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The Journal of the Astronautical Sciences

, Volume 56, Issue 4, pp 593–619 | Cite as

Transient aero-thermal mapping of passive Thermal Protection system for nose-cap of Reusable Hypersonic Vehicle

  • Shripad P. Mahulikar
  • Shashank Khurana
  • Ritesh Dungarwal
  • Sushil G. Shevakari
  • Jayakumar Subramanian
  • Amit V. Gujarathi
Article

Abstract

The temperature field history of passive Thermal Protection System (TPS) material at the nose-cap (forward stagnation region) of a Reusable Hypersonic Vehicle (RHV) is generated. The 3-D unsteady heat transfer model couples conduction in the solid with external convection and radiation that are modeled as time-varying boundary conditions on the surface. Results are presented for the following two cases: (1) nose-cap comprised of ablative TPS material only (SIRCA/PICA), and (2) nose-cap comprised of a combination of ablative TPS material with moderate thermal conductivity and insulative TPS material. Comparison of the temperature fields of SIRCA and PICA [Case (1)] indicates lowering of the peak stagnation region temperatures for PICA, due to its higher thermal conductivity. Also, the use of PICA and insulative TPS [Case (2)] for the nose-cap has higher potential for weight reduction than the use of ablative TPS alone.

Keywords

Radiative Heat Transfer Stagnation Region Heat Flow Rate Heat Spreading Thermal Protection System 
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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Copyright information

© American Astronautical Society, Inc. 2008

Authors and Affiliations

  • Shripad P. Mahulikar
    • 1
  • Shashank Khurana
    • 1
  • Ritesh Dungarwal
    • 1
  • Sushil G. Shevakari
    • 1
  • Jayakumar Subramanian
    • 1
  • Amit V. Gujarathi
    • 1
  1. 1.Department of Aerospace EngineeringIndian Institute of Technology BombayIndia

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