NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsIodine Propellant Feed System Flow ModelingThe use of solid iodine as a propellant in Hall-effect thrusters (HETs) is currently being investigated for small-satellite applications. CubeSats offer an inexpensive mode of access to space; however, they currently lack significant propulsion capability. A high specific impulse (I (sub sp)) propulsion system would permit a significant change in velocity, delta v, to be imparted for orbital maintenance, transfers, or de-orbit maneuvers. An electric propulsion system that uses iodine as a propellant has a number of advantages. It has an exceptionally high rho times I (sub sp) figure of merit (density multiplied by the specific impulse), meaning that it can achieve a large total delta v with a relatively low combination of propellant mass and propellant tank volume. Also, the propellant feed system operates at low pressures (a few psia at most), as opposed to the use of super-critical xenon stored at very high pressure. Low pressure operation can lower system mass while greatly reducing the risk of propellant tank rupture, making low pressure a vitally important property for propellants on secondary payloads like CubeSats, where risks must be minimized. The iSAT mission aims to demonstrate iodine-fed HET technology, flying it in space onboard a 12U 912-unit) CubeSat. In the iSAT propellant feed system (PFS), solid iodine is sublimed through heating to produce gaseous propellant that is conducted through tubing to the thruster and cathode. The sublimation process is governed by the iodine (I2) vapor pressure, which is shown as a function of temperature in figure 1. As gaseous I2 flows out of the tank, the gas pressure in the volume containing the solid iodine propellant is reduced until a balance between the flow of iodine out of the tank and the sublimation rate of solid iodine at the equilibrium gas pressure and chosen tank temperature is reached.Document ID20180006416Acquisition SourceMarshall Space Flight CenterDocument TypeTechnical Memorandum (TM)AuthorsMartin, A. K.*(NASA Marshall Space Flight Center Huntsville, AL, United States)*Sawicki, P.*(NASA Internships, Fellowships, Scholarships (NIFS) Program Huntsville, AL, United States)*Polzin, K. A.*(NASA Marshall Space Flight Center Huntsville, AL, United States)*Date AcquiredOctober 17, 2018Publication DateOctober 1, 2018Subject CategoryPropellants And FuelsReport/Patent NumberM-1474M18-6867NASA/TM-2018-220124Distribution LimitsPublicCopyrightWork of the US Gov. Public Use Permitted.Available DownloadsNameType20180006416.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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