Abstract
Hybrid thermal protection systems for aerospace applications based on ablative material (ASTERM (TM)) and ceramic matrix composite (SICARBON (TM)) 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 degrees 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 degrees 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 degrees C.
| Original language | English |
|---|---|
| Pages (from-to) | 159-165 |
| Number of pages | 7 |
| Journal | unknown |
| Volume | unknown |
| DOIs | |
| Publication status | Published - 1 Dec 2015 |
Keywords
- Ceramic-matrix composites
- Carbon fibre
- Thermomechanical
- Joints/joining
- A. Carbon fibre
- A. Ceramic-matrix composites (CMCs)
- B. Thermomechanical
- E. Joints/joining
Project and Funding Information
- Project ID
- info:eu-repo/grantAgreement/EC/FP7/283797/EU/HYBRID ABLATIVE DEVELOPMENT FOR RE-ENTRY IN PLANETARY ATMOSPHERIC THERMAL PROTECTION/HYDRA
- Funding Info
- European Project ‘‘HYDRA’’ (G.A. n. 283797) with the financial support by the European Commission.