Parts application analysis - Array D Redundant Command Receiver

dc.contributor.author	Fox, T. W.
dc.date.accessioned	2015-09-09T22:30:14Z
dc.date.available	2015-09-09T22:30:14Z
dc.date.issued	1971
dc.description.abstract	The purpose of the Parts Application Analysis is to determine the stress level for each part in ea.ch application and to identify any part(s) that is stressed beyond its recommended derating. In this analysis the amount of derating was determined from parts ratings at an operating temperature of 75°C, which represents the maximum temperature anticipated during 2 years of lunar surface operation.
dc.description.statementofresponsibility	summarized by T. W. Fox.
dc.format.extent	60 leaves
dc.format.mimetype	application/pdf
dc.identifier.other	31111000670032
dc.identifier.uri	https://hdl.handle.net/20.500.11753/386
dc.language.iso	en
dc.publisher	Bendix Aerospace Systems Division
dc.relation.ispartofseries	ALSEP technical memorandum
dc.source.uri	https://www.lpi.usra.edu/lunar/ALSEP/pdf/31111000670032.pdf
dc.subject.lcc	TL789.8.U6A5
dc.subject.lcsh	Apollo Lunar Surface Experiments Package
dc.title	Parts application analysis - Array D Redundant Command Receiver

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