Date of Award:
5-2016
Document Type:
Thesis
Degree Name:
Master of Science (MS)
Department:
Physics
Committee Chair(s)
J. R. Dennison
Committee
J. R. Dennison
Committee
Vince Wickwar
Committee
Farrell Edwards
Abstract
An existing space environment simulation test chamber used in the study of electron emission, sample charging and discharge, electrostatic discharge and arcing, electron transport, and luminescence of spacecraft materials now has extended temperature control capabilities. By incorporating a two-stage, closed-cycle helium cryostat, it is now possible to simulate the temperature typical spacecraft will experience when in orbit, ranging from < 40 K to > 450 K. The system was designed to maintain compatibility with an existing ultrahigh vacuum chamber that can simulate diverse space environments. This vacuum chamber can simulate space environment conditions by producing the same pressure, amount of electrons, electromagnetic radiation and temperature a typical satellite may experience when in orbit. For testing, multiple cameras are positioned to view the spacecraft sample to measure the amount of light that may be emitted from the sample. This is important, especially for space-based optical observatories where light contamination is of concern. The cryostat system can also be adapted for use in other test facilities, as well as in a standalone configuration for specific tests that involve low-temperature electronic conductivity tests.
Checksum
e85e23a59909e085ef87d117c7d18f8a
Recommended Citation
Dekany, Justin, "Cryostat System for Spacecraft Materials Testing" (2016). All Graduate Theses and Dissertations, Spring 1920 to Summer 2023. 5014.
https://digitalcommons.usu.edu/etd/5014
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