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Goal: Advance a key technology for the Planetary Defense technique known as Ion Beam Deflection (IBD) Gap: Current Planetary Defense concepts are not well suited to the most likely sized threat object (50 m to 140 m diameter).3 Ion beam deflection—in which an ion beam is directed to impact the threat object—is superior to other concepts for the asteroid size range of interest. It is independent of the characteristics of the threat object (material, density, strength, rotation state), takes only weeks to a few months to provide sufficient deflection, and is gentle enough to not disrupt the body. High-power electric propulsion systems are becoming available which are essential for Ion Beam Deflection including NASA’s Power and Propulsion Element (PPE)—63 kW solar array and JPL’s NEXIS gridded ion thruster (20-kW per thruster). Small ion beam divergence angles, ≤ ~4 degrees, are needed to enable sufficient stand-off distances during deflection operations; however current state-of-the-practice ion optics provide ion beam divergence angles of > 20 degrees. Innovation: Develop slotted-carbon-carbon composite grids for ultra-low ion beam divergence Approach: Design, fabricate and test flat ion optics for ultra-low beam divergence. Need flat ion optics electrodes to get low ion beam divergence at hundreds of meters. Use carbon-carbon materials for flat grids (zero to slightly negative coefficient of thermal expansion). Convert upstream side to insulator (silicon carbide) to create single-grid composite ion optics. Experimentally test at GRC to demonstrate ion beam divergence angles of ≤ 4 degrees and compare with model results
Demonstration of such low ion beam divergence angles will establish the validity of ion beam deflection for planetary defense
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