Status of the Next 7 Kw Power Processing Unit

Todd, Philip C.; Martinelli, R. M.; Wiseman, Steve; Pinero, Luis R.

doi:10.2514/6.2005-3868

Cited by 10 publications

(6 citation statements)

References 3 publications

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“…It has a flexible, scalable architecture which can be adapted to a wide range of thrusters 4 and missions, with a wide throttle range capability (250 to 7200 W), a >0.2 kW/kg specific power, and a simple thermal interface (a 65 °C baseplate). 3 The PPU design was fully documented prior to manufacturing with all drawings and assembly instructions in place and under configuration management prior to fabrication. 4 The NEXT PPU is fully-compatible with operating the NSTAR thruster over its full throttle table; this was successfully demonstrated using the NEXT breadboard PPU on an EM NSTAR thruster.…”

Section: B Power Processor Unitmentioning

confidence: 99%

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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: B Power Processor Unitmentioning

confidence: 99%

“…4). 3 This was preceded by fabrication and successful integration test of breadboard PPU during Phase 1. The PPU is planned to be delivered to GRC for thruster integration testing and then qualificationlevel vibration and thermal vacuum testing back at L3.…”

Section: B Power Processor Unitmentioning

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 engineering model (EM) PPU was manufactured by L3 Communications ETI (L3) [25]. This was preceded by fabrication and successful integration test of breadboard PPU during Phase 1.…”

Section: Power Processing Unitmentioning

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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“…‡ ‡ The NEXT system consists of a high performance, 7-kW, ion thruster; a modular, 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. [1][2][3][4] 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. Technology validation and mission analysis results in Phase 1 indicated that the NEXT technologies have the capabilities that provide the expected benefits, and further development was warranted.…”

Section: Introductionmentioning

confidence: 99%