مدلسازي فرايند تخريب كامپوزيتهاي فداشونده

If the bodies, such as the head and nose of missile, nozzle or combustion chamber of the rocket, which are exposed to sever heat, are not protected against it, then they cannot perform for the purpose they are designed. One of the recommended methods to protect these systems against heat is the usage of the ablativ insulators. In this work, the thermal behavior of ablative composites of silicon rubber matrix and glass reinforced fibers was studied and modelled. For this purpose, the mass and energy equation in ablation conditions were simultaneously solved numerically using finite difference method and the various related parameters of the insulator were determined as a function of temperature and time. This modelling will allow to predict the proper thickness of the ablative composite in the actual service conditions. This method can also be used in designing of the other ablative composites.