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158 Chapter 4 required input rf power to the antenna assuming that the antenna efficiency and coupling (reflected power) are known. The approximate induced AC magnetic field can then be calculated from Eq. (4.5-18) and the ion confinement factor fc , found as in Section 4.3.4. A simple iteration then gives the final discharge loss and rf power. It should be noted that as the discharge chamber length decreases, the antenna axial extent also decreases, which reduces the electric field interaction region and decreases the AC axial magnetic field strength due to end effects in the solenoid coil. The ability to breakdown the neutral gas initially and then couple the rf energy to the electrons efficiently may be compromised as the length decreases, which would also affect the discharge loss scaling. A disadvantage of rf ion thrusters is that the antenna must be insulated from the plasma, and the insulator is then subject to ion bombardment and material deposition. Dielectric discharge chambers are susceptible to mechanical problems in fabrication, environmental testing and launch, and life issues from coating of the insulator surface with conducting layers. The structural issue has been addressed on some flight units by the use of a ceramic discharge chamber with an exterior mounted antenna structure to provide the rigidity required for launch survival. While the discharge loss in rf ion thrusters is typically higher than that found for well-designed electron-bombardment ion thrusters such that the total efficiency is lower, the simplified design of rf thrusters makes it easier to analyze them and predict the performance than most other ion thruster configurations. The rf thruster design concept eliminates any potential discharge cathode life issues and utilizes fewer power supplies to operate the discharge. These factors make rf ion thrusters very competitive for future spaceflight applications. 4.6 Microwave Ion Thrusters An alternative to producing the plasma in the thruster with electron discharges or rf induction heating of the electron population is to generate the plasma using electromagnetic fields at microwave frequencies. This eliminates life issues associated with the discharge hollow cathode, and the lack of applied DC voltages in the discharge chamber can potentially reduce the sputter erosion of electrodes exposed to the plasma as compared with that of DC electron discharges. However, electromagnetic waves can propagate and be absorbed in plasmas only under certain conditions. For example, if the microwave frequency is too high or the plasma density too low, the microwave radiation is reflected completely from the plasma. If the conditions are such that the microwaves do propagate in the plasma, the microwave energy is coupled to the plasma by resonant heating of the electrons in a magnetic field in thePDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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