Numerical Analysis of Heating Shock on Nose of Aerospace Projectiles

In this article thermal stress of graphite nose of aerospace projectiles is investigated. The governing equations، boundary conditions، rate of surface recession، ablation model of graphite، and also moving mesh generation are described. In order to calculate thermal stress، at first unsteady heat transfer equation in an unstructured moving mesh is solved using finite volume method for reentry period، then the results of the thermal analysis are transferred to a structure analysis software. Aerodynamic pressure is applied as a variable with time and position and thermal stress is calculated for the reentry flight. There is a good agreement between the current results and those of the other researchers.