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dc.contributor.authorPetach, M.en_US
dc.contributor.authorDurand, D.en_US
dc.contributor.authorMichaelian, M.en_US
dc.contributor.authorRaab, J.en_US
dc.contributor.authorTward, E.en_US
dc.date.accessioned2011-04-28T15:32:53Z
dc.date.available2011-04-28T15:32:53Z
dc.date.issued2008-05
dc.identifier.isbn978-1-934021-02-6
dc.identifier.urihttp://hdl.handle.net/1853/38740
dc.descriptionPresented at the 16th International Cryocooler Conference, held May 17-20, 2008 in Atlanta, Georgia.en_US
dc.description.abstractNASA, under the Cryogenic Fluid Management (CFM) Project, in partnership with Ball Aerospace Technologies Corporation (BATC), conducted a reduced boil-off demonstration employing an actively cooled thermal radiation shield. The shield, designed and fabricated by NASA, consisted of overlapping panels of 1100 aluminum foil, and three parallel 1/8 inch cooling lines attached to the foil with adhesive and communicating with 1/4 inch inlet and outlet manifolds. The shield and gas distribution network were instrumented and integrated with BATC's 500 L liquid nitrogen (LN2) cryogenic propellant tank simulator, high-performance multi-layer insulation (MLI), and a cryocooler and pressurized helium circulator. Two test conditions were run to evaluate the thermal performance of the system. An initial test was performed to measure the baseline or passive steady state heat leak into the LN2 tank. In the second test, the cryocooler/circulator was driven at maximum power until the system again reached steady state. By removing heat from both the shield and the tank support structure via the circulating helium stream, the average shield temperature dropped from ~228 K to ~132 K and the total heat leak into the tank was reduced by 82 %. This was despite the fact that the flow rate in the distribution network was unexpectedly low due to a partial blockage in one of the recuperators.en_US
dc.language.isoen_USen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesCryocoolers 16. Cryocoolers for 1-30 K aerospace applicationsen_US
dc.subjectCryocoolers for 1-30 k aerospace applicationsen_US
dc.subjectCryogenic Fluid Management Projecten_US
dc.subjectActively cooled thermal radiation shielden_US
dc.titleMIRI Cooler System Design Updateen_US
dc.typeProceedingsen_US
dc.contributor.corporatenameNorthrop Grumman Aerospace Systemsen_US
dc.publisher.originalICC Pressen_US


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