TY - GEN
T1 - Thermal response of a spatially graded metal-ceramic structural panel to non-uniform heating in hypersonic flow
AU - Deierling, Phillip E.
AU - Zhupanska, Olesya I.
AU - Pasiliao, Crystal L.
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2015
Y1 - 2015
N2 - In this paper, the thermal response of metal-ceramic Ti-6Al-4V/TiB2 functionally graded composite structural panels is studied and compared against a Ti-6Al-4V structural panel with an Exelis Acusil® II syntactic foam thermal protection system. Structural panels are subjected to thermal and mechanical loads resulting from hypersonic flight over a representative trajectory. Mechanical loads are the by-product of aggressive maneuvering at high air speeds and angles of attack. Thermal loads as a result of aerodynamic heating are applied to the material systems as laminar, turbulent and transitional heat flux on the outer surface. Transitional heat fluxes are used to evaluate the effectiveness of Ti-6Al-4V/TiB2 graded in two principal directions, e.g., through-thickness and surface parallel to flow. The computational results indicate that when subjected to uniform surface heat flux, the graded material system can eliminate through-thickness temperature gradients that are otherwise present in traditional thermal protection systems. Furthermore, graded material systems can also eliminate through-thickness temperature gradients and significantly reduce in-plane surface temperature gradients when subjected to non-uniform surface aerodynamic heating.
AB - In this paper, the thermal response of metal-ceramic Ti-6Al-4V/TiB2 functionally graded composite structural panels is studied and compared against a Ti-6Al-4V structural panel with an Exelis Acusil® II syntactic foam thermal protection system. Structural panels are subjected to thermal and mechanical loads resulting from hypersonic flight over a representative trajectory. Mechanical loads are the by-product of aggressive maneuvering at high air speeds and angles of attack. Thermal loads as a result of aerodynamic heating are applied to the material systems as laminar, turbulent and transitional heat flux on the outer surface. Transitional heat fluxes are used to evaluate the effectiveness of Ti-6Al-4V/TiB2 graded in two principal directions, e.g., through-thickness and surface parallel to flow. The computational results indicate that when subjected to uniform surface heat flux, the graded material system can eliminate through-thickness temperature gradients that are otherwise present in traditional thermal protection systems. Furthermore, graded material systems can also eliminate through-thickness temperature gradients and significantly reduce in-plane surface temperature gradients when subjected to non-uniform surface aerodynamic heating.
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U2 - 10.2514/6.2016-0490
DO - 10.2514/6.2016-0490
M3 - Conference contribution
AN - SCOPUS:85088750078
SN - 9781624103926
T3 - 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
BT - 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -