cmc technology for windward and nose of the ixv vehicle : towards full-scale manufacturing and qualification.

Paper number

IAC-13,D2,6,3,x18787

Author

Mr. Thierry Pichon, Herakles, Safran, France

Year

2013

Abstract

The launch of the Intermediate eXperimental Vehicle will represent a major achievement, with the first European in-flight demonstration of some of the most advanced technologies in the field of re-entry. In particular, this vehicle will rely on a large array of C-SiC based thermal protection systems, in development for many years, but still to be completely validated through an actual spacecraft application. 
 

Herakles, Safran, has been entrusted since 2008 with the development and qualification of two of the most critical TPS subsystems of the vehicle : the nose and the panels covering the major part of the windward area, two of the most heated areas during re-entry. After a successful CDR outcome in 2011, these subsystems are currently well into the middle of the qualification and flight model manufacturing phase.

The technology developed for these applications combines a high-temperature resistant C-SiC outer shell, mechanically fastened to the structure of the vehicle, and internal lightweight insulation layers. These systems have to comply with a set of very strict requirements related to the harsh environment of atmospheric re-entry, combined aerodynamic shape control and mass objectives. Consequently, a large number of test campaigns have been performed throughout the detailed design phase, addressing the different components of the subsystems, with particular focus on C-SiC parts and on integrated subsystem performance.


For a full verification of the level of performance of the TPS, a series of qualification tests will take place in 2013 on a full-size nose and on panels representing the most critical areas of the Windward. These tests will comprise dynamic loads, representing the Vega launcher environment and the parachute extraction shocks, and thermal and mechanical tests that will allow to verify the heat transfer within the components of the TPS, and the mechanical sizing margins under the re-entry conditions.

The paper provides a comprehensive status of the activity performed on the IXV Nose and Windward TPS subsystems, giving an insight of the manufacturing of the components of the Qualification Model, including initial subscale and prototype CMC parts. It will also present the preparation of the qualification tests, that comprise both dynamic tests and thermal and mechanical tests on a series of full-scale parts representing the nose of the vehicle and the most critical areas of the windward TPS.

Abstract document

IAC-13,D2,6,3,x18787.brief.pdf

Manuscript document

IAC-13,D2,6,3,x18787.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.