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Prediction of Heatshield Material Performance in an Arcjet

  • S. McDowell
Conference paper

Introduction

During hypersonic re-entry into the Earth’s atmosphere, a vehicle is likely to experience a severe aero-thermal environment with regards to temperature, pressure and shear stress. The extreme temperatures behind the bow shock may cause the air to dissociate and undergo ionisation. Thermal energy is transferred to the vehicle surface from this hot gas in the form of heat. To manage the vehicles heatshield thermal loading, one method is to use a charring, ablating heatshield. This choice of thermal protection system typically uses a composite material comprising a fibre matrix impregnated with a resin. This type of high performance charring ablator is comprised of carbon fibres and a phenolic resin. Due to the extreme thermal environment seen during re-entry, this carbon phenolic material may ablate at the surface, char in depth and outgas. These three mechanisms reduce the transfer of thermal energy from the flow into the surface by mass removal, internal chemical decomposition and transpiration cooling and thus reduce the thermal energy through to the load bearing structure and interior of the vehicle.

Keywords

Rarefaction Wave Wall Condition Sweet Spot Thermal Protection System Transpiration Cool 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

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    Keenan, J.A.: Journal AIAA, 94-2083Google Scholar
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    Carnicom, M.L.: Description of Three Major Thermochemistry Decks Used with the CMA Programs, vol. 1Google Scholar
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    Capsule Aerothermodynamics, AGARD report 808Google Scholar
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    Boyd, D.: AIAA 2010-1175, 1175 (2010)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • S. McDowell
    • 1
  1. 1.Defence Science and Technology LaboratoryFarehamUK

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