Abstract Thermal Protection System (TPS) is an essential component of space vehicles to
protect them against the aerothermal heating imposed on them during the atmospheric …

Materials capable of oxidizing in a protective manner at ultrahigh (> 1700° C) temperatures
are needed to push beyond this barrier defined by SiC. Although possessing attractive …

Qualification and reusability campaigns were performed on ultra-high temperature ceramic
matrix composites (UHTCMCs) made of a ZrB 2-SiC matrix with short/long carbon fibre to …

An experimental campaign has been carried out to characterize a new class of Ultra-High-
Temperature Ceramic Matrix Composites for near-zero ablation Thermal Protection …

Composites based on hafnium carbide and reinforced with continuous naked carbon fiber
with and without PyC interface were prepared at low temperature by precursor infiltration …

The oxidation resistance of ultra-high-temperature ceramic material (HfB 2-30 vol% SiC)-2
vol% rGO (rGO: reduced graphene oxide) under long-term exposure (2000s) to a supersonic …

This paper presents the results of experimental tests for the characterization of Ultra-High-
Temperature Ceramic Matrix Composite (UHTCMC) materials for near-zero erosion rocket …

C f/SiC and C f/ZrC-SiC composites were fabricated via a novel combined process, which
achieved a lower open porosity below 8% compared with the single PIP process …

The effects of SiC content on aero-thermal resistance capabilities of ZrB 2-xSiC-5Y 2 O 3
ceramics (x= 5, 10, 15, 18.5 vol%) in atmospheric re-entry environment were investigated …

Abstract C/C-SiC-HfC composites were fabricated by using Precursor Infiltration and
Pyrolysis (PIP) combined with Gaseous Silicon Infiltration (GSI) process. Different GSI …