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Diagnostic system design for the Ion Auxiliary Propulsion System (IAPS). Flight tests of two 8 cm mercury ionThe mechanical, thermal, electrical design and the ground test results of four types of detectors are explained. The DSS is designed to measure the thruster efflux material deposition and S/C potential relative to the local plasma in the vicinity of two 8 cm mercury ion thrusters. The DSS consists of two quartz crystal microbalance (QCM) detectors, one potential probe, nine solar cell arrays, seven ion collectors and two electronic packages.
Document ID
19810011644
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hurst, E. B. (NASA Lewis Research Center Cleveland, OH, United States)
Thomas, G. Z. (Hughes Aircraft Co. Los Angeles, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Spacecraft Instrumentation
Report/Patent Number
E-727
NASA-TM-81702
Report Number: E-727
Report Number: NASA-TM-81702
Meeting Information
Meeting: Intern. Elec. Propulsion Conf.
Location: Las Vegas, NV
Country: United States
Start Date: April 21, 1981
End Date: April 23, 1981
Sponsors: AIAA, Japan Society for Aeronautical and Space Sciences, DGLR
Accession Number
81N20172
Funding Number(s)
PROJECT: RTOP 542-05-12
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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