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Numerical Model Set-Up and Virtual Testing of a CMC Flap for Re-Entry Vehicle

[+] Author Affiliations
Roberto Scigliano, Marika Belardo, Mario De Stefano Fumo

Italian Aerospace Research Centre (CIRA), Capua, Italy

Salvatore Celentano

University of Naples “Federico II”, Naples, Italy

Paper No. IMECE2017-70390, pp. V001T03A012; 8 pages
  • ASME 2017 International Mechanical Engineering Congress and Exposition
  • Volume 1: Advances in Aerospace Technology
  • Tampa, Florida, USA, November 3–9, 2017
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-5834-9
  • Copyright © 2017 by ASME


CIRA has recently set up a research and development project with Italian industrial partners, with the aim of develop hot structures based on ceramic matrix composites technology (C-C/SiC), code named SHS-CMC project. The project focuses on the application of the technology on the control surface of a re-entry vehicle, with the final objective of reaching TRL 5/6, to be spent in more challenging projects such as ESA SPACE RIDER. Thanks to CIRA heritage on ESA EXPERT flap plasma wind tunnel testing, the demonstrator of SHS-CMC project technology will be based on the EXPERT flap geometry, to be tested for final TRL assessment, in more demanding environment such as those of ESA-SPACE RIDER atmospheric re-entry phase.

Besides the manufacturing process development it is of paramount importance to have robust and reliable thermal-mechanical models for design, in which both the material anisotropy and the most representative heat transfer phenomena are modelled and validated through test.

In the present work the thermal model of the technological demonstrator has been set up. The validation of the model has been obtained trough numerical experimental correlation of PWT test on a similar test article developed in the frame of ESA EXPERT project. The virtual test shows good agreement with experiments in terms of temperature maps. This is the first step to be accomplished before the final qualification test and numerical-experimental validation of the SHS-CMC technology demonstrator, and subsequent TRL assessment.

Copyright © 2017 by ASME



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