Homidzoda Shahobuddin Hoshim,  Eshov Bakhtier Badalovich

Annotation:

This study investigates the effect of aerodynamic heating on the nose cone of spacecraft manufactured from carbon– carbon composites with a silicon carbide matrix (C/C+SiC). Using numerical simulation methods and computational analysis performed in the Abaqus/Standard and MATLAB software environments, heat transfer processes, the influence of temperature gradients, and their temporal evolution at various points of the nose cone were examined. The obtained results indicate that during atmospheric flight, the frontal region of the nose cone is subjected to maximum thermal loads, after which the heat flux gradually propagates into the inner layers of the structure. The results obtained using MATLAB are in good agreement with the temperature distribution predicted by Abaqus simulations, confirming the validity and accuracy of the developed numerical model. The conducted study demonstrates that the C/C+SiC composite exhibits high thermal resistance and can be effectively applied as a material for Thermal Protection Systems (TPS) of spacecraft nose structures.

Keywords: C/C+SiC, nose cone, heat transfer, Abaqus, MATLAB, Thermal Protection System (TPS), aerodynamics.