Ceramic Composites and Thermal Protection Systems for Reusable Re-Entry Vehicles

Next generation of reusable launch vehicles and new hypersonic space vehicle conceptsare currently under development, moving from traditional aerodynamic configuration towardsslender profiles. Main expected benefits are reduction of drag, enhancement in lift-to-drag ratio andreduction of interferences with radio frequency transmissions during the re-entry. Flexibility indesigning sharp profiles is strictly conditioned to the availability of suitable materials andprocessing technologies, required to fabricate components and surfaces able to withstand higherheat fluxes induced by the new profiles. Advances in the field of CMC's for high temperaturestructures and TPS are the basis for innovative approaches to the design of future RLV's. Besidebaseline solutions, already available and well characterized, as for C/SiC CMC's, ultra hightemperature ceramics seem to offer the right chance to fabricate hot structures having the requiredheat-resistant and load carrying capabilities. This paper deals with technologies based on the use ofdiboride based CMC's which can be considered promising candidate materials for the fabrication ofhot structures of slender bodies, such as nose cap and wing leading edges. Recent experimentalresults will be presented and discussed