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Thermo-chemical surface instabilities of SiC-ZrB2 ceramics in high enthalpy dissociated supersonic airflows
Affiliation:1. National Research Council of Italy, Institute of Science and Technology for Ceramics, Via Granarolo, 64-48018 Faenza (RA), Italy;2. University of Naples “Federico II”, Dept. Industrial Engineering, Aerospace Engineering Division, P.le V. Tecchio, 80- 80125 Napoli, Italy;1. School of Materials Science and Engineering, Beijing Institute of Technology, Beijing, 100081, China;2. National Key Laboratory of Science and Technology on Materials Under Shock and Impact, Beijing, 100081, China;3. Fuzhou QiYue Ceramic Powder Co., Ltd, Fuzhou, 350301, China;1. Institute of Space Systems (IRS), University of Stuttgart, Pfaffenwaldring 29, 7569-Stuttgart, Germany;2. German Aerospace Center (DLR), Pfaffenwaldring 38-40, 70569-Stuttgart, Germany;1. Key Laboratory of Inorganic Coating Materials, Shanghai Institute of Ceramics, Chinese Academy of Sciences, Shanghai, 200050, China;2. Research Center of Composite Materials, Shanghai University, Shanghai, 200072, China;3. The State Key Lab of High Performance Ceramics and Superfine Microstructure, Shanghai Institute of Ceramics, Chinese Academy of Sciences, Shanghai, 200050, China;1. PROMES-CNRS Laboratory, 7 rue du four solaire, 66120 Font-Romeu Odeillo, France;2. von Karman Institute for Fluid Dynamics, 72 Chaussée de Waterloo, 1640 Rhode St Genèse, Belgium;3. Research Group Electrochemical and Surface Engineering, Vrije Universiteit Brussel, Pleinlaan 2, B-1050 Elsene/Brussel, Belgium;4. University of Tuebingen, Department of Geosciences, Applied Mineralogy, Wilhelmstrasse 56, 72074 Tuebingen, Germany;1. State Key Laboratory for Powder Metallurgy, Central South University, Changsha 410083, PR China;2. Advanced Research Center, Central South University, Changsha 410083, PR China
Abstract:The response of three different SiC-ZrB2 ceramics obtained by hot-pressing was studied at typical conditions of thermal protection systems of a re-entry spacecraft. Button-like lab-scale demonstrators were manufactured and tested in high enthalpy dissociated supersonic airflows using an arc-jet ground facility. Under severe aero-heating of up to 21 MJ/kg of specific total enthalpy and 3.5 MW/m2 of (cold-wall) heat flux the SiC-ZrB2 UHTC buttons endured rather well, though thermo-chemical surface instabilities started taking place for side wall surface temperatures of some buttons above 2050 K. The experimental determinations of the surface temperature, correlated to the microstructure changes occurred during testing, allowed to interpret the observed phenomena. Potentials and limits of the oxidation-resistant SiC-ZrB2 system to withstand such extreme conditions were outlined.
Keywords:SiC particulate UHTC composites  Thermo-mechanical properties  Thermo-chemical surface instabilities under severe aero-heating  Oxidation  CFD
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