Analysis Of Combined Radiation-Conductive Heat Transfer During Destruction Of Porous Carbon-Ceramic Matrix Composite Material Of Thermal Protection

Ceramic matrix composites (CMC) are currently considered as promising for application in the thermal protection system of reentry modules of new spacecraft. In the article, physical and mathematical models for the analysis of destruction and combined radiation-conductive heat transfer in porous CMC consisting of carbon fibers coated with silicon carbide are proposed. The models consider all principal physical and chemical processes occurring in the material during its heating and thermochemical destruction. To solve the problem, an original finite-element DMA software was developed. Modeling has shown that at temperatures above 800 degrees C the influence of radiation heat exchange on the process of heating and destruction of CMC becomes significant.