No abstract

No abstract

To understand the interaction between the SPT-100 thruster and the spacecraft, accurate knowledge of exhaust plume properties must be obtained. This investigation utilized a suite of interrelated diagnostic probes in an effort to provide detailed knowledge of the exhaust plume on a molecular kinetic level. Probes used for the investigation included a retarding potential analyzer, a planar Faraday probe, an emissive probe, both total-and radiant-heat-ux probes, as well as a newly developed neutral particle ux probe. Combining the knowledge gained from these probes it was possible to quantify the transport of mass, energy, and charge within the plume at 0.5-and 1.0-m radius from the thruster exit. Among the phenomena uncovered were a high-energy ionic annulus surrounding a narrow low-energy core within the plume at 0.5-m radius from the thruster exit. This core structure was lled in at 1.0-m radius. Additionally, a population of energetic charge-exchange neutrals was found within 25 deg of the thruster centerline along with the corresponding low-energy charge-exchange ions attributed to plume/background gas interactions.

No abstract

The plasma properties of the very near-field (10 to 50 mm) plume of the D55 anode layer thruster (TAL) were measured as part of an effort lead by NumerEx of Albuquerque, NM to model the processes within TALs. The D55 is the 1.35 kW TAL counterpart to the SPT-100 and was made by TsNUMASH of Kaliningrad, Russia. The thruster was tested in the 6 m diameter by 9 m long vacuum chamber at (lie Plasmadynamics and Electric Propulsion Laboratory (PEPL), and the diagnostic probes were positioned using a three axis translation table system. A Faraday probe, water-cooled Hall probes, emissive probes, and Langmuir probes were used to examine the near-field plasma properties. Water-cooled Hall probes were employed to explore the effect of the closed drift current on the radial magnetic field. The change in the magnetic field due to the Hall current was found to be less than five percent over the region examined. Ion current density profiles showed that the annular beam focuses within 40 mm of the thruster exit plane. Similarly, the electron temperature and number density radial profiles showed peaks near the discharge chamber at 10 mm axially, and the peaks moved toward the axis within 40 mm. The peak electron temperature decreased with axial distance, while the number density remained approximately constant over the very near-field region.