NEXT Ion Propulsion System Development Status and Performance

Patterson, Michael J.; Benson, Scott W.

doi:10.2514/6.2007-5199

Cited by 59 publications

(33 citation statements)

References 13 publications

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“…Electrothermal propulsion includes devices like arcjets [4][5][6], resistojets [7], hollow cathode thrusters [8,9], and the Pocket Rocket microthruster [10] which is the subject of this paper. Electrostatic propulsion has been dominated by a large variety of gridded ion thrusters, the most recent developments including NASA's annular-geometry ion engine (AGI-Engine) [11,12] and the NASA evolutionary xenon thruster (NEXT) [13,14], but also include experimental technologies like the field emission electric propulsion (FEEP) concept [15] and its precedent colloid thrusters. Finally, electromagnetic propulsion boasts the mature Hall-effect thruster [16] and its variants [17][18][19], as well as newer technologies like magnetoplasmadynamic (MPD) thrusters [20,21] and ablative pulsed plasma thrusters (PPTs) [22].…”

Section: Introductionmentioning

confidence: 99%

A Comprehensive Cold Gas Performance Study of the Pocket Rocket Radiofrequency Electrothermal Microthruster

Charles

Boswell

2017

Front. Phys.

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This paper presents computational fluid dynamics simulations of the cold gas operation of Pocket Rocket and Mini Pocket Rocket radiofrequency electrothermal microthrusters, replicating experiments performed in both sub-Torr and vacuum environments. This work takes advantage of flow velocity choking to circumvent the invalidity of modeling vacuum regions within a CFD simulation, while still preserving the accuracy of the desired results in the internal regions of the microthrusters. Simulated results of the plenum stagnation pressure is in precise agreement with experimental measurements when slip boundary conditions with the correct tangential momentum accommodation coefficients for each gas are used. Thrust and specific impulse is calculated by integrating the flow profiles at the exit of the microthrusters, and are in good agreement with experimental pendulum thrust balance measurements and theoretical expectations. For low thrust conditions where experimental instruments are not sufficiently sensitive, these cold gas simulations provide additional data points against which experimental results can be verified and extrapolated. The cold gas simulations presented in this paper will be used as a benchmark to compare with future plasma simulations of the Pocket Rocket microthruster.

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Section: Introductionmentioning

confidence: 99%

A Comprehensive Cold Gas Performance Study of the Pocket Rocket Radiofrequency Electrothermal Microthruster

Charles

Boswell

2017

Front. Phys.

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“…[17], [18] The objectives of this development were to improve upon the state-of-art NASA Solar Electric Propulsion Technology Application Readiness (NSTAR) system flown on Deep Space-1 to enable flagship class missions by achieving:…”

Section: Solar Electric Propulsion (Sep)mentioning

confidence: 99%

In-Space Propulsion Technology products for NASA's future science and exploration missions

Anderson

Pencil

Peterson

et al. 2011

2011 Aerospace Conference

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Abstract-Since 2001, the In-Space Propulsion Technology (ISPT) project has been developing and delivering in-space propulsion technologies that will enable or enhance NASA robotic science missions. These in-space propulsion technologies are applicable, and potentially enabling, for future NASA flagship and sample return missions currently being considered, as well as having broad applicability to future competed mission solicitations. The high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance for lower cost was completed in 2009. Two other ISPT technologies are nearing completion of their technology development phase: 1) NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 2) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; aerothermal effect models: and atmospheric models for Earth, Titan, Mars and Venus. This paper provides status of the technology development, applicability, and availability of in-space propulsion technologies that have recently completed their technology development and will be ready for infusion into NASA's Discovery, New Frontiers, Science Mission Directorate (SMD) Flagship, and Exploration technology demonstration missions.

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“…1). This system represents a significant improvement over the state-of-the-art (SOA) NASA's Solar Electric Propulsion Technology Application Readiness (NSTAR) ion propulsion system because each element delivers higher performance and has lower specific mass.…”

Section: Introductionmentioning

confidence: 99%