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Clementine Engineering Experiments Program.

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dc.contributor.author Garrett, H. B. en_US
dc.contributor.author Rustan, P.
dc.date.accessioned 2004-10-03T05:20:42Z
dc.date.available 2004-10-03T05:20:42Z
dc.date.issued 1995
dc.identifier.citation Journal of Spacecraft and Rockets. en_US
dc.identifier.clearanceno 95-1180
dc.identifier.uri http://hdl.handle.net/2014/31494
dc.description.abstract Spacecraft must survive and operate reliably in the space environment for long periods of time. Radiation, temperature variations, spacecraft charging, surface contamination, and micrometeoroids/space debris all present environmental challenges to spacecraft missions. The environmental issues associated with these effects require in-situ space experiments to properly quantify the environment and its effects. To obtain data on specific microelectronic and sensor systems in the space environment, several engineering experiments were developed for the Clementine spacecraft and the Clementine lunar transfer booster or Interstage Adapter Satellite (ISAS). These platforms allowed testing of advanced spacecraft microelectronic and sensor devices in a lunar transfer orbit that intersects Earth's radiation belts and debris environment and in interplanetary space where direct exposure to solar flares, Galactic Cosmic Rays, and micrometeoroids was possible. A suite of experiments was developed by the Naval Research Laboratory (NRL), the Jet Propulsion Laboratory (JPL), NASA Langley Research Center (LaRC), the Aerospace Corporation, and NASA Goddard Space Flight Center (GSFC) to investigate in detail specific radiation and environmental reliability issues. This paper presents an introduction to the issues being investigated, the instruments provided for the mission, and the rationale for the engineering program. en_US
dc.format.extent 1151754 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other Spacecraft reliability en_US
dc.title Clementine Engineering Experiments Program. en_US


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