Title page for ETD etd-042607-155701

Document Type thesis

Author Name Krolak, Matthew Joseph

URN etd-042607-155701

Title Optimization of a Magnetoplasmadynamic Arc Thruster

Degree ME

Department Electrical & Computer Engineering

Advisors
Alexander Emanuel, Advisor
Sergey Makarov, Committee Member
Robert Labonte, Committee Member

Keywords
Electric Propulsion
Plasma Thruster
Thruster
MPD

Date of Presentation/Defense 2007-04-26

Availability unrestricted

Abstract
As conventional chemical rockets reach the outer limits of their abilities, significant research is going into alternative thruster technologies, some of which decouple the maximum thrust and efficiency from the propellant’s internal chemical energy by supplying energy to the propellant as needed. Of particular interest and potential is the electrically powered thruster, which promises very high specific thrust using relatively inexpensive and stable propellant gasses. Some such thrusters, specifically ion thrusters, have achieved significant popularity for various applications. However, there exist other classes of electrical thrusters which promise even higher levels of efficiency and performance.
This thesis will focus on one such thruster type – the magnetoplasmadynamic thruster – which uses an ionized propellant flow and large currents to accelerate the propellant gas by electrical and magnetic force interactions. The necessary background will be presented in order to understand and characterize the operation of such devices, and a theoretical model will be developed in order to estimate the levels of performance which can be expected. Simulations will be performed and analyzed in order to better understand the principles on which these devices are designed.
Finally, a thruster package will be designed and built in order to test the performance of the device and accuracy of the model. This will include a high-current power supply, ignition circuit, gas delivery system, and nozzle. Finally, the measured performance of this thruster package will be measured and compared to the theoretical predictions in order to validate the models constructed for this type of thruster.

Files
OPTIMIZATION_OF_A_MAGNETOPLASMADYNAMIC_ARC_THRUSTER.pdf

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Document Type	thesis
Author Name	Krolak, Matthew Joseph
URN	etd-042607-155701
Title	Optimization of a Magnetoplasmadynamic Arc Thruster
Degree	ME
Department	Electrical & Computer Engineering
Advisors	Alexander Emanuel, Advisor Sergey Makarov, Committee Member Robert Labonte, Committee Member
Keywords	Electric Propulsion Plasma Thruster Thruster MPD
Date of Presentation/Defense	2007-04-26
Availability	unrestricted
Abstract As conventional chemical rockets reach the outer limits of their abilities, significant research is going into alternative thruster technologies, some of which decouple the maximum thrust and efficiency from the propellant’s internal chemical energy by supplying energy to the propellant as needed. Of particular interest and potential is the electrically powered thruster, which promises very high specific thrust using relatively inexpensive and stable propellant gasses. Some such thrusters, specifically ion thrusters, have achieved significant popularity for various applications. However, there exist other classes of electrical thrusters which promise even higher levels of efficiency and performance. This thesis will focus on one such thruster type – the magnetoplasmadynamic thruster – which uses an ionized propellant flow and large currents to accelerate the propellant gas by electrical and magnetic force interactions. The necessary background will be presented in order to understand and characterize the operation of such devices, and a theoretical model will be developed in order to estimate the levels of performance which can be expected. Simulations will be performed and analyzed in order to better understand the principles on which these devices are designed. Finally, a thruster package will be designed and built in order to test the performance of the device and accuracy of the model. This will include a high-current power supply, ignition circuit, gas delivery system, and nozzle. Finally, the measured performance of this thruster package will be measured and compared to the theoretical predictions in order to validate the models constructed for this type of thruster.
Files	OPTIMIZATION_OF_A_MAGNETOPLASMADYNAMIC_ARC_THRUSTER.pdf