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Electron penetration of spacecraft thermal insulationThe external thermal blanket with 13 mils of polyethylene which has the known range and stopping power as a function of electron energy is investiated. The most recent omnidirectional peak Jovian electron flux at 5 Jupiter radii is applied, the electron current penetrating the thermal blanket is calculated and allowed to impinge on a typical 20 mil polyethylene insulator surrounding a wire. The radiation dose rate to the insulator is then calculated and the electrical conductivity found. The results demonstrate that the increased electronic mobility is sufficient to keep the maximum induced electric field two orders of magnitude below the critical breakdown strength.
Document ID
19820006347
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Powers, W. L.
(TRW Defense and Space Systems Group Redondo Beach, CA, United States)
Adams, B. F.
(TRW Defense and Space Systems Group Redondo Beach, CA, United States)
Inouye, G. T.
(TRW Defense and Space Systems Group Redondo Beach, CA, United States)
Date Acquired
August 10, 2013
Publication Date
October 1, 1981
Publication Information
Publication: NASA. Lewis Research Center Spacecraft Charging Technol., 1980
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
82N14220
Funding Number(s)
CONTRACT_GRANT: JPL-955500
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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