IXV CMC Thermal Protection System Post-flight Preliminary Analysis

Paper number

IAC-16,D2,6,3,x32322

Coauthor

Mr. Thierry Pichon, Airbus Safran Launchers, France

Coauthor

Mr. Renaud Barreteau, Herakles, Safran, France

Coauthor

Mr. François Buffenoir, Herakles, Safran, France

Year

2016

Abstract

The Intermediate experimental Vehicle (IXV) atmospheric re-entry demonstrator, developed within the FLPP (Future Launcher Preparatory Program) and funded by ESA, 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. A key technology that has been demonstrated in real conditions through the flight of this ambitious vehicle is the Thermal Protection System (TPS) of the Vehicle. Within this program, HERAKLES, Safran Group, has been 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 non ablative outer mould line (OML) for enhanced aerodynamic control.

After the successful flight of February the 11th, 2015, the vehicle has been recovered and the excellent behaviour of the TPS to the thermal loads of re-entry has been assessed. Recorded data have also been retrieved, which allows performing a preliminary analysis of this flight.

This paper describes the first findings and conclusions made on this historical IXV flight based on the thermocouples and displacement sensors measurements.

Abstract document

IAC-16,D2,6,3,x32322.brief.pdf

Manuscript document

IAC-16,D2,6,3,x32322.pdf (🔒 authorized access only).

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