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Performance of a flight qualified, thermoelectrically temperature controlled QCM sensor with power supply, thermal controller and signal processorA thermoelectrically temperature controlled quartz crystal microbalance (QCM) system was developed for the measurement of ion thrustor generated mercury contamination on spacecraft. Meaningful flux rate measurements dictated an accurately held sensing crystal temperature despite spacecraft surface temperature variations from -35 C to +60 C over the flight temperature range. An electronic control unit was developed with magentic amplifier transformer secondary power supply, thermal control electronics, crystal temperature analog conditioning and a multiplexed 16 bit frequency encoder.
Document ID
19810005646
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wallace, D. A.
(Berkeley Industries Laguna Beach, CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1980
Publication Information
Publication: NASA. Johnson Space Center The 11th Space Simulation Conf.
Subject Category
Spacecraft Propulsion And Power
Accession Number
81N14158
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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