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High Energy Plume Impingement on Spacecraft Systems AFOSR Telecon

High Energy Plume Impingement on Spacecraft Systems AFOSR Telecon. Jarred Alexander Young October 22, 2013. Current Events. Langmuir Probe testing Testing completed Post-processing underway Power Supply Basic design received

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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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