The impelling demand for materials able to operate at temperature above 2000 °C pushes the scientific research towards continuous search of materials possessing a combination of properties more and more challenging. C/SiC composites are currently the most used materials for aerospace applications, such as nose cones, leading edges and rocket nozzles, owing to excellent mechanical properties and thermal shock resistance but their operational limit is ~1600 °C. ISTEC activities have been recently focused on fabrication of continuous carbon fiber reinforced ZrB2- and ZrC- based ceramic matrix composites (UHTCCs) which have the potential to operate above 2000 °C. This lecture illustrates processing techniques and characterization of unidirectional (1D) UHTCMCs focusing on the aspects of matrix densification, fiber/matrix interface, fracture behavior, thermal shock and oxidation behavior.
Mechanical Properties and Microstructure of Unidirectional UHTCCs
L ZOLI;A VINCI;S FAILLA;P GALIZIA;D SCITI
2018
Abstract
The impelling demand for materials able to operate at temperature above 2000 °C pushes the scientific research towards continuous search of materials possessing a combination of properties more and more challenging. C/SiC composites are currently the most used materials for aerospace applications, such as nose cones, leading edges and rocket nozzles, owing to excellent mechanical properties and thermal shock resistance but their operational limit is ~1600 °C. ISTEC activities have been recently focused on fabrication of continuous carbon fiber reinforced ZrB2- and ZrC- based ceramic matrix composites (UHTCCs) which have the potential to operate above 2000 °C. This lecture illustrates processing techniques and characterization of unidirectional (1D) UHTCMCs focusing on the aspects of matrix densification, fiber/matrix interface, fracture behavior, thermal shock and oxidation behavior.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
