Microcooling Channel Effect on a Monopropellant Microelectromechanical System Thruster Performance
2017; American Institute of Aeronautics and Astronautics; Volume: 33; Issue: 6 Linguagem: Inglês
10.2514/1.b36393
ISSN1533-3876
Autores Tópico(s)Spacecraft and Cryogenic Technologies
ResumoNo AccessTechnical NoteMicrocooling Channel Effect on a Monopropellant Microelectromechanical System Thruster PerformanceJeongmoo Huh and Sejin KwonJeongmoo HuhKorea Advanced Institute of Science and Technology, Daejeon 305-701, Republic of Korea and Sejin KwonKorea Advanced Institute of Science and Technology, Daejeon 305-701, Republic of KoreaPublished Online:30 May 2017https://doi.org/10.2514/1.B36393SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Leomanni M., Garulli A., Giannitrapani A. and Scortecci F., "Propulsion Options for Very Low Earth Orbit Microsatellites," Acta Astronautica, Vol. 133, No. 3, April 2017, pp. 444–454. doi:https://doi.org/10.1016/j.actaastro.2016.11.001 AASTCF 0094-5765 CrossrefGoogle Scholar[2] Haag G. S., Sweeting M. 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TopicsAircraft EnginesCatalysisChemical KineticsCombustion ChambersElectric PropulsionIon ThrusterMonopropellantsNozzlesPropellantPropulsion and PowerRocket EngineRocket PropellantRocketrySpacecraft PropulsionThermochemistry and Chemical KineticsThermophysics and Heat Transfer KeywordsHall Effect ThrusterMonopropellantsMicroelectromechanical SystemsSolid PropellantsCatalystsSmall SatellitesMicropropulsion SystemsChamber PressureElectrical EnergyHigh Aspect RatioAcknowledgmentsThis work was supported by the National Research Foundation of Korea (NRF) grant funded by the Korean government (MSIP) (no. NRF-2015R1A2A1A15055373).PDF Received12 July 2016Accepted13 March 2017Published online30 May 2017
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