Development Status of the NEXT Propellant Management System

Aadland, Randall S.; Monheiser, Jeff; Driscoll, Elizabeth; Wilson, Fred; Benson, Scott W.

doi:10.2514/6.2004-3974

Cited by 16 publications

(11 citation statements)

References 3 publications

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“…6 All assemblies have completed functional testing, and both flight-like HPA and LPA assemblies have successfully completed qualification-level vibration testing (14.10 G rms through each of the 3 axes for 2 min duration) (ref. 13) and thermal vacuum testing (four thermal cycles from 12 to 70 °C). The assemblies have been delivered to GRC and are being prepared for system integration testing.…”

Section: Propellant Management Systemmentioning

confidence: 99%

NEXT Ion Propulsion System Development Status and Performance

Patterson

Benson²

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Section: Propellant Management Systemmentioning

confidence: 99%

NEXT Ion Propulsion System Development Status and Performance

Patterson

Benson²

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…The EM Propellant Management System (PMS) was manufactured by Aerojet [26]. The PMS delivers low pressure gas to the thruster from a supercritical xenon supply source, and it consists of a High Pressure Assembly (HPA) and a Low Pressure Assembly (LPA).…”

Section: Propellant Management Systemmentioning

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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“…11 Flow rate was controlled using variable, electro-mechanical pressure regulators and thermal throttles. 22 During thruster operation, voltages and currents were measured with digital multimeters and shunts. These measured parameters were used to set thruster operating conditions, as well as to determine thruster performance.…”

Section: Test Support Hardware and Operating Conditionsmentioning

confidence: 99%

NEXT Ion Thruster Performance Dispersion Analyses

Soulas

Patterson²

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The NEXT ion thruster is a low specific mass, high performance thruster with a nominal throttling range of 0.5-7 kW. Numerous engineering model and one prototype model thrusters have been manufactured and tested. Of significant importance to propulsion system performance is thruster-to-thruster performance dispersions. This type of information can provide a bandwidth of expected performance variations both on a thruster and a component level. Knowledge of these dispersions can be used to more conservatively predict thruster service life capability and thruster performance for mission planning, facilitate future thruster performance comparisons, and verify power processor capabilities are compatible with the thruster design. This study compiles the test results of five engineering model thrusters and one flight-like thruster to determine unit-to-unit dispersions in thruster performance. Component level performance dispersion analyses will include discharge chamber voltages, currents, and losses; accelerator currents, electron backstreaming limits, and perveance limits; and neutralizer keeper and coupling voltages and the spot-to-plume mode transition flow rates. Thruster level performance dispersion analyses will include thrust efficiency.

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Development Status of the NEXT Propellant Management System

Cited by 16 publications

References 3 publications

NEXT Ion Propulsion System Development Status and Performance

NEXT Ion Propulsion System Development Status and Performance

Technology Readiness of the NEXT Ion Propulsion System

NEXT Ion Thruster Performance Dispersion Analyses

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