Browsing by Author "A, Pavan"

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.