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Analysis of High-Energy Plume Impingement on Spacecraft Systems

Preliminary analysis of beam data focusing on energy levels, flux values, and engine settings. Notes on beam testing challenges and sputtering damage observed. Upcoming tasks include continued beam testing and plasma characteristic measurements to aid in post-processing.

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Analysis of High-Energy Plume Impingement on Spacecraft Systems

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  1. High Energy Plume Impingement on Spacecraft SystemsAFOSR Telecon Jarred Alexander Young November 26, 2012

  2. Preliminary Beam Analysis • RPA positioned ~4” away from beam exit • Using sourcemeter readings to analyze beam energy • Energy peaks seen in the 180-220 eV range • Preliminary Flux Values: 6.2E14 #/m2-s • Engine Settings of shown beam data (voltages relative to ground) • Anode: 211 V • Discharge: 136 .7 V • Accel: -291 V • Filament Current: 5.5 A

  3. Notes on Beam Testing • Low beam current due to power supply issues • Emitter filament experiencing intermittent functionality • Supply would show voltage but no current shown • Spoke with Acopian engineers about filament supply • Supply must be returned; should be back by end of week • Dirty voltage adjust potentiometer causing malfunction • Will be able to finish working on test matrix at that point

  4. Sputtering Damage • RPA grounding plate exposed to ion beam • Golden discoloration all over plate, fingerprint residue burned onto plate, brass screws discolored • Ion beam sputtered brass and deposited on plate (?) Damaged Brass screw Manufacturer fingerprint

  5. Upcoming Tasks • Continue beam testing across different thruster settings • Gather Plasma characteristics for each setting as well using Langmuir probe • Gather current measurements on all power supplies • Possible measure of total beam current • Aid with post processing

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