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Europa Clipper Thermal Control Design

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dc.contributor.author Ochoa, Hared A.
dc.contributor.author Hua, Jenny
dc.contributor.author Lee, Raymond
dc.contributor.author Mastropietro, A.J.
dc.contributor.author Bhandari, Pradeep
dc.date.accessioned 2020-05-05T21:11:10Z
dc.date.available 2020-05-05T21:11:10Z
dc.date.issued 2018-07-08
dc.identifier.citation 48th International Conference on Environmental Systems (ICES), Albuquerque, New Mexico, July 8 - July 12, 2018 en_US
dc.identifier.clearanceno 18-2212
dc.identifier.uri http://hdl.handle.net/2014/48271
dc.description.abstract This paper details the design developments of the Europa Clipper spacecraft thermal control system and its primary element the Heat Redistribution System (HRS). The Europa Clipper spacecraft will launch in the early 2020s and will have multiple flybys of Jupiter’s icy moon, Europa. The HRS, which utilizes a Mechanically Pumped Fluid Loop (MPFL) to reclaim waste heat from an avionics vault module and redistribute it to the propulsion module and radiator, has become an integral part of the spacecraft architecture both in terms of mechanical configuration and spacecraft operations capability. A walkthrough on the planned implementation of the HRS on the primary spacecraft modules is provided along with a description on thermal control of spacecraft hardware not located on the HRS vault, where thermal isolation and tolerance to extreme thermal environment drives the hardware designs. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA: Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2018 en_US
dc.title Europa Clipper Thermal Control Design en_US
dc.type Preprint en_US


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