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dc.contributor.authorBarcena, Jorge
dc.contributor.authorFlorez, Sonia
dc.contributor.authorPerez, Beatriz
dc.contributor.authorBouilly, Jean-Marc
dc.contributor.authorPinaud, Gregory
dc.contributor.authorFischer, Wolfgang P.
dc.contributor.authorde Montbrun, Agnes
dc.contributor.authorDescomps, Michel
dc.contributor.authorZuber, Christian
dc.contributor.authorRotaermel, Waldermar
dc.contributor.authorHermann Hald, Ing
dc.contributor.authorPortela, Pedro
dc.contributor.authorMergia, Konstantina
dc.contributor.authorTriantou, Kostoula
dc.contributor.authorVekinis, George
dc.contributor.authorStefan, Adriana
dc.contributor.authorBan, Cristina
dc.contributor.authorIonescu, Gheorghe
dc.contributor.authorBernard, Dominique
dc.contributor.authorLeroy, Vincent
dc.contributor.authorMassuti, Bartomeu
dc.contributor.authorHerdrich, Georg H.
dc.date.accessioned2017-03-09T10:38:25Z
dc.date.available2017-03-09T10:38:25Z
dc.date.issued2014
dc.identifier.citationJorge Barcena, Sonia Florez, Beatriz Perez, Jean-Marc Bouilly, Gregory Pinaud, Wolfgang P. Fischer, Agnes de Montbrun, Michel Descomps, Christian Zuber, Waldermar Rotaermel, Ing Hermann Hald, Pedro Portela, Konstantina Mergia, Kostoula Triantou, George Vekinis, Adriana Stefan, Cristina Ban, Gheorghe Ionescu, Dominique Bernard, Vincent Leroy, Bartomeu Massuti, and Georg H. Herdrich, Novel Hybrid Ablative/Ceramic Development for Re-Entry in Planetary Atmospheric Thermal Protection: Interfacial Adhesive Selection and Test Verification Plan, 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Atlanta, GA.en
dc.identifier.urihttp://hdl.handle.net/11556/380
dc.description.abstractThe FP7 project HYDRA addresses the development of a hybrid thermal protection solution, where a low density ablator is attached on top of a thermo-structural ceramic core by means of the use of high temperature adhesives. The project aims to design, integrate and verify a robust and lightweight thermal shield solution for atmospheric earth re-entry. The main advantage of a hybrid heat-shield is based on the capability of the thin ablative top layer to bear high thermal loads, while the tough ceramic composite underneath provides structural support.en
dc.description.sponsorshipEuropean Commission FP7, 283797, HYDRAen
dc.language.isoengen
dc.publisherAIAA American Institute of Aeronautics and Astronauticsen
dc.titleNovel Hybrid Ablative/Ceramic Development for Re-Entry in Planetary Atmospheric Thermal Protection: Interfacial Adhesive Selection and Test Verification Planen
dc.typeconferenceObjecten
dc.identifier.doi10.2514/6.2014-2373en
dc.isiNoen
dc.relation.projectIDinfo:eu-repo/grantAgreement/EC/FP7/283797/EU/Hybrid Ablative Development for Re-Entry in Planetary Atmospheric Thermal Protection/HYDRAen
dc.rights.accessRightsembargoedAccessen
dc.subject.keywordsThermal Protection Systemsen
dc.subject.keywordsAtmospheric Re-entryen
dc.subject.keywordsAblative materialsen
dc.subject.keywordsCeramic Matrix Compositesen


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