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        <identifier>oai:www.ideals.illinois.edu:2142/132603</identifier>
        <datestamp>2026-02-20</datestamp>
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          <dc:description>Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2026-02-19 without embargo terms</dc:description>
          <dc:description>The student, Justin Shell, accepted the attached license on 2025-12-11 at 16:26.</dc:description>
          <dc:description>The student, Justin Shell, submitted this Thesis for approval on 2025-12-11 at 16:32.</dc:description>
          <dc:description>This Thesis was approved for publication on 2025-12-11 at 17:12.</dc:description>
          <dc:description>DSpace SAF Submission Ingestion Package generated from Vireo submission #23139 on 2026-02-19 at 18:30:18</dc:description>
          <dc:title>Development, thermal analysis, and verification of an inverted pendulum thrust stand</dc:title>
          <dc:creator>Shell, Justin</dc:creator>
          <dc:date>2025-12-11</dc:date>
          <dc:contributor>Rovey, Joshua L</dc:contributor>
          <dc:subject>Inverted pendulum thrust stand</dc:subject>
          <dc:subject>hall thruster</dc:subject>
          <dc:subject>thermal drift</dc:subject>
          <dc:subject>thrust measurements</dc:subject>
          <dc:subject>facility</dc:subject>
          <dc:language>eng</dc:language>
          <dc:description>This thesis presents the construction of a null-style inverted pendulum thrust stand for the University of Illinois at Urbana-Champaign’s Electric Propulsion Laboratory (EPL). Hanging, torsional and inverted pendulum thrust stands are briefly discussed followed by an in-depth discussion of the University of Illinois at Urbana-Champaign’s inverted pendulum thrust stand. Thermal drift was investigated on the thrust stand with component level, sub-system level, and system level testing. Thermal drift data were analyzed and are discussed with recommended mitigation strategies. Relative error was calculated on the thrust stand, and an example relative error calculation was performed for a low power Hall thruster. Facility test setups are discussed with pumping speed experimentally calculated. The SPT-50 and SPT-70 were hot fired and thrust values were measured. The setup and electrical configuration are discussed for the thrusters. Thrust values are then compared with literature to validate the thrust stand.</dc:description>
          <dc:date>2025-12</dc:date>
          <dc:type>Thesis</dc:type>
          <dc:identifier>https://hdl.handle.net/2142/132603</dc:identifier>
          <dc:rights>Copyright 2025 Justin Shell</dc:rights>
          <degree>
            <department>Aerospace Engineering</department>
            <discipline>Aerospace Engineering</discipline>
            <grantor>University of Illinois Urbana-Champaign</grantor>
            <name>M.S.</name>
            <level>Thesis</level>
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