Application of the NEXT Ion Thruster Lifetime Assessment to Thruster Throttling

Noord, Jonathan L. Van; Herman, Daniel A.

doi:10.2514/6.2008-4526

Cited by 17 publications

(22 citation statements)

References 14 publications

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“…The NEXT thruster service life analysis is being updated based upon the LDT data and component testing findings as well as being applied for potential mission opportunities to assess thruster wear and performance (Ref. 20).…”

Section: Introductionmentioning

confidence: 99%

NEXT Long-Duration Test Plume and Wear Characteristics After 16,550 h of Operation and 337 kg of Xenon Processed

Herman¹,

Soulas²,

Patterson³

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Section: Introductionmentioning

confidence: 99%

NEXT Long-Duration Test Plume and Wear Characteristics After 16,550 h of Operation and 337 kg of Xenon Processed

Herman¹,

Soulas²,

Patterson³

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

Self Cite

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“…[11] A review of life assessment predictions examining wear mechanisms at various throttle conditions was completed. [12] A LongDuration Test (LDT) was initiated to validate and qualify the NEXT propellant throughput capability to a qualification-level of 450 kg, 1.5 times the mission-derived throughput requirement of 300 kg. As of December 31, 2008, the Engineering Model (EM) thruster has accumulated 19,556 hours of operation.…”

Section: Recent Progressmentioning

confidence: 99%

Recent electric propulsion development activities for NASA science missions

Pencil

2009

2009 IEEE Aerospace Conference

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Abstract(The primary source of electric propulsion development throughout NASA is managed by the In-Space Propulsion Technology Project at the NASA Glenn Research Center for the Science Mission Directorate. The objective of the Electric Propulsion project area is to develop near-term electric propulsion technology to enhance or enable science missions while minimizing risk and cost to the end user. Major hardware tasks include developing NASA's Evolutionary Xenon Thruster (NEXT), developing a long-life High Voltage Hall Accelerator (HIVHAC), developing an advanced feed system, and developing crossplatform components. The objective of the NEXT task is to advance next generation ion propulsion technology readiness. The baseline NEXT system consists of a highperformance, 7-kW ion thruster; a high-efficiency, 7-kW power processor unit (PPU); a highly flexible advanced xenon propellant management system (PMS); a lightweight engine gimbal; and key elements of a digital control interface unit (DCIU) including software algorithms. This design approach was selected to provide future NASA science missions with the greatest value in mission performance benefit at a low total development cost. The objective of the HIVHAC task is to advance the Hall thruster technology readiness for science mission applications. The task seeks to increase specific impulse, throttle-ability and lifetime to make Hall propulsion systems applicable to deep space science missions. The primary application focus for the resulting Hall propulsion system would be cost-capped missions, such as competitivelyselected, Discovery-class missions. The objective of the advanced xenon feed system task is to demonstrate novel manufacturing techniques that will significantly reduce mass, volume, and footprint size of xenon feed systems over conventional feed systems. This task has focused on the development of a flow control module, which consists of a three-channel flow system based on a piezo-electrically actuated valve concept, as well as a pressure control module, which will regulate pressure from the propellant tank. Cross-platform component standardization and simplification are being investigated through the Standard Architecture task to reduce first user costs for implementing electric propulsion systems. Progress on current hardware development, recent test activities and future plans are discussed.

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“…The thruster can operate for substantial duration, over 60 kh, at this operating condition with the TT10 input of -350 V for accelerator grid voltage (in previous throttle tables and in the service life publication the model calculations were 45 kh for an accelerator grid voltage of -500 V) (Ref. 18). The centerline accelerator groove erosion depth as a function of test duration during TL01 (0.5 kW) run segment is shown in Figure 20.…”

Section: Tl01-05 Kw Input Power-100 a 275 Vmentioning

confidence: 99%

“…18). The high thermal load can impact magnetic field strength if degradation of the magnetic material occurs.…”

Section: Tl37-47 Kw Input Power-352 a 1179 Vmentioning

confidence: 99%

Application of the NEXT Ion Thruster Lifetime Assessment to Thruster Throttling

Cited by 17 publications

References 14 publications

NEXT Long-Duration Test Plume and Wear Characteristics After 16,550 h of Operation and 337 kg of Xenon Processed

NEXT Long-Duration Test Plume and Wear Characteristics After 16,550 h of Operation and 337 kg of Xenon Processed

Recent electric propulsion development activities for NASA science missions

Status of the NASA's Evolutionary Xenon Thruster (NEXT) Long-Duration Test after 30,352 Hours of Operation

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