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Thermo-mechanical performance of an ablative/ceramic composite hybrid thermal protection structure for re-entry applications
Affiliation:1. National Centre for Scientific Research “Demokritos”, Athens Gr-15310, Greece;2. Tecnalia Research & Innovation, Donostia-San Sebastian E-2009, Spain;3. German Aerospace Center (DLR), 70569 Stuttgart, Germany;4. Airbus Defense & Space, Saint Médard en Jalles F-33165, France;5. Airbus Defense & Space, Bremen D-28199, Germany;1. School of Materials Science and Engineering, Engineering Research Institute, Gyeongsang National University, Jinju 660-701, Republic of Korea;2. School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Republic of Korea;3. Agency for Defense Development, 4-R&D Center, Daejeon 305-600, Republic of Korea;4. Department of Mechanical Engineering, The University of Utah, Salt Lake City, UT 84112, USA;1. Centre for Advanced Structural Ceramics, Department of Materials, Imperial College, London SW7 2AZ, UK;2. Dstl, Porton Down, Salisbury, Wiltshire SP4 0JQ, UK;1. Institute of Advanced Structure Technology, Beijing Institute of Technology, Beijing 100081, PR China;2. Beijing Key Laboratory of Lightweight Multi-Functional Composite Materials and Structures, Beijing Institute of Technology, Beijing 100081, PR China;3. School of Mechanics, Civil Engineering and Architecture, Northwestern Polytechnical University, Xi''an 710072, PR China;1. 1320 Beal Ave., University of Michigan, Ann Arbor, Michigan 48109, USA;2. NASA Ames Research Center, MS 234-1, Moffett Field, CA 94035, USA;3. 3775 Discovery Dr, University of Colorado, Boulder, CO 80303, USA
Abstract:Hybrid thermal protection systems for aerospace applications based on ablative material (ASTERM?) and ceramic matrix composite (SICARBON?) have been investigated. The ablative material and the ceramic matrix composite were joined using graphite and zirconia–zirconium silicate based commercial high temperature adhesives. The thermo-mechanical performance of the structures was assessed from room temperature up to 900 °C. In all the joints there is a decrease of shear strength with the increase of temperature. Analysis of the fractured surfaces showed that above 150 °C the predominant mode of fracture is cohesive failure in the bonding layer. The joints fabricated with the zirconia–zirconium silicate based adhesive present the best performance and they have the potential to be used as hybrid thermal protection systems for aerospace applications in the temperature range 700–900 °C.
Keywords:A  Ceramic-matrix composites (CMCs)  A  Carbon fibre  B  Thermomechanical  E  Joints/joining
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