Thermographic Characterization and Comparison of 200W and 600W Hall Thrusters

@inproceedings{Matlock2007ThermographicCA,
  title={Thermographic Characterization and Comparison of 200W and 600W Hall Thrusters},
  author={Taylor Scott Matlock and W A Hargus and Carlton F. W. Larson},
  year={2007}
}
Thermal analysis of Hall thrusters is necessary for both performance optimization and spacecraft integration. The thermal characteristics of the thruster influence the lifetime, energy losses, and spacecraft integration. The lifetime of most Hall thrusters is limited by the erosion of the insulating materials within the discharge chamber, which may vary with temperature. Thruster thermal data are also indicative of thruster energy losses as well as the heating characteristics of spacecraft… CONTINUE READING

References

Publications referenced by this paper.
SHOWING 1-8 OF 8 REFERENCES

Surface temperature influence onto ceramic sputtering rate

A. A. Semenov
  • 2007

12S

Joint Propulsion Conference, AZ Tucson, July
  • Mazouffre, P. Echegut, and M. Dudeck. A calibrated infrared imaging study on the steady state thermal behaviour of
  • 2005

9R

Conference, FL Ft Lauderdale, July
  • Jankovsky, C. McLean, and J. McVey. Preliminary evaluation of a 10kw hall thruster. In 37th AIAA Aerospace
  • 2004

8D

June
  • Jacobsen, D. Manzella, R. Hofer, and P. Peterson. Nasa’s 2004 hall thruster program. In 40th Joint Propulsion
  • 1999

Thermal analysis of a stationary plasma thruster

Roche
  • AIAA,
  • 1998

6M

CA San Diego, July
  • Domonkos, A. Gallimore, and M. Patterson. Thermographic investigation of 3.2 mm diameter orificed hollow cathodes.
  • 1995