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356 Chapter 7 the wall that also have a small exposed area to the plasma, resulting in low radial ion currents to the wall. This is evidenced by the erosion pattern typically observed on TAL guard rings [29], which tends to be on the downstream face from particles outside the thruster instead of on the inside diameter from the channel plasma. While the ion and electron currents and power deposition to the inside diameter of the metallic guard ring are likely smaller than in the dielectric-wall thruster case (where the power loss due to the electrons is dominant), the erosion on the face of the guard ring indicates energetic ion bombardment is occurring. This effect is significant in determining the life of the TAL. However, TAL thrusters are characterized by having the anode in close contact with the magnetized plasma near the channel exit, in contrast to the dielectric- wall Hall thrusters. The magnetized plasma has a high electron temperature, which causes a significant amount of power to be deposited from the discharge current on the anode. It is possible to evaluate this power loss mechanism based on the current and sheath potential at the anode. As described above, the discharge current is essentially equal to the electron current collected at the anode. In order for the TAL thruster to transfer a large fraction of the discharge voltage to the ions, the potential of the plasma near the anode must be close to the anode potential. Assuming the local plasma potential is then equal to or slightly positive relative to the anode, the electron current to the anode, Ia , deposits 2TeV in energy from the plasma (see Appendix C). The power deposited on the anode, Pa , is then given by Pa=2TeVIa 2TeVId, (7.3-47) where Eq. (7.2-26) has been used. If the plasma potential is negative relative to the anode, the thruster efficiency will suffer due to the loss of discharge voltage available to the ions, and the anode heating will increase due to the positive- going sheath potential accelerating electrons into the anode. Equation (7.3-47) then represents a reasonable, but not worst-case, heat flux to the anode. This power loss to the anode can be related to the beam current using the fraction of the discharge current that produces beam current, which is defined as b = Ib . (7.3-48) Id Therefore, the power to the anode isPDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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