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

Simon, M.; Vilnrotter, V.; Mileant, A.; Hinedi, S.

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