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International Journal of Applied Research in Mechanical Engineering

Abstract

Ablative materials are used in heat shields of spacecrafts re-entering the atmosphere to protect them from high aerodynamic heating. A computer program has been developed to predict the pyrolysis and thermal response in ablative materials. The computational results are verified by performing experiments conducted at the test facility in Vikram Sarabhai Space Centre. The properties and thickness of char formed are crucial to determine heat ingress. Using an inverse problem, the thermo-physical properties of char formed from the ablative material, which have not been determined earlier, are estimated. Thickness of char formed is also predicted using the program.

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