Modeling and Parametric Performance Analysis of Field Emission Electric Propulsion

Table of Contents

• Acronyms
• 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
• A List of Appendices
  • A.1 FEEP thruster developmental milestone
  • A.2 Summary of FEEP performance
  • A.3 The preliminary FEEP thruster requirements
  • A.4 Preliminary FEEP thruster component dimensions
  • A.5 Previous FEEP performance test
    • A.5.1 Performance test of single porous Tungsten crown emitter [104]
    • A.5.2 Performance test of cluster of 3 porous Tungsten crown emitter [104]
  • A.6 Space experience of ARCS Indium LMIS thruster
  • A.7 Crown multi-emitter manufacturing process

Objectives & Key Themes

This thesis focuses on the modeling and parametric performance analysis of a Field Emission Electric Propulsion (FEEP) thruster. The overarching goal is to investigate and analyze the thruster's parametric performance through mathematical and 3D CAD modeling, as well as simulation, to understand its behavior with various liquid metal propellants.

• Establish a mathematical model and preliminary design for a FEEP system.
• Investigate the parametric performance of FEEP thrusters using different propellants.
• Analyze the operational considerations and mission applications of FEEP thrusters.
• Optimize the design parameters, particularly the crown emitter topology, for improved performance.
• Utilize MATLAB simulations to study thrust and exhaust velocity variations.

Excerpt from the Book

Chapter Summaries

Chapter 1: Introduction: This chapter provides an introduction to electric propulsion, including its types and applications, as well as the motivation for and contribution of this work.

Chapter 2: FEEP background and literature review: This chapter presents the theoretical foundation for the FEEP thruster, its operating principle, major components, functions, and emitter characteristics.

Chapter 3: Field Emission Electric Propulsion modeling: In this chapter, the mathematical and CAD modeling of major components of the FEEP thruster, with detailed discussions, are provided.

Chapter 4: Parametric analysis of FEEP system: This chapter covers the parametric performance of the field emission electric propulsion system, as well as parametric studies and analysis.

Chapter 5: Conclusion and future work: This chapter summarizes the findings and provides recommendations for future work regarding the FEEP system.

Keywords

CubeSat, electric propulsion, emitter, FEEP, thruster, satellite, spacecraft, modeling, parametric analysis, ion propulsion, Taylor cone, thrust, specific impulse, optimization

Frequently Asked Questions

What is this work generally about?

This thesis focuses on the modeling and parametric performance analysis of a Field Emission Electric Propulsion (FEEP) system, a type of advanced electric propulsion for spacecraft, with a particular emphasis on its design and operational characteristics.

What are the central thematic areas?

The central thematic areas include electric propulsion overview, field emission theory, FEEP thruster design and modeling, parametric performance analysis of FEEP systems, and optimization of thruster components.

What is the primary goal or research question?

The primary goal is to establish a comprehensive mathematical model and a preliminary design for a FEEP system, and to thoroughly investigate its parametric performance using various liquid metal propellants through simulation and analysis.

Which scientific method is used?

The scientific method employed involves mathematical modeling, 3D CAD modeling of the FEEP thruster's components, and parametric performance analysis conducted via MATLAB simulations to study changes in thrust and exhaust velocity.

What is covered in the main part?

The main part of the thesis covers the theoretical background of FEEP, detailed mathematical and CAD modeling of its components, a description of the thruster's design, and a comprehensive parametric analysis of the FEEP system's performance.

Which keywords characterize the work?

Key terms characterizing this work include electric propulsion, FEEP, thruster, modeling, parametric analysis, CubeSat, emitter, satellite, spacecraft, ion propulsion, Taylor cone, thrust, specific impulse, and optimization.

What is a Field Emission Electric Propulsion (FEEP) thruster?

A FEEP thruster is an advanced electrostatic propulsion system that generates thrust by field ionizing a liquid metal and accelerating the resulting ions with a strong electric field. It typically uses liquid metals like caesium or indium as propellant.

What role does the "Taylor cone" play in FEEP operation?

The Taylor cone is a crucial phenomenon in FEEP, referring to the conical shape formed by the liquid metal propellant's free surface at the emitter tip under the combined effects of electrostatic force and surface tension, which facilitates the stable extraction of ions.

How is the FEEP thruster integrated with CubeSats?

The thesis discusses the integration of the FEEP thruster into CubeSat missions, highlighting its low-cost, high-performance capabilities for de-orbiting, orbit control, attitude control, and other advanced maneuvers for small satellites.

What propellants are typically used in FEEP systems?

Common propellants for FEEP systems are liquid metals with low ionization potential and good wetting capabilities, such as caesium, indium, gallium, rubidium, and mercury.