Simple Model for Cathode Coupling Voltage Versus Background Pressure in a Hall Thruster

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/143041/1/6.2017-4889.pd

Expanded Thruster Mass Model Incorporating Nested Hall Thrusters

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/143089/1/6.2017-4729.pd

High Power Demonstration of a 100 kW Nested Hall Thruster System

The XR-100 team successfully completed high power system testing of a Nested Hall Thruster system made up of the X3 Nested Hall Thruster, a modular Power Processing Unit, and a 5 valve Mass Flow Controller as the culmination of work performed under a NASA NextSTEP program. The test campaign attained several key firsts, including highest directly measured thrust of an electric propulsion (EP) string, highest demonstrated current of an EP string, and highest power operation of an EP string at thermal equilibrium published to date. Most importantly, the XR-100 system testing demonstrated that a 100 kW-class Nested Hall Thruster system has comparable performance and behavior to current state-of-the-art mid power Hall Thrusters, validating that the heritage technology can be scaled up to 100+ k

Passive High-speed Imaging of Ion Acoustic Turbulence in a Hollow Cathode

Peer Reviewedhttps://deepblue.lib.umich.edu/bitstream/2027.42/143104/1/6.2017-4973.pd

100 kW Nested Hall Thruster System Development

Large scale cargo transportation to support human missions to the Moon and Mars will require very high power Solar Electric Propulsion (SEP) systems operating between 200 and 400 kW. Aerojet Rocketdyne's NextSTEP program is developing and demonstrating a 100 kW EP system, the XR-100, using a Nested Hall Thruster (NHT) designed for powers up to 200 kW, a modular power processor and a modular flow controller. The three year program objective is to operate the integrated EP system continuously at 100 kW for 100 h, advancing this very high power Electric Propulsion (EP) system to Technology Readiness Level (TRL) 5. With our University of Michigan, Jet Propulsion Laboratory and NASA Glenn Research Center teammates, Aerojet Rocketdyne has completed the initial phase of the program, including operating the thruster at up to 30 kW to validate the thermal models and developing and operating multiple power processor modules in the required seriesparallel configuration. The current phase includes completing a TRL 4 integrated system test at reduced power to validate all system operating phases. Design upgrades to demonstrate the TRL 5 capabilities are underway. This paper will present the high power XR-100 capabilities, overall program and design approach and the latest test results for the 100 kW EP system demonstration program

High Power Demonstration of a 100 kW Nested Hall Thruster System

The XR-100 team successfully completed high power system testing of a Nested Hall Thruster system made up of the X3 Nested Hall Thruster, a modular Power Processing Unit, and a 5 valve Mass Flow Controller as the culmination of work performed under a NASA NextSTEP program. The test campaign attained several key firsts, including highest directly measured thrust of an electric propulsion (EP) string, highest demonstrated current of an EP string, and highest power operation of an EP string at thermal equilibrium published to date. Most importantly, the XR-100 system testing demonstrated that a 100 kW-class Nested Hall Thruster system has comparable performance and behavior to current state-of-the-art mid power Hall Thrusters, validating that the heritage technology can be scaled up to 100+ k

Update on the Nested Hall Thruster Subsystem for the NextSTEP XR-100 Program

Under the NextSTEP program led by Aerojet Rocketdyne in collaboration with NASA Glenn Research Center the University of Michigan, and the Jet Propulsion Laboratory, the XR-100 100 kW Electric Propulsion system is being developed to Technology Readiness Level (TRL) 5. As part of this program, the X3, a Nested Hall Thruster (NHT) designed to operate at powers up to 200kW, is being further developed through parallel modeling and experimental efforts with the ultimate goal of supporting a 100kW-100hr system test in the final year of the NextSTEP program. Recent developments for the X3 subsystem are presented including a summary of testing and modeling results and design updates in anticipation of a risk reduction test scheduled for the summer of 2018

Plasma Heating with Beating Electrostatic Waves

The heating of ions in a magnetized plasma with two electrostatic waves whose frequencies differ by the ion cyclotron frequency is analytically, numerically, and experimentally characterized. This process, denoted beating electrostatic wave (BEW) heating, is of particular interest since its ability to non-resonantly accelerate low energy ions suggests that it may be more effective at ion energization than the traditional, resonant heating produced by a single electrostatic wave (SEW). To explore this possibility, the BEW and SEW mechanisms were examined through an analysis of single particle orbits as well as the average power absorbed by an ion ensemble. Using the total input energy density of the waves as a metric, it was found that there are three distinct regimes for comparing the two processes: (I) for low energy density, there is a criterion for the onset of heating that depends on the wave parameters, and this criterion is satisfied for a lower input energy density with BEW; (II) at intermediate energy density, once heating has onset for both processes, SEW heating is superior; and (III) at high energy density above a threshold value that depends both on the wave parameters and background plasma, the BEW heating process is predicted to lead to higher heating levels. These analytical conclusions were tested in a low-temperature experimental setup by examining the increase in ion temperature produced by SEW and BEW as a function of total input energy density and fraction of energy in each wave. The experimental results were found to correspond to within error to the theoretical trends predicted for the first regime (I) and qualitative agreement was found for the second regime (II). Saturation effects combined with a limited available energy density to the experiment precluded a systematic investigation of the third energy density regime

Future Directions for Electric Propulsion Research

The research challenges for electric propulsion technologies are examined in the context of s-curve development cycles. It is shown that the need for research is driven both by the application as well as relative maturity of the technology. For flight qualified systems such as moderately-powered Hall thrusters and gridded ion thrusters, there are open questions related to testing fidelity and predictive modeling. For less developed technologies like large-scale electrospray arrays and pulsed inductive thrusters, the challenges include scalability and realizing theoretical performance. Strategies are discussed to address the challenges of both mature and developed technologies. With the aid of targeted numerical and experimental facility effects studies, the application of data-driven analyses, and the development of advanced power systems, many of these hurdles can be overcome in the near future

Measurements of ion velocity and wave propagation in a hollow cathode plume

The mechanism responsible for the production of energetic ions in the plume of hollow cathodes for electric propulsion is still an open issue. These ions are of concern to cathode and thruster lifetime, particularly for cathodes operating at high (>20 A) discharge currents. Recent theoretical and experimental investigations suggest that there is a correlation between ion energy gain and ion acoustic turbulence. In this paper we present measurements of the evolution of the ion velocity distribution function in the near plume of a 100 A-class hollow cathode, operated in a regime in which the dominant mode is ion acoustic turbulence. Ion flow and thermal properties were related to measurements of the background plasma, fluctuation spectra, and dispersion relations obtained from an array of Langmuir probes. We found ions to flow outward from the cathode and accelerate downstream, to supersonic speeds, approximately aligned with the acoustic wave group velocity vectors. The directions of the ion flow and wave propagation were similar for a range of discharge currents and mass flow rates in the jet region of the plume. One operating condition showed a significant temperature increase, also in the direction of acoustic wave propagation, corresponding to the highest wave energy condition. These results are interpreted in the context of ion acoustic turbulence as a contributing mechanism for ion energy gain