Propulsion performance of a microcavity discharge device
de Chadenedes, Mark L.
Loading…
Permalink
https://hdl.handle.net/2142/24167
Description
Title
Propulsion performance of a microcavity discharge device
Author(s)
de Chadenedes, Mark L.
Issue Date
2011-05-25T15:02:49Z
Director of Research (if dissertation) or Advisor (if thesis)
Burton, Rodney L.
Department of Study
Aerospace Engineering
Discipline
Aerospace Engineering
Degree Granting Institution
University of Illinois at Urbana-Champaign
Degree Name
M.S.
Degree Level
Thesis
Keyword(s)
Microcavity
discharge
thruster
microcavity discharge
microcavity discharge thruster
electrothermal
electrothermal thruster
plasma
plasma thruster
Abstract
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.
Use this login method if you
don't
have an
@illinois.edu
email address.
(Oops, I do have one)
IDEALS migrated to a new platform on June 23, 2022. If you created
your account prior to this date, you will have to reset your password
using the forgot-password link below.
