Modeling and Parametric Performance Analysis of Field Emission Electric Propulsion

Table of Contents

1 Introduction

1.1 Motivation

1.2 Electric propulsion overview

1.2.1 Rocket equation

1.2.2 Specific impulse

1.2.3 Energy and thrust efficiency

1.2.4 Types of electric propulsion

1.2.5 General application of EP

1.3 Thesis objectives and contributions

1.4 Thesis scope and outline

2 FEEP background and literature review

2.1 Field emission theory

2.1.1 Emitter critical current and impedance

2.1.2 Emitter onset voltage and Taylor cone

2.1.3 Emitter surface stability

2.2 Filed emission electric propulsion overview

2.2.1 FEEP thruster description

2.2.2 FEEP mission application

2.2.3 FEEP operational consideration

3 Field Emission Electric Propulsion modeling

3.1 Modeling Overview

3.1.1 Shape propellant flow model

3.1.2 Propellant flow equation of motion

3.1.3 Ion formation model

3.2 FEEP thruster preliminary design

3.2.1 Thruster head component

3.2.2 Propellant tank components

3.2.3 Electronics (DCIU/PPU)

3.2.4 Cathode neutralizer component

3.2.5 FEEP thruster 3D model assembly

3.2.6 FEEP thruster integration with CubeSat

4 Parametric analysis of FEEP system

4.1 Performance parametric analysis

4.1.1 Thrust change of FEEP over time

4.1.2 Thrust change of FEEP over voltage

4.2 FEEP thruster design parameter optimization

4.2.1 Crown emitter topology optimization

5 Conclusion and future work

5.1 Summary

5.2 Future work

Objectives and Topics

This thesis aims to develop a comprehensive mathematical and 3D CAD model of a Field Emission Electric Propulsion (FEEP) system to analyze its parametric performance. The research focuses on identifying how various thruster parameters, such as propellant type and electrical voltage, influence the overall efficiency, thrust output, and operational stability of the thruster in micro-satellite environments.

• Mathematical modeling of Field Emission Electric Propulsion systems.
• 3D CAD design and structural topology optimization of FEEP thruster components.
• Parametric performance analysis concerning propellant mass, exhaust velocity, and ion flow.
• Investigation of operational requirements for micro-satellite integration.

Excerpt from the Book

Summary of Chapters

1 Introduction: Provides an overview of space electric propulsion, discusses the current motivations for miniaturized propulsion systems, and outlines the research objectives.

2 FEEP background and literature review: Establishes the theoretical foundation for field emission thrusters, covering ion source mechanisms, Taylor cone physics, and existing thruster technologies.

3 Field Emission Electric Propulsion modeling: Details the mathematical modeling of propellant flow and ion formation, alongside the preliminary 3D design of FEEP components.

4 Parametric analysis of FEEP system: Presents the results of simulation studies regarding thrust variations over time and voltage, and discusses topology optimization of the crown emitter.

5 Conclusion and future work: Summarizes the thesis findings and suggests potential future improvements, such as advanced optimization algorithms for thruster design.

Keywords

CubeSat, Electric Propulsion, Emitter, FEEP, Thruster, Satellite, Spacecraft, Field Emission, Taylor Cone, Ion Source, Modeling, Parametric Analysis, Topology Optimization, Propellant Flow, Micro-propulsion

Frequently Asked Questions

What is the primary focus of this research?

The work focuses on the mathematical modeling and parametric performance analysis of Field Emission Electric Propulsion (FEEP) systems designed for small satellite applications.

What are the key themes addressed in the thesis?

Key themes include field emission physics, propulsion system design, 3D structural modeling, and performance optimization based on propellant and electrical inputs.

What is the main objective of this study?

The primary goal is to provide a comprehensive model of a FEEP thruster and to analyze how different design parameters affect its propulsion performance.

Which scientific methodology is utilized?

The research employs a combined approach of theoretical fluid dynamics modeling, 3D CAD design, and numerical parametric simulations to evaluate thruster behavior.

What topics are covered in the main body?

The main body covers field emission theory, the specific operational requirements for FEEP thrusters, 3D design concepts, and performance simulations under various scenarios.

How would you characterize this work through keywords?

The work is characterized by terms such as FEEP, CubeSat, Field Emission, Thruster, Ion Source, and Parametric Analysis.

Why is the Taylor cone essential to the FEEP system?

The Taylor cone is the physical structure formed by the liquid metal propellant under an intense electric field, which enables the stable field evaporation of ions at the apex.

What is the significance of the crown emitter in this study?

The crown emitter is a critical component that allows for multiple emission sites, facilitating higher thrust output while maintaining the compact size requirements of CubeSats.