Thermal Protection Systems (TPS) are used to protect a rocket payload until it arrives intact at its destination. Reliable tools for their design must be defined. The degradation process generated by aerodynamic heating in polymeric ablators can be calculated using lumped models at low computational cost. This work presents a simplified but valid model for the ablation of polymeric composites using lumped source terms to simulate physical phenomena that occur during ablation. Reference works were considered for comparison. The model was compared to experimental results of ablative materials used by the Brazilian Space Program. Mass loss rate curves were generated and presented good agreement to the results. Evolution of ablation and pyrolysis was also evaluated through the model's results.
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