THERMOCHEMICAL ABLATION OF CARBON/CARBON COMPOSITES WITH NON-LINEAR THERMAL CONDUCTIVITY

Abstract

Carbon/carbon composites have been typically used to protect a rocket nozzle from high temperature oxidizing gas. Based on the Fourier's law of heat conduction and the oxidizing ablation mechanism, the ablation model with non-linear thermal conductivity for a rocket nozzle is established in order to simulate the one-dimensional thermochemical ablation rate on the surface and the temperature distributions by using a written computer code. As the presented results indicate, the thermochemical ablation rate of a solid rocket nozzle calculated by using actual thermal conductivity, which is a function of temperature, is higher than that by a constant thermal conductivity, so the effect of thermal conductivity on the ablation rate of a solid rocket nozzle made of carbon/carbon composites cannot be neglected.

Keywords

Dates

  • Submission Date2014-02-02
  • Revision Date2014-04-12
  • Acceptance Date2014-07-12
  • Online Date2015-01-04

DOI Reference

10.2298/TSCI1405625L

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