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Ion Thruster Plasma Generators 105 essentially perpendicular to the surface. The number of electrons lost at the cusp depends on the local sheath potential and the effective loss area at the cusp. Ions produced in the discharge chamber can flow back to the hollow cathode, to the anode wall, or to the plane of the accelerator. At the accelerator, these ions are either intercepted and collected by the screen electrode with an effective transparency, Tg , or are extracted from the plasma through the grids to become beam ions. The screen grid transparency depends on the optical transparency of the grid and the penetration of the high voltage fields from the accelerator region into the screen apertures. While this transparency is an input to the discharge model, it is calculated by the ion optics codes described in Chapter 5. In this model, the high-voltage power supply that accelerates the ions, called the screen supply, is connected to the anode. This means that the ions fall from the average plasma potential in the discharge chamber to form the beam. It is also possible to connect the screen supply to the screen and cathode, which means that the ion current in the beam must pass through the discharge supply. This changes the algebra slightly in calculating the discharge performance, but it does not change the results. The components of the particle and energy balance model are described in the following sections. 4.3.2 Magnetic Multipole Boundaries Ring-cusp ion thrusters use alternating polarity permanent magnet rings oriented perpendicularly to the thruster axis, with the number of rings selected and optimized for different size thrusters [20]. This configuration provides magnetic confinement of the electrons with finite loss at the magnetic cusps, and electrostatic confinement of the ions from the anode wall due to the quasi- ambipolar potentials at the boundary from the transverse magnetic fields. Line- cusp thrusters also use high field magnets, but the magnets are configured in alternating polarity axial lines that run along the chamber wall. Asymmetries at the ends of the line cusps cause plasma losses and difficulties in producing a uniform symmetric field at the cathode exit, which adversely affects the electron confinement and thruster efficiency. Ring-cusp thrusters are the most commonly used discharge chamber design at this time due to their ability to produce high efficiency and uniform plasmas at the ion accelerator surface if properly designed. A schematic representation of a section of a ring cusp magnetic multipole boundary is shown in Fig. 4-10. In this view, a cut along the axis through a six- ring boundary at the wall is made, leaving the ends of the alternating magnets visible. The magnetic field lines terminate at the magnet face, resulting in a cusp magnetic field with field lines perpendicular to the wall at the magnet.PDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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