Propulsion performance of a microcavity discharge device

This work explores the requirements for an effective nanosatellite propulsion system. A candidate system is proposed in the form of a microcavity discharge device modified for use as an electrothermal thruster, called a MCD thruster. Development of the MCD thruster was primarily experimental in nature, although computational modeling provided validation and suggested future development paths. Three types of tests were performed to validate the performance of the MCD thruster. Thrust measurements validated the performance of an integral supersonic nozzle and provided an estimate of the thrust coefficient obtainable in a fully developed system. Paschen minimum breakdown measurements provided insight into the fundamental physics of the MCD thruster and suggested an optimal voltage amplitude. Heating and thermal efficiency tests indicated the MCD thruster is capable of meeting the performance requirements for a nanosatellite propulsion system.

Name thesis:degree_name

M.S.

Level thesis:degree_level

Thesis

Discipline thesis:degree_discipline

Aerospace Engineering

Grantor

University of Illinois at Urbana-Champaign

Year dc:date

2011

Author dc:creator

• de Chadenedes, Mark L.

Contributors dc:contributor

• Burton, Rodney L.

• Microcavity
• discharge
• thruster
• microcavity discharge
• microcavity discharge thruster
• electrothermal
• electrothermal thruster
• plasma
• plasma thruster

Statement dc:rights

• Copyright 2011 Mark de Chadenedes

Language dc:language

en

Handle dc:identifier

http://hdl.handle.net/2142/24167

OAI identifier oai:identifier

oai:www.ideals.illinois.edu:2142/24167