9th Int. Conference on Recent Advances in Space Tech. 2019, İstanbul, Turkey, 11 - 14 June 2019
Development of a solver in
order to estimate the material response of charring ablative materials which
are utilized as thermal protection systems in space vehicles is presented. First,
the governing equations for modeling transient thermal response of charring
ablative materials and the adopted numerical solution schemes are reviewed. The
governing equations include energy balance, pyrolysis kinetics and mass
balance. Solution of the governing equations in conjunction with appropriate
boundary conditions gives the thermal response of the ablative material.
Equations are discretized using vertex-centered finite volume method and solved
in a loosely coupled sequential way. Verification studies showed that the results
of the developed code are in good agreement with those in the references.