Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
817217 | Composites Part B: Engineering | 2015 | 7 Pages |
Abstract
Hybrid thermal protection systems for aerospace applications based on ablative material (ASTERMâ¢) and ceramic matrix composite (SICARBONâ¢) 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.
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Authors
K. Triantou, K. Mergia, S. Florez, B. Perez, J. Barcena, W. Rotärmel, G. Pinaud, W.P.P. Fischer,