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dc.contributor.authorFerrari, Luca
dc.contributor.authorBarbato, Maurizio
dc.contributor.authorEsser, Burkard
dc.contributor.authorPetkov, Ivaylo
dc.contributor.authorKuhn, Markus
dc.contributor.authorGianella, Sandro
dc.contributor.authorBarcena, Jorge
dc.contributor.authorJimenez, Christina
dc.contributor.authorFrancesconi, Daniele
dc.contributor.authorLiedtke, Volker
dc.contributor.authorOrtona, Alberto
dc.date.accessioned2017-03-08T13:19:26Z
dc.date.available2017-03-08T13:19:26Z
dc.date.issued2016-10-15
dc.identifier.citationLuca Ferrari, Maurizio Barbato, Burkard Esser, Ivaylo Petkov, Markus Kuhn, Sandro Gianella, Jorge Barcena, Christina Jimenez, Daniele Francesconi, Volker Liedtke, Alberto Ortona, Sandwich structured ceramic matrix composites with periodic cellular ceramic cores: an active cooled thermal protection for space vehicles, Composite Structures, Volume 154, 15 October 2016, Pages 61-68, ISSN 0263-8223, http://dx.doi.org/10.1016/j.compstruct.2016.07.043.en
dc.identifier.issn0263-8223en
dc.identifier.urihttp://hdl.handle.net/11556/377
dc.description.abstractCeramic cellular structures and ceramic matrix composites (CMCs), are promising materials for thermal protection systems (TPS) of future space vehicles. This is because of the good thermal properties of their cellular cores coupled with the matchless thermo-mechanical resistance of their CMC skins. A high temperature TPS with active cooling accomplished by flowing a gas into the sandwich’s core is investigated in this work. Three-dimensional thermo fluid dynamics analysis was first performed to evaluate the heat exchange in the ceramic sandwich under a Earth re-entry condition. The simulations, aiming at optimizing the TPS configuration, analysed several cellular ceramics structures by varying inlet and outlet positions, the coolant fluid and mass flows. A hexagonal cell was chosen as basic element of the porous ceramic. Sandwich structure components were produced and assembled by joining. Finally a prototypic leading edge was produced and tested in plasma wind tunnel in a standard re-entry condition. Cooling was performed with different gases and mass flows. Results are reported and discussed.en
dc.description.sponsorshipThe research leading to these results has received funding from the European Union Seventh Framework Programme (FP7/2007–2013) under grant agreement N° 312807.en
dc.language.isoengen
dc.publisherELSEVIER SCI LTD, THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLANDen
dc.titleSandwich structured ceramic matrix composites with periodic cellular ceramic cores: an active cooled thermal protection for space vehiclesen
dc.typearticleen
dc.identifier.doi10.1016/j.compstruct.2016.07.043en
dc.isiYesen
dc.relation.projectIDinfo:eu-repo/grantAgreement/EC/FP7/312807/EU/INNOVATIVE THERMAL MANAGEMENT CONCEPTS FOR THERMAL PROTECTION OF FUTURE SPACE VEHICLES/THORen
dc.rights.accessRightsembargoedAccessen
dc.subject.keywordsThermal Protection Systemsen
dc.subject.keywordsThermal Managementen
dc.subject.keywordsHypersonic Vehiclesen
dc.subject.keywordsCeramic Matrix Compositesen
dc.subject.keywordsCellular Ceramicsen
dc.identifier.essn1879-1085en
dc.journal.titleComposite Structuresen
dc.page.final68en
dc.page.initial61en
dc.volume.number154en


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