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Thermomechanical behaviour of a damaged thermal protection system: experimental correlation and influence of hypersonic flow

Published online by Cambridge University Press:  27 January 2016

W. H. Ng ,
P. P. Friedmann ,
A. M. Waas  and
J. J. McNamara
W. H. Ng
Affiliation:
Department of Aerospace Engineering, University of Michigan, Ann Arbor, Michigan, USA
P. P. Friedmann
Affiliation:
Department of Aerospace Engineering, University of Michigan, Ann Arbor, Michigan, USA
A. M. Waas
Affiliation:
Department of Aerospace Engineering, University of Michigan, Ann Arbor, Michigan, USA
J. J. McNamara
Affiliation:
Department of Mechanical & Aerospace Engineering, Ohio State University, Columbus, Ohio, USA
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Abstract

This paper describes a combined experimental and numerical study on damaged and undamaged space shuttle tile thermal protection system (TPS). The principal objective of the study is to determine its thermomechanical behaviour and assess the structural integrity of the TPS. The TPS tile specimens are subjected to a temperature profile corresponding to the thermal loads of the Access to Space reference vehicle. Experiments are conducted in a vacuum chamber that allows re-entry static pressure to be simulated. Temperatures on the top and bottom surfaces of the specimen, and the strains in the underlying structure are recorded. The experimental results are used to guide the development of a refined finite element model, which is subsequently used to simulate the interactions between the high speed external flow past the cavity that represents damage. Using this model, the relative effects of damage on the thermal protection capability and the induced thermal stresses are determined by comparing the response of the damaged configurations with the undamaged configuration. Damage increases the thermal loads and significantly reduces the radiation heat loss from the surface of the tile, resulting in elevated temperatures. Results indicate that damage can raise the maximum temperature in the tile to values that exceed its melting point.

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1164 , February 2011 , pp. 69 - 82
Copyright
Copyright © Royal Aeronautical Society 2011

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