Sandwich structured ceramic matrix composites with periodic cellular ceramic cores: an active cooled thermal protection for space vehicles

2016 ◽  
Vol 154 ◽  
pp. 61-68 ◽  
Author(s):  
Luca Ferrari ◽  
Maurizio Barbato ◽  
Burkard Esser ◽  
Ivaylo Petkov ◽  
Markus Kuhn ◽  
...  
Keyword(s):  
Thermal Protection ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Space Vehicles ◽  
Matrix Composites ◽  
Cellular Ceramic

INTRODUCTION TO C3HARME PROJECT

2021 ◽  
Author(s):  
LUCA ZOLI ◽  
DILETTA SCITI
Keyword(s):  
High Temperature ◽  
High Speed ◽  
Thermal Protection ◽  
Weight Ratio ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Matrix Composites ◽  
Thermal Protection Systems ◽  
Protection Systems ◽  
Ultra High Temperature

High-speed aviation brings many challenges, one being the materials used ensure the aircraft and rockets travelling at hypersonic speed arrive at their destination safely. Control surfaces and thermal protection systems for vehicles flying at Mach 5 or above must withstand extremely hot temperatures and intense mechanical vibrations at launch, during cruising and re-entry into the Earth’s atmosphere. UHTCMCs (Ultra-High Temperature Ceramic Matrix Composites) belong to a new subclass of ceramic matrix composites (CMCs) with superior properties in terms of structural and chemical stability at elevated temperature and erosion/ablation resistance keeping excellent strength-to-weight ratio, thermal shock resistance and adequate damage tolerance. They are the latest potential candidates for thermal protection systems (TPSs), able to outperform bulk ultra-high temperature ceramics (UHTCs). C3HARME is a 4-years EU funded program involving 12 European partners from 6 countries focused on the design, fabrication and testing of UHTCMCs for nearzero erosion nozzles and near-zero ablation TPS tiles. C3harme will look at different technologies coming from the science of bulk ceramics and CMCs and combine them to find out new approaches for their manufacturing. Novel theoretical models and testing methodologies are necessary to characterize properly these materials. This talk will summarize some of the findings and advances of the program, with special emphasis on the innovative approaches that we have implemented.

scholarly journals Study on Impact Resistance of C/SiC Ceramic Matrix Composites for Thermal Protection of the Aerospace Vehicle

2021 ◽  
Vol 2021 ◽  
pp. 1-10
Author(s):  
Ye Lin ◽  
Bin Liu
Keyword(s):  
Residual Strength ◽  
Structural Integrity ◽  
Thermal Protection ◽  
Impact Damage ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Structure Design ◽  
Matrix Composites ◽  
Sic Composites ◽  
The Impact

This paper evaluates the impact damage tolerance of ceramic matrix composites and contrasts their tensile and compression strengths under impact and nonimpact conditions. The representative C/SiC composites from PIP are examined under the dropped tip system. In this paper, the surface impact test of C/SiC composites is carried out. By testing a series of specimens of various impact energies, the tensile and compression properties after impact are studied. Meanwhile, by comparing the changes of the specimens after impact and nonimpact, the fracture process, fracture modes, and residual strength are investigated. The results indicate that the residual tensile strength after impact reduces greatly, compared with the nonimpact material, by about 25%–45%, while the compression strength reduces slightly. The residual strength of tension and compression illustrates that low-energy impact effect on the structural integrity must be given priority in the thermal protection structure design of astronautics and aeronautics.

A Study of Bridged Delaminations in High Temperature Laminates Under Heat Flux Loading

Materials ◽  
2003 ◽  
Author(s):  
Thomas Siegmund ◽  
Ashwin Hattiangadi
Keyword(s):  
Heat Flux ◽  
High Temperature ◽  
Thermal Loading ◽  
Significant Contribution ◽  
Thermal Protection ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
High Heat ◽  
Heat Fluxes ◽  
Matrix Composites

High temperature ceramic matrix composites (CMCs) are material considered in many applications where high heat fluxes constitute a significant contribution to loading. The laminates can fulfill their function as thermal protection layers only if they stay intact, i.e. without internal delaminations or spalling, such that the heat flux remains undisturbed by such events. Crack bridging is an important effect in CMCs, and its implication to CMC laminates under thermal loading is investigated.

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