Structural and Thermal Response of 30 CM Diameter Ion Thruster Optics

By: Nasa, National Aeronautics and Space Adm

Tabular and graphical data are presented which are intended for use in calibrating and validating structural and thermal models of ion thruster optics. A 30 cm diameter, two electrode, mercury ion thruster was operated using two different electrode assembly designs. With no beam extraction, the transient and steady state temperature profiles and center electrode gaps were measured for three discharge powers. The data showed that the electrode mount design had little effect on the temperatures, but significantly impacted the motion of the electrode center. Equilibrium electrode gaps increased with one design and decreased with the other. Equilibrium displacements in excess of 0.5 mm and gap changes of 0.08 mm were measured at 450 W discharge power. Variations in equilibrium gaps were also found among assemblies of the same design. The presented data illustrate the necessity for high fidelity ion optics models and development of experimental techniques to allow their validation. Macrae, G. S. and Zavesky, R. J. and Gooder, S. T. Glenn Research Center RTOP 506-42-31...

• Format: Paperback
• Language: English
• ISBN: 1729013341
• ISBN13: 9781729013342
• Release Date: January 1
• Publisher: Independently Published
• Length: 30 Pages
• Weight: 0.21 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"