Dynamical and thermal qualification of the C–SiC nose for the IXV

The Intermediate experimental Vehicle (IXV) atmospheric re-entry demonstrator, developed within the FLPP (Future Launcher Preparatory Program) and funded by ESA, was aimed at developing a demonstration vehicle that gave Europe a unique opportunity to increase its knowledge in the field of advanced atmospheric re-entry technologies. Within this program, HERAKLES, Safran Group, was in charge of the TPS of the windward and nose assemblies of the vehicle, and has developed and manufactured SepcarbInox® Ceramic Matrix Composite (CMC) protection systems that provided a high temperature resistant nonablative outer mold line (OML) for enhanced aerodynamic control. A key component of this TPS is the nose assembly, which is one the most loaded part during re-entry. The paper describes the analysis activities that led to the qualification of the nose assembly, through two activities:•Dynamical behavior of the nose.•Thermal behavior of the nose For both cases, the paper shows how FE models, compared with tests results, led to the understanding and simulation of the nose assembly behavior, allowing HERAKLES to confirm the design margins before flight. •Nose dynamical test revealed a non-linear behavior of its TPS.•FE models have been updated to match actual behavior of nose TPS.•Thermal tests of nose TPS revealed that thermo-mechanical FE models are representatives.•With those updated models, nose margins have been assessed and are positive.•These results led to the qualification of the IXV nose TPS.