Browsing by Keyword "Ceramic Matrix Composites"
Now showing 1 - 3 of 3
Results Per Page
Sort Options
Item Infra-red and vibration tests of hybrid ablative/ceramic matrix technological breadboards for earth re-entry thermal protection systems(2017-05-03) Barcena, Jorge; Garmendia, Iñaki; Triantou, Kostoula; Mergia, Konstatina; Perez, Beatriz; Florez, Sonia; Pinaud, Gregory; Bouilly, Jean-Marc; Fischer, Wolfgang P.P.; EXTREMAT; POLIMEROSA 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/m2) and vibration test under launcher conditions (Volna and Ariane 5). Sub-scale tile samples (100×100 mm2) 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.Item Novel Hybrid Ablative/Ceramic Development for Re-Entry in Planetary Atmospheric Thermal Protection: Interfacial Adhesive Selection and Test Verification Plan: Interfacial adhesive selection and test verification plan(AIAA American Institute of Aeronautics and Astronautics, 2014) Barcena, Jorge; Florez, Sonia; Perez, Beatriz; Bouilly, Jean-Marc; Pinaud, Gregory; Fischer, Wolfgang P.; de Montbrun, Agnes; Descomps, Michel; Zuber, Christian; Rotaermel, Waldermar; Hermann Hald, Ing; Portela, Pedro; Mergia, Konstantina; Triantou, Kostoula; Vekinis, George; Stefan, Adriana; Ban, Cristina; Ionescu, Gheorghe; Bernard, Dominique; Leroy, Vincent; Massuti, Bartomeu; Herdrich, Georg H.; Marinou, A.; Massuti, T.; EXTREMAT; POLIMEROSThe 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.Item Sandwich structured ceramic matrix composites with periodic cellular ceramic cores: an active cooled thermal protection for space vehicles: an active cooled thermal protection for space vehicles(2016-10-15) Ferrari, Luca; Barbato, Maurizio; Esser, Burkard; Petkov, Ivaylo; Kuhn, Markus; Gianella, Sandro; Barcena, Jorge; Jimenez, Christina; Francesconi, Daniele; Liedtke, Volker; Ortona, Alberto; EXTREMATCeramic 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.