Thermo-mechanical performance of an ablative/ceramic composite hybrid thermal protection structure for re-entry applications

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.