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The Design of an Optimum System for Monitoring the Operational Status of a Spacecraft

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dc.contributor.author Simon, M. en_US
dc.contributor.author Vilnrotter, V. en_US
dc.contributor.author Mileant, A. en_US
dc.contributor.author Hinedi, S. en_US
dc.date.accessioned 2004-09-30T23:21:37Z
dc.date.available 2004-09-30T23:21:37Z
dc.date.issued 1996 en_US
dc.identifier.clearanceno 96-1368 en_US
dc.identifier.uri http://hdl.handle.net/2014/26492
dc.description.abstract The design of a spacecraft monitoring system based on a Neyman-Pearson Detection Criterion is discussed. Each noncatastrophic state of the spacecraft is indicated by the transmission of a specific signal to the ground station. Complete failure of the spacecraft is indicated by the transmission of no signal. The set of signals chosen to represent the spacecraft states consists of a group of orthogonally spaced (in frequency) carriers each with unknown (random) phase. en_US
dc.format.extent 2051632 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other spacecraft design Neyman-Pearson complete failure failure detection criterion spacecraft monitoring systems spacecraft monitoring en_US
dc.title The Design of an Optimum System for Monitoring the Operational Status of a Spacecraft en_US


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