Numerical Analysis of Erosion in carbon-Phenolic Solid Rocket Nozzle

The main objective of this study is to develop a one-dimensional model for the analysis of the
charring ablative material over the surface of a solid rocket nozzle. These materials are also
used in spacecraft thermal protection systems. Despite the enormous amount of research in this
area, the design methodology for ablative heat shield sand and the models on which these
designs are based, still require considerable improvement. A very limited number of materials
have been used thus, the development and testing of new materials are required. The mass
fraction of the TPS can reach very high values, so investigations aiming to optimize the
heatshield mass are necessary. Following, A mathematical model was developed to predict the
one-dimensional thermal response of the ablative material, with steady-state ablation
approximation to obtain the surface temperature. Simulations of carbon–phenolic solid rocket
motor nozzle have been carried out to validate the model and to investigate the role of the most
uncertain parameters. The designing of model used in this analysis is done through the CAECAD; and CFD simulation carried out in MP-GUI with numerical program compiling with
MP-Solver. The model was validated with the experimental results through a survey of
literature related to thermal shields.