NEXT Ion Propulsion System Production Readiness

Hoskins, W. Andrew; Aadland, Randall S.; Meckel, Nicole; Talerico, Leonard; Monheiser, Jeffrey M.

doi:10.2514/6.2007-5856

Cited by 11 publications

(2 citation statements)

References 25 publications

(34 reference statements)

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“…22 Accelerator grid voltages from 500 to 10,000 volts were studied with a maximum discovered at about 2500 V (see figure 3). The simulation was modeled after NASA's NEXT ion thruster 23 , with electron injection beam of 10 Amps, with average velocities for O, Si, Fe of 173000, 133000, and 93000 m/s. The VSim calculated specific energy is approximately 4E7 kJ/kg, compared to the theoretical value of 5.4E4, and represents a worst case.…”

Section: Isotope Separationmentioning

confidence: 99%

Lunar-sourced GEO Powersats: An Integrated ISRU System

Schubert

Anderson

Somera

et al. 2018

2018 AIAA SPACE and Astronautics Forum and Exposition

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Solar power satellites (powersats) can be built almost entirely from lunar resources. When C-class asteroids are also included as ore bodies a complete powersat can be built through in situ resource utilization (ISRU) given appropriate processing and transportation technology. This article provides an in-depth overview of the technical feasibility and economic viability of lunar construction and operations for powersat component construction and delivery to geostationary earth orbit (GEO). Techno-economic analysis suggests a return on investment in seven years assuming a three percent discount rate. Electrical power collected in GEO and beamed to terrestrial receivers by the powersats can be sold as baseload power in the wholesale electricity market to generate revenue. This work presents a complete concept of operations from initial rocket launches to regolith harvesting through transport to GEO. Lunar infrastructure can be constructed of modules to optimize size and weight for launch costs. Future growth can be derived from using ISRU to build additional processing bases. A scaleup in this manner can provide 22% of the world's energy needs by the end of a 20-year period. This work builds upon previous studies and completes the architectural description of predominantly lunar-sourced GEO powersats.

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Section: Isotope Separationmentioning

confidence: 99%

Lunar-sourced GEO Powersats: An Integrated ISRU System

Schubert

Anderson

Somera

et al. 2018

2018 AIAA SPACE and Astronautics Forum and Exposition

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“…5 Each of these units underwent extensive component level testing, completed environmental testing (with the exception of the PPU), and was tested together in system integration testing. [6][7][8][9] The status of the NEXT project, results from IPS component testing, and the results of integration testing can be found in Refs. 5-15. The NEXT thruster service life capability is being assessed through a comprehensive service life validation scheme that utilizes a combination of testing and analyses.…”

Section: Introductionmentioning

confidence: 99%

End-of-test Performance and Wear Characterization of NASA's Evolutionary Xenon Thruster (NEXT) Long-Duration Test

Shastry

Herman²,

Soulas

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The NASA's Evolutionary Xenon Thruster (NEXT) project is developing the nextgeneration solar electric ion propulsion system with significant advancements beyond the state-of-the-art NASA Solar Electric Propulsion Technology Application Readiness (NSTAR) ion propulsion system to provide future NASA science missions with enhanced capabilities. A Long-Duration Test (LDT) was initiated in June 2005 to validate the thruster service life modeling and to quantify the thruster propellant throughput capability. Testing was recently completed in February 2014, with the thruster accumulating 51,184 hours of operation, processing 918 kg of xenon propellant, and delivering 35.5 MN-s of total impulse. As part of the test termination procedure, a comprehensive performance characterization was performed across the entire NEXT throttle table. This was performed prior to planned repairs of numerous diagnostics that had become inoperable over the course of the test. After completion of these diagnostic repairs in November 2013, a comprehensive end-of-test performance and wear characterization was performed on the test article prior to exposure to atmosphere. These data have confirmed steady thruster performance with minimal degradation as well as mitigation of numerous life limiting mechanisms encountered in the NSTAR design. Component erosion rates compare favorably to pretest predictions based on semi-empirical models used for the thruster service life assessment. Additional data relating to ion beam density profiles, facility backsputter rates, facility backpressure effects on thruster telemetry, and modulation of the neutralizer keeper current are presented as part of the end-of-test characterization. Presently the test article for the NEXT LDT has been vented to atmosphere with post-test disassembly and inspection underway. NomenclatureBOL = beginning-of-life CEX = charge exchange CRA = center radius aperture DCA = discharge cathode assembly ELT = extended life test EM = engineering model EM3 = engineering model 3 thruster EPC = end-of-test performance characterization GRC = NASA Glenn Research Center HiPEP = High-Power Electric Propulsion IPS = ion propulsion system J B = beam current, A J NK = neutralizer keeper current, A LDT = long-duration test ̇ = main plenum mass flow rate, sccm ̇ = discharge cathode mass flow rate, sccm 2 ̇ = neutralizer cathode mass flow rate, sccm NCA = neutralizer cathode assembly NEXT = NASA's Evolutionary Xenon Thruster NSTAR = NASA's Solar Electric Propulsion Technology Application Readiness P IN = input power, kW PM = prototype model PPC = post-test performance characterization PPU = power processing unit QCM = quartz-crystal microbalance TL = throttle level TT9 = Throttle Table 9 TT10 = Throttle Table 10 V A = accelerator grid voltage, V V B = beam power supply voltage, V VF = vacuum facility WT = wear test φ = aperture or orifice diameter

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Technology Readiness of the NEXT Ion Propulsion System

Benson

Patterson

2008

2008 IEEE Aerospace Conference

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Abstract-The NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system has been in advanced technology development under the NASA In-Space Propulsion Technology project. The highest fidelity hardware planned has now been completed by the government/industry team, including: a flight prototype model (PM) thruster, an engineering model (EM) power processing unit, EM propellant management assemblies, a breadboard gimbal, and control unit simulators. Subsystem and system level technology validation testing is in progress. To achieve the objective Technology Readiness Level 6, environmental testing is being conducted to qualification levels in ground facilities simulating the space environment. Additional tests have been conducted to characterize the performance range and life capability of the NEXT thruster. This paper presents the status and results of technology validation testing accomplished to date, the validated subsystem and system capabilities, and the plans for completion of this phase of NEXT development. The next round of competed planetary science mission announcements of opportunity, and directed mission decisions, are anticipated to occur in 2008 and 2009. Progress to date, and the success of on-going technology validation, indicate that the NEXT ion propulsion system will be a primary candidate for mission consideration in these upcoming opportunities.

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NEXT Ion Propulsion System Production Readiness

Cited by 11 publications

References 25 publications

Lunar-sourced GEO Powersats: An Integrated ISRU System

Lunar-sourced GEO Powersats: An Integrated ISRU System

End-of-test Performance and Wear Characterization of NASA's Evolutionary Xenon Thruster (NEXT) Long-Duration Test

Technology Readiness of the NEXT Ion Propulsion System

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