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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Chapter 5 Ion Thruster Accelerator Grids Ion thrusters are characterized by the electrostatic acceleration of ions extracted from the plasma generator [1]. An illustration of a direct current (DC) electron bombardment ion thruster showing the ion accelerator, the plasma generator, and the neutralizer cathode was shown in Fig. 1-1. The ion accelerator consists of electrically biased multi-aperture grids, and this assembly is often called the ion optics. The design of the grids is critical to the ion thruster operation and is a trade between performance, life, and size. Since ion thrusters need to operate for years in most applications, life is often a major design driver. However, performance and size are always important in order to satisfy the mission requirements for thrust and specific impulse (Isp) and to provide a thruster size and shape that fits onto the spacecraft. There are many factors that determine the grid design in ion thrusters. The grids must extract the ions from the discharge plasma and focus them through the downstream accelerator grid (accel grid) and decelerator grid (decel grid) (if used). This focusing has to be accomplished over the range of ion densities produced by the discharge chamber plasma profile that is in contact with the screen grid, and also over the throttle range of different power levels that the thruster must provide for the mission. Since the screen grid transparency was shown in Chapter 4 to directly impact the discharge loss, the grids must minimize ion impingement on the screen grid and extract the maximum number of the ions that are delivered by the plasma discharge to the screen grid surface. In addition, the grids must minimize neutral atom loss out of the discharge chamber to maximize the mass utilization efficiency of the thruster. High ion transparency and low neutral transparency drives the grid design toward larger screen grid holes and smaller accel grid holes, which impacts the optical focusing of the ions and the beam divergence. The beam divergence also should be minimized to reduce thrust loss and plume impact on the spacecraft or solar arrays, although some amount of beam divergence can usually be 189

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