Fundamentals of Electric Propulsion: Ion and Hall Thrusters

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Fundamentals of Electric Propulsion: Ion and Hall Thrusters ( fundamentals-electric-propulsion-ion-and-hall-thrusters )

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Hall Thrusters 381 0.10 0.09 0.08 0.07 0.06 0.05 0.04 0.03 0.02 0.01 0.00 0 50 100 150 200 250 300 350 Ion Energy (eV) Fig. 7-21. Sputtering yield calculated for singly ionized xenon on BNSiO2 versus ion energy for two incidence angles. 0 deg 45 deg data deep in the channel. This can be remedied by additional sputter-yield measurements at low energy and a refinement of the sputtering yield in Eq. (7.5-2). It is possible to develop some simple scaling rules for Hall thruster erosion in the magnetized plasma region near the exit plane. It was estimated in Section 7.3.4 that the ion flux to the wall in dielectric-wall Hall thrusters was about 10% of the beam current. It can be assumed that the energy of the ion flux to the wall is related to the beam energy, which is proportional to the discharge voltage. An examination of Fig. 7-21 shows that the sputtering yield is essentially a linear function of the ion energy. The erosion rate in Eq. (7.5-1) then becomes K I b V d = K I d V d , ( 7 . 5 - 3 ) Aw bAw where K is a constant, Aw is the wall area, and Eq. (7.3-10) has been used for the beam current efficiency. Equation (7.5-3) shows that the erosion rate of the thruster wall is proportional to the power density in the accelerator channel [4]. This indicates that larger Hall thrusters are required to increase the power for a given operation time as determined by the allowable erosion of the insulator wall thickness. A good rule-of-thumb for the relationship of operation time over a reasonable throttle range of a given Hall thruster design is power * operation time constant. Sputtering Yield (mm3/C)

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