This paper describes a new high-power thrust stand developed for use with high-power (up to 250 kW) magnetoplasmadynamic (MPD) thrusters, which is installed in a high-vacuum MPD facility at Lewis Research Center. The design of the stand is based on inverted pendulum configuration, with the result of large displacements and high resolution. Calibration results showed that thrust measurements were linear and repeatable to within a fraction of 1 percent. The thrust stand was used for testing water-cooled MPD thrusters at power levels up to 125 kW. The thruster, however, is quite well suited for testing other types of electric propulsion devices.

Thrust stand for high‐power electric propulsion devices

A thrust stand for use with high power electric propulsion devices was designed and tested. The thrust stand was specifically tailored to the needs of a 100 to 250 kW magnetoplasmadynamic (MPD) thruster program currently in progress at the NASA Lewis Research Center. The thrust stand structure was built as an inverted pendulum arrangement, supported at the base by water-cooled electrical power flexures. Thrust stand tares due to thruster discharge current were demonstrated to be negligible. Tares due to an applied field magnet current, after considerable effort, were reduced to less than 3.0 percent of measured thrust. These tares, however, could be determined independently and subtracted from the indicated thrust measurement. A detailed description is given for the thrust stand design and operation with a 100 kW class MPD device. Other thrust stand tares due to vibration and thermal effects are discussed, along with issues of accuracy and repeatability.

/pdf/design-of-a-thrust-stand-for-high-power-electric-propulsion-1milruvy7q.pdf

Design of a thrust stand for high power electric propulsion devices

Piloted Mars Mission Requirements of relatively short trip times and low initial mass in Earth orbit as identified by the NASA Space Exploration Initiative, indicate the need for multimegawatt electric propulsion systems. The design considerations and results for two thruster types, the argon ion, and hydrogen magnetoplasmadynamic thrusters, are addressed in terms of configuration, performance, and mass projections. Preliminary estimates of power management and distribution for these systems are given. Some assessment of these systems' performance in a reference Space Exploration Initiative piloted mission are discussed. Research and development requirements of these systems are also described.

/pdf/multimegawatt-electric-propulsion-system-design-5awatnxuxa.pdf

Multimegawatt electric propulsion system design considerations

Evolving new propulsion technologies through a rational and conscious effort to minimize development costs and program risks while maximizing the performance benefits is intuitively practical. A phased approach to the evolution of nuclear electric propulsion from use on planetary probes, to lunar cargo vehicles, and finally to manned Mars missions with a concomitant growth in technology is considered. Technology levels and system component makeup are discussed for nuclear power systems and both ion and magnetoplasmadynamic thrusters. Mission scenarios are described, which include analysis of a probe to Pluto, a lunar cargo mission, Martian split, all-up, and quick-trip mission options. Evolutionary progression of the use of NEP in such missions is discussed.

Evolutionary use of nuclear electric propulsion

was then calculated using the voltage data along with a semi-empirical thrust formula derived and veried previously for the same thruster. The non-useful voltage component (the voltage associated with the thruster’s power losses) was found to scale linearly with current and applied magnetic eld and inversely with mass ow rate. This behavior was attributed to electrode sheath eects and decreased conductivity with increasing applied magnetic eld. The eciency was found to increase with applied magnetic eld for all current and mass ow rate values and the enhancement of the eciency by the applied magnetic eld was found to be greater when the mass ow rate is reduced. The observed minimum in the eciency vs current curve was related to interplay between the components of the thrust and was shown experimentally and analytically to increase with increasing applied eld and decreasing mass ow rate.

https://alfven.princeton.edu/papers/JPC2010Lev.pdf

Scaling of Efficiency with Applied Magnetic Field in Magnetoplasmadynamic Thrusters

Performance of a 100 kW, applied field magnetoplasmadynamic (MPD) thruster was evaluated and sensitivities of discharge characteristics to arc current, mass flow rate, and applied magnetic field were investigated. Thermal efficiencies as high as 60 percent, thrust efficiencies up to 21 percent, and specific impulses of up to 1150 s were attained with argon propellant. Thrust levels up to 2.5 N were directly measured with an inverted pendulum thrust stand at discharge input powers up to 57 kW. It was observed that thrust increased monotonically with the product of arc current and magnet current.

/pdf/performance-of-a-100-kw-class-applied-field-mpd-thruster-w9vtlmi8xy.pdf

Performance of a 100 kW class applied field MPD thruster

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Performance of a 100 kW class applied field MPD thruster