NEXT Multi-Thruster Array Test - Engineering Demonstration

Patterson, Michael J.; Foster, John E.; McEwen, Heather; Pencil, Eric; Noord, Jonathan Van; Herman, Daniel A.

doi:10.2514/6.2006-5180

Cited by 15 publications

(9 citation statements)

References 9 publications

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“…Electric propulsion thrusters use electric and magnet ¦elds; while operating, they generate high power electromagnetic and thermal radiation. Therefore, there is a danger of negative thrusters interference though Hall-and ion-based clusters tests have shown [28,3133] that negative interference can be successfully minimized or even entirely eliminated.…”

Section: Figure 5 Independent (A) and Common (B) Eps Architecturesmentioning

confidence: 99%

Concept of electric propulsion realization for high power space tug

Zakharenkov

Semenkin

Solodukhin

2016

Progress in Propulsion Physics

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Popular at the beginning of the Space Age, ambitious projects aimed at Moon, Mars, and other space objects exploration, have returned with new technology and design level. High power space tug with electric propulsion system (EPS) is mainly considered as a transport vehicle for such missions. Modern high power space tugs projects as well as their spacecraft (SC) power and propulsion systems are reviewed in the paper. The main technologies and design solutions needed for high-power EPS realization are considered.

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Section: Figure 5 Independent (A) and Common (B) Eps Architecturesmentioning

confidence: 99%

Concept of electric propulsion realization for high power space tug

Zakharenkov

Semenkin

Solodukhin

2016

Progress in Propulsion Physics

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“…This MTAT utilized multiple engineering model (EM) NEXT ion thrusters as well as laboratory power consoles and laboratory propellant feed systems to operate multiple thrusters simultaneously. The engineering demonstration portion of MTAT [21] focused on the characterization of performance and behavior of the individual thrusters and the array as affected by the simultaneous operation of multiple ion thrusters. The MTAT physics effort focused on the characterization of the plasma environment generated by the simultaneous operation of multiple ion thrusters.…”

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 primary components of the test included: four EM thrusters mounted on a reconfigurable array, one of which was an instrumented non-operational unit, a gimbal simulator articulating one thruster, laboratory power supplies, laboratory xenon feed systems, extensive plume and plasma diagnostics, and a data acquisition and control system. Test objectives and sequences concentrated on engineering evaluation of thruster operations [29], plume characterization and interactions, with variation in thruster spacing and gimbaling effects considered [30], [31], neutralizer performance in multi-thruster arrays [32], and plasma environments around the thruster array and at the spacecraft interfaces [33].…”

Section: Multi-thrustermentioning

confidence: 99%

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 Multi-Thruster Array Test - Engineering Demonstration

Cited by 15 publications

References 9 publications

Concept of electric propulsion realization for high power space tug

Concept of electric propulsion realization for high power space tug

Recent electric propulsion development activities for NASA science missions

Technology Readiness of the NEXT Ion Propulsion System

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