The cross-field electron mobility in Hall thrusters is known to be enhanced by wall collisionality and turbulent plasma fluctuations. Although progress has been made in understanding the plasma-wall interaction and instabilities responsible for the anomalous transport, a predictive model based on the underlying physics of these processes has yet to emerge. Hybrid-PIC simulations of the Hall thruster have typically depended on semi-empirical models of the mobility to provide sufficient electron current to match experimental results. These models are capable of qualitatively predicting the plasma response over a wide range of operating conditions, but have limited quantitative capabilities unless they are calibrated with experimental data. The efficacy of several electron mobility models in reproducing the plasma response of a 6 kW laboratory Hall thruster are assessed. With respect to a two-region mobility model that is frequently reported in the literature, a three-region model for the mobility is shown to significantly improve the agreement with experimentally measured profiles of the plasma potential and electron temperature.

Life-limiting processes in hollow cathodes are determined largely by the temperature of the emitter. To support development of cathode life models we have developed a noncontact temperature measurement technique which employs a stepper motor-driven fiber optic probe. The probe is driven inside the hollow cathode and collects light radiated by the hot interior surface of the emitter. Ratio pyrometry is used determine the axial temperature profile. Thermocouples on the orifice plate provide measurements ofthe external temperature during cathode operation and are used to calibrate the pyrometer system in situ with a small oven enclosing the externally heated cathode. Initial measurements of the temperature distribution in a hollow cathode with the same geometry as a cathode that failed after operating at 12 A emission current for 27800 hours are discussed.

A versatile double Langmuir probe technique has been developed by incorporating analytical fits to Laframboise's numerical results for ion current collection by biased electrodes of various sizes relative to the local electron Debye length. Application of these fits to the double probe circuit has produced a set of coupled equations that express the potential of each electrode relative to the plasma potential as well as the resulting probe current as a function of applied probe voltage. These equations can be readily solved via standard numerical techniques in order to determine electron temperature and plasma density from probe current and voltage measurements. Because this method self-consistently accounts for the effects of sheath expansion, it can be readily applied to plasmas with a wide range of densities and low ion temperature (T(i)/T(e) ≪ 1) without requiring probe dimensions to be asymptotically large or small with respect to the electron Debye length. The presented approach has been successfully applied to experimental measurements obtained in the plume of a low-power Hall thruster, which produced a quasineutral, flowing xenon plasma during operation at 200 W on xenon. The measured plasma densities and electron temperatures were in the range of 1 × 10(12)-1 × 10(17) m(-3) and 0.5-5.0 eV, respectively. The estimated measurement uncertainty is +6%∕-34% in density and +∕-30% in electron temperature.

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