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High Energy Plume Impingement on Spacecraft Systems AFOSR Telecon

This report covers Langmuir Probe data analysis of high-energy plume impingement on spacecraft systems. The post-processing of data is ongoing, revealing unique plasma characteristics. Future work includes completing data analysis, conducting material experiments, and studying solar cell technology and interconnectors.

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High Energy Plume Impingement on Spacecraft Systems AFOSR Telecon

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  1. High Energy Plume Impingement on Spacecraft SystemsAFOSR Telecon Jarred Alexander Young October 22, 2013

  2. Current Events • Langmuir Probe testing • Testing completed • Post-processing underway • Power Supply • Basic design received • Checked ion source for possible arcing at higher voltage levels • Material Testing • Designed specimen holder for Al needles

  3. Langmuir Probe Data • Post-processing underway on all data • Using Chen analysis programs • Parameters haven’t been found yet • Data may be representative of a shifted Maxwellian due to non-standard plasma environment

  4. Langmuir Probe Data from NEXT Thruster array • Beam energy: ~1800 V • Beam Current: 3.52 A • Plasma Potentials: 1.5-3 V • Electron Temperature: ~0.6-1 eV • From: Foster, et al., Plasma Characteristics in the Plume of a NEXT Multi-Thruster Array (2006)

  5. Langmuir Probe Data from SPPL-1 • Probe starts to attract electrons around ~190 V inside the ion beam • May be possible that this data represents a shifted Maxwellian due to low densities in the beam • Dominated by beam ion velocity

  6. Future Work • Finish probe data post processing • Provide data to Burak • Material Experiments • Perform re-do of Aluminum experiments • Start on Mylar experiments • Looking into Solar cells and solar cell interconnectors

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