1.3.1 Hall Effect Thruster (HET)

    2.1.3.2 Field Emission Electric Propulsion and Electrospray Thruster

    2.1.3.3 Gridded ion Thruster

    2.2 EQUATIONS AND BASIC CONCEPTS OF PROPULSION

    2.2.1 Thrust

    2.2.2 Specific Impulse

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