University of Illinois Urbana-Champaign

Characterization of a multimode propellant operating in a porous glass electrospray thruster

Adduci, Anthony

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ADDUCI-THESIS-2023.pdf

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https://hdl.handle.net/2142/120091

Description

Title
Characterization of a multimode propellant operating in a porous glass electrospray thruster
Author(s)
Adduci, Anthony
Issue Date
2023-04-26
Director of Research (if dissertation) or Advisor (if thesis)
Rovey, Joshua
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)
Multimode, electrospray, porous glass
Abstract
Multimode space propulsion is an emerging technology that shows a promising increase in mission flexibility, adaptability, and mass savings for specific missions [1]. Finding a propellant that operates well in multiple propulsive modes is a key step in getting multimode propulsion systems flying in space. This study characterizes a novel multimode propellant named FAM-110A through operation in a porous glass electrospray thruster. Measurements acquired include current-voltage characteristic curves, plume ion potential via a retarding potential analyzer, and mass to charge ratio via a linear time of flight spectrometer. FAM-110A emitted more current at comparable emitter voltages as compared to EMIM-BF4. Currents of 422 μA and 305 μA were observed at voltages of +1760 V and -1730 V respectively. RPA measurements showed less field free fragmentation during thruster operation with FAM-110A and also a 0.9% average energy efficiency. During cation emission, it was found that the FAM-110A plume consists of primarily the EMIM cation with no observable evidence of the presence of HA+. Many species were found to exist in the negative emission plume including the two know anions: nitrate, and ethylsulfate. Performance parameters were calculated for each propellant. The calculations showed the thruster operating with FAM-110A produced 3.9 μN and 9.1 μN more thrust in cation and anion emission, respectively. The specific impulse of FAM-110A was 1412 seconds lower in positive mode and 1485 seconds lower in negative mode. The calculated propulsive efficiency for FAM-110A was 35.9% lower during positive mode and 21.2% lower during negative mode when compared to EMIM-BF4.
Graduation Semester
2023-05
Type of Resource
Thesis
Handle URL
https://hdl.handle.net/2142/120091
Copyright and License Information
Copyright 2023 Anthony Adduci

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