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132 Chapter 4 300 280 260 240 220 200 180 160 140 120 100 0.76 0.78 0.80 0.82 0.84 Mass Utilization Efficiency 0.92 0.94 0.96 TH15 Data TH15 Model Fig. 4-19. Discharge loss versus mass utilization efficiency for the NSTAR thruster at the high power TH15 throttle point. plasma electron confinement such that the convective losses are minimized at low neutral density and higher electron temperatures. A significant challenge for most discharge models is handling the primary electrons correctly. For the case of monoenergetic primaries assumed in this model, the primary density is determined by collisional and ballistic (direct-to- anode) losses that change as a function of the neutral pressure, which is inversely proportional to the mass utilization efficiency. The primary electron density then varies strongly as the mass utilization efficiency is changed. However, if primary electrons are neglected altogether (i.e., assumed thermalized immediately in the cathode plume) so that the plasma in the discharge chamber is produced only by ionization by the high-energy tail of the Maxwellian electron population, the discharge loss is extremely high. This is shown in Fig. 4-20, where the discharge loss in the NEXIS thruster increases to over 240eV/ion if the primary electron ionization effects are neglected. Likewise, if the primary electron density is independent of the neutral pressure, then the discharge loss curve in Fig. 4-20 has a steep slope resulting from an excessive number of primary electrons at low mass utilization (high pressure), which produces more ionization than actually occurs. Clearly, including the presence of primary electrons in the analysis is required for the model results to agree with the data, which, in turn, suggests that primary or energetic electrons and non-Maxwellian electron populations must exist in this type of thruster. 0.86 0.88 0.90 Discharge Loss (eV/ion)PDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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