Publication:
Testing N2O/CO2 oxidizer mixtures with paraffin based μaluminum fuels for Mars Ascent Vehicles

dc.contributor.coauthorKarakaş, Hakkı
dc.contributor.departmentDepartment of Mechanical Engineering
dc.contributor.departmentN/A
dc.contributor.kuauthorKarabeyoğlu, Mustafa Arif
dc.contributor.kuauthorKara, Ozan
dc.contributor.kuprofileFaculty Member
dc.contributor.kuprofilePhD Student
dc.contributor.otherDepartment of Mechanical Engineering
dc.contributor.schoolcollegeinstituteCollege of Engineering
dc.contributor.schoolcollegeinstituteGraduate School of Sciences and Engineering
dc.contributor.yokid114595
dc.contributor.yokidN/A
dc.date.accessioned2024-11-09T23:49:22Z
dc.date.issued2019
dc.description.abstractThe objective of this research is to perform experimental test of a hybrid rocket motor by using N2O/CO2 mixture as the oxidizer and paraffin wax as fuel with the addition of metallic powders such as micron size aluminum and magnesium. The impact of 3-micron size aluminum on key performance parameters such as specific impulse (Isp), regression rate (r), and combustion efficiency (ηcomb) has been studied experimentally using a lab scale hybrid motor with 70 mm grain length and 30 mm outer grain diameter. Thermochemical performance of the various propellants studied in this paper are evaluated using NASA’s Chemical Equilibrium Analysis (CEA) software. Numerous tests are performed with N2 O/CO2 mixtures as the oxidizer. CO2 as a saturated liquid is mixed with liquid N2 O between 8 to 30% by mass in order to measure the motor performance characteristics such as average regression rate, r and combustion efficiency, ηcomb. Experiments were performed in the blowdown mode using the self-pressurizing capability of the mixed oxidizer around 45-50 bar. Chamber pressure of the hybrid motor was in the 15-30 bar range. Successful ignition and motor operation of the mixed oxidizer is achieved all the way up to 22% CO2 in the mixture. Initial conclusion from this study indicate that mixing CO2 with N2 O is a viable method of burning CO2 in a practical rocket system for Mars missions.
dc.description.indexedbyScopus
dc.description.issue2019
dc.description.openaccessYES
dc.description.publisherscopeInternational
dc.identifier.doi10.2514/6.2019-3923
dc.identifier.isbn9781-6241-0590-6
dc.identifier.linkhttps://www.scopus.com/inward/record.uri?eid=2-s2.0-85095969025&doi=10.2514%2f6.2019-3923&partnerID=40&md5=7087612b2d1741c2947a030a460f089c
dc.identifier.scopus2-s2.0-85095969025
dc.identifier.urihttps://dx.doi.org/10.2514/6.2019-3923
dc.identifier.urihttps://hdl.handle.net/20.500.14288/14362
dc.keywordsAluminum
dc.keywordsCarbon dioxide
dc.keywordsChemical analysis
dc.keywordsCombustion
dc.keywordsMartian surface analysis
dc.keywordsNASA
dc.keywordsParaffins
dc.keywordsPropulsion
dc.keywordsRockets
dc.keywordsChamber pressure
dc.keywordsChemical equilibriums
dc.keywordsCombustion efficiencies
dc.keywordsExperimental test
dc.keywordsHybrid rocket motors
dc.keywordsKey performance parameters
dc.keywordsMars Ascent vehicle
dc.keywordsMotor performance
dc.keywordsMixtures
dc.languageEnglish
dc.publisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
dc.sourceAIAA Propulsion and Energy Forum and Exposition, 2019
dc.subjectMechanical Engineering
dc.titleTesting N2O/CO2 oxidizer mixtures with paraffin based μaluminum fuels for Mars Ascent Vehicles
dc.typeConference proceeding
dspace.entity.typePublication
local.contributor.authorid0000-0002-5071-6133
local.contributor.authoridN/A
local.contributor.kuauthorKarabeyoğlu, Mustafa Arif
local.contributor.kuauthorKara, Ozan
relation.isOrgUnitOfPublicationba2836f3-206d-4724-918c-f598f0086a36
relation.isOrgUnitOfPublication.latestForDiscoveryba2836f3-206d-4724-918c-f598f0086a36

Files