1 Infra-Red and vibration tests of hybrid ablative/ceramic matrix technological breadboards for earth re-entry thermal protection systems Jorge Barcena a,* , Iñaki Garmendia b , Kostoula Triantou c , Konstatina Mergia c , Beatriz Perez a , Sonia Florez a , Gregory Pinaud d , Jean-Marc Bouilly d and Wolfgang P.P. Fischer e a Industry and Transport Division, Tecnalia Research and Innovation, Mikeletegi Pasealekua 2, E-20009 Donostia-San Sebastian (Spain) b Department of Mechanical Engineering, University of the Basque Country UPV/EHU, Engineering School of Gipuzkoa, Plaza de Europa, 1, 20018 Donostia-San Sebastian (Spain) c Institute of Nuclear Technology and Radiation Protection N.C.S.R. "Demokritos", Aghia Paraskevi, 15310 Athens (Greece). d Reentry Systems and Technologies Department , Airbus Safran Launchers SAS, Rue du Général Niox – BP 20011, 33165 Saint Médard en Jalles (France) e Reentry Systems and Technologies Department , Airbus Safran Launchers GmbH, Airbus-Allee 1, D-28199 Bremen (Germany) ABSTRACT A new thermal protection system for atmospheric earth re-entry is proposed. This concept combines the advantages of both reusable and ablative materials to establish a new hybrid concept with advanced capabilities. The solution consists of the design and the integration of a dual shield resulting on the overlapping of an external thin ablative layer with a Ceramic Matrix Composite (CMC) thermo-structural core. This low density ablative material covers the relatively small heat peak encountered during re-entry the CMC is not able to bear. On the other hand the big advantage of the CMC based TPS is of great benefit which can deal with the high integral heat for the bigger time period of the re-entry. To verify the solution a whole testing plan is envisaged, which as part of it includes thermal shock test by infra-red heating (heating flux up to 1 MW/m 2 ) and vibration test under launcher conditions (Volna and Ariane 5). Sub-scale tile samples (100  100 mm 2 ) representative of the whole system (dual ablator/ceramic layers, insulation, stand-offs) are specifically designed, assembled and tested (including the integration of thermocouples). Both the thermal and the vibration test are analysed numerically by simulation tools using Finite Element Models. The experimental results are in good agreement with the expected calculated parameters and moreover the solution is qualified according to the specified requirements. Keywords: thermal protection systems, atmospheric re-entry, ceramic matrix composite, infra-red tests, vibration tests, atmospheric re-entry, adhesives, joining, ablative material