Investigation on Ammonium Perchlorate Based Electrically Controlled Propellants

dc.contributor.authorFiorenza, Nicholas Paulen
dc.contributor.committeechairYoung, Gregoryen
dc.contributor.committeememberSchetz, Joseph A.en
dc.contributor.committeememberMeadows, Josephen
dc.contributor.departmentAerospace and Ocean Engineeringen
dc.date.accessioned2025-05-28T08:01:36Zen
dc.date.available2025-05-28T08:01:36Zen
dc.date.issued2025-05-27en
dc.description.abstractAn experimental study exploring the ignition behavior of an electrically controlled gel monopropellant (ECGP) composed of an ionically conducting liquid polymer (polyethylene glycol) and ammonium perchlorate (AP) was conducted. Complexation of AP with PEG enabled ion transport when a voltage was applied resulting in ignition. Although the propellant was manufactures by solution casting, the final product contained no solvent as confirmed by thermogravimetric analysis. Several electrode configurations were explored which balanced or limited either oxidation or reduction at the electrodes. Other than when reduction was limited, ignition always occurred at the anode. Limiting reduction resulted in an apparent increase in the bulk resistivity of the propellant which was attributed to enhanced bubble/gas formation at the cathode. The increase in apparent bulk resistivity resulted in enhanced joule heating and a shift in ignition mechanism from predominately electrochemical to thermal. This behavior is supported by analysis of the current data and infrared temperature measurements. The temperature measurements demonstrate that the highest temperatures occur where the processes are limited. The competition between thermally and electrolytically induced ignition and combustion characteristics of the gel polymer electrolyte will be presented in this thesis.en
dc.description.abstractgeneralThere are two main classes of rockets: one that utilizes liquid propellants, and one that utilizes solid propellants. All liquid propellants are susceptible to leaks, and many traditional liquid propellants are both toxic and/or carcinogenic. As for solid propellants, their primary drawbacks are their inability to be throttled and their inability to be easily extinguished, or in other words, once they are lit there is little control. This research investigates an alternative approach in the development of an electrically controlled propellant where the decomposition mechanisms of a polyethylene glycol (PEG) based propellant is investigated. The polymer is incorporated as both a binder and a fuel source with ammonium perchlorate ionic salt as the primary oxidizer. Two different experimental configurations are studied with varying electrode geometries. Under an applied voltage, there are two competing and complementary decomposition mechanisms: thermal and electrochemical, which can be tailored by controlling the surface area of the electrodes to limit the electrochemistry occurring at one side.en
dc.description.degreeMaster of Scienceen
dc.format.mediumETDen
dc.identifier.othervt_gsexam:44024en
dc.identifier.urihttps://hdl.handle.net/10919/134247en
dc.language.isoenen
dc.publisherVirginia Techen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectElectrically Controlled Combustionen
dc.subjectPolymer Electrolytesen
dc.subjectRocket Propulsionen
dc.titleInvestigation on Ammonium Perchlorate Based Electrically Controlled Propellantsen
dc.typeThesisen
thesis.degree.disciplineAerospace Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

Files

Original bundle
Now showing 1 - 1 of 1
Loading...
Thumbnail Image
Name:
Fiorenza_NP_T_2025.pdf
Size:
8.4 MB
Format:
Adobe Portable Document Format

Collections