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Ion Thruster Plasma Generators 131 280 260 240 220 200 180 160 140 120 100 0.76 0.78 0.80 0.82 0.84 Mass Utilization Efficiency 0.92 0.94 0.9 25 V Data 25 V Model 26.5 V Data 26.5 V Model 27.5 V Data 27.5 V Model Fig. 4-18. Example of the discharge loss versus mass utilization efficiency for three discharge voltages in the NEXIS thruster [38]. The discharge model also matches the discharge loss data obtained from other thrusters. Figure 4-19 shows the discharge loss measured at JPL in a laboratory copy of the NSTAR thruster [39] operating at the full power (2.3 kW) TH15 throttle level. The model predictions agree with the thruster data if the measured 6.5-V cathode voltage drop in the NSTAR hollow cathode [40] is used for Vc . The ability of a 0-D model to match the NSTAR data is significant only in that the NSTAR plasma is not very uniform (flatness parameter 0.5) and contains over 20% double ions peaked on the axis. The 0-D model likely works in this case because the ionization is still dominated by the average volume effects, and the losses are still determined by the magnetic field structure at the wall, which 0-D models can capture sufficiently to give reasonably accurate results. The shape of the performance curves is also important. As the mass utilization is increased, the neutral density in the discharge chamber decreases [see Eq. (4.3-35)] and more of the primary energy goes into heating the plasma electrons and energy loss directly to the anode, as was illustrated by the simplified model for the idealized thruster case in Section 4.2. Optimal thruster designs have flatter discharge performance curves that exhibit lower discharge losses as the mass utilization efficiency is increased. The model suggests that this is generally achieved in thrusters by designing for good primary and 0.86 0.88 0.90 Discharge Loss (eV/ion)PDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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