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Aerothermal analysis of an advanced hot structure for hypersonic flight tests

Published online by Cambridge University Press:  01 February 2011

Raffaele Savino ,
Mario De Stefano Fumo ,
Giuliano Marino  and
Mario Tului
Raffaele Savino
Affiliation:
Dept. of Space Science and Engineering (DISIS), University of Naples (Italy)
Mario De Stefano Fumo
Affiliation:
Dept. of Space Science and Engineering (DISIS), University of Naples (Italy)
Giuliano Marino
Affiliation:
Centro Italiano Ricerche Aerospaziali (CIRA), Capua (Italy)
Mario Tului
Affiliation:
Centro Sviluppo Materiali (CSM), Roma (Italy)
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Abstract

This paper deals with the aerothemodynamic analysis of an advanced concept of hot structure to be investigated in the Expert flight test programme.

Three-dimensional fluid dynamic computations have been carried out at the flight conditions of the reference Expert trajectory to evaluate the aerothermodynamic field and the thermal loads on the winglet. The physical model includes viscous effects, real gas properties, non equilibrium chemical reactions and surface catalytic effects. The unsteady aerothermal analysis has been carried out considering different thermal boundary conditions (adiabatic wall or thermal coupling with the capsule metallic skin).

The results are discussed with particular attention to the temperature distributions in the Ultra High Temperature Ceramics (UHTC) and in the structural support.

Type
Research Article
Information
MRS Online Proceedings Library (OPL) , Volume 851: Symposium NN – Materials for Space Applications , 2004 , NN11.5
Copyright
Copyright © Materials Research Society 2005

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References

REFERENCE

1. Muylaert, J., Cipollini, F., Tumino, G., Kordulla, W., Saccoccia, G., Stravinidis, C.: “Preparing for Atmospheric reentry with EXPERT's Help”, ESA Bullettin n. 114, May 2003, pp. 42–48.Google Scholar
2. Walpot, L., Ottens, H.: “FESART/EXPERT Aerodynamic and Aerothermodynamic analysis of the REV and KHEOPS configuration”, ESA ESTEC Technical Report TOS-MPA/2718/LW, 16th September 2002.Google Scholar
3. Ottens, H., Walpot, L.: “EXPERT Model 4.2, Model description and trajectory analysis”, ESA ESTEC Technical Report TOS-MPA/2749/HO, 10th April 2003.Google Scholar
4. Chamberlain, A.L., Fahrenoltz, W.G., Hilmas, G.E., Ellerby, D.T.: “Characterization of Zirconium Diboride for Thermal protection Systems”, Key Engineering Materials, 264–268, 493–496, 2004.Google Scholar
5. Monti, R., Pezzella, G., Savino, R., Paterna, D., Esposito, A.: “Aerothermodynamic study of an advanced thermal protection system”, 4th European Workshop on Hot Structures and Thermal Protection System for Space vehicles, 26–29 November 2002, Palermo, Italy.Google Scholar
6. Anderson, J.D. Jr, “Hypersonic and High Temperature Gas Dynamics”, AIAA, 2000.Google Scholar
7. Rasky, D.J., Advanced Ceramic Matrix Composites for TPS, Current Technology for Thermal Protection System, NASA Conference Publication CP-3157, 1992.Google Scholar
8. Valente, T., Tului, M., Bartuli, C.: “Deposizione al plasma di rivestimenti UHTC per protezioni termiche di velivoli da rientro”, Proceedings of Materiali per lo Spazio:Sintesi, Metodologie, Tecnologie, Bonassola(SP), 7–8 June, 2001.Google Scholar
9. Jameson, A., Schmidt, W., Turkel, E., Numerical Solution of the Euler Equations by Finite Volume Methods Using Runge-Kutta Time-Stepping Schemes, Technical Report AIAA-81–1259, AIAA 14th Fluid and Plasma Dynamics Conference, Palo Alto, California, June 1981.Google Scholar
10. Savino, R., De Stefano Fumo, M., Paterna, D., Serpico, M., Aerothermodynamic Study of UHTC-based Thermal Protection System, Accepted for publication in Aerospace Science and Technology, 2004.Google Scholar
11. Tauber, M.E.: “A review of High-Speed Convective, Heat Transfer Computation Methods”, NASA Technical Paper 2914, 1989.Google Scholar
12. TPSX Material Properties Database, NASA.Google Scholar
13. Marschall, J., Chamberlain, A., Crunkleton, D., Rogers, B.: “Catalytic Atom Recombination on ZrB2/SiC and HfB2/SiC Ultrahigh-Temperature Ceramic Composites, Journal of Spacecraft and Rockets, Vol. 41, N.4, July-August 2004, pp. 576–581.Google Scholar