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102 Chapter 4 created essentially a field-free region in the center of the thruster that produced uniform plasmas. The magnets in various versions of this concept were oriented in rings or in axial lines to provide plasma confinement. Moore biased the wall and magnets at cathode potential and placed the anodes inside the cusp fields, as shown in Fig. 4-8(e), to require that electrons diffuse across the field lines by collisions or turbulent transport before being lost. The permanent magnet ring- cusp thruster of Sovey [6] is shown in Fig. 4-8(f), which has become the most widely used thruster design to date. The divergent field Kaufman ion thruster matured in the 1970s with the development of 30-cm mercury thrusters [7,8]. Kaufman thrusters are described in more detail in Section 4.4. Concerns with using mercury as the propellant resulted in the development of xenon ion thrusters [9,10], which emerged at the same time that the benefits of ring-cusp confinement geometries became apparent [6,11,12]. The design and development of the NASA Solar Electric Propulsion Technology Applications Readiness (NSTAR) [13] and Xenon Ion Propulsion System (XIPS®) [14] flight thrusters in the 1990s was based on this early work. At this time, only two of these magnetic field geometries are still used in DC ion thrusters: the multipole magnetic field ring-cusp thrusters and the divergent solenoidal magnetic fields in Kaufman-type thrusters. Ring-cusp thrusters use alternating polarity permanent magnet rings placed around the anode-potential thruster body. Energetic electrons are injected along a weak diverging magnetic field at the cathode and demagnetize sufficiently to bounce from the surface magnetic fields until they either lose their energy by collisions or find a magnetic cusp to be lost to the anode. Kaufman thrusters inject energetic electrons along a strong diverging solenoidal magnetic field with the pole-pieces typically at cathode potential and rely on cross-field diffusion of the electrons to an anode electrode placed near the cylindrical wall to produce ionization and create a stable discharge. 4.3.1 Generalized 0-D Ring-Cusp Ion Thruster Model The idealized plasma-generator model developed in Section 4.2 is useful in describing how the discharge produces the plasma, but neglects many of the particle flows and energy transport mechanisms found in actual thrusters. The complete particle flows in a thruster discharge chamber are shown in Fig. 4-9. The primary electron current emitted by the hollow cathode, Ie , generates ions and plasma electrons. The ions flow to the accelerator structure ( Is ), to the anode wall ( Iia ), and back to the cathode ( Ik ). Some fraction of the primary electrons is lost directly to the anode at the magnetic cusp ( IL ). The plasma electrons are also predominately lost to the anode at the cusp ( Ia ), with only aPDF Image | Fundamentals of Electric Propulsion: Ion and Hall Thrusters
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