The effect of the application of a powder additive of a phase change material on the ablative properties of a hybrid composite

摘要

The necessity to ensure thermal protection for sensitive elements of the aviation technology, being exposed to a high temperature of a thermal stream, enforces the emergence of new materials with high thermo-protective properties. The investigations focused on laminates consisting of six layers of carbon and aramid fabrics, which were laid down in an epoxy resin matrix base L285 MGS and H500 MGS hardener. The ablative thermoprotective properties were modified with powder additives (in the rear part of the composite such as PCM, MMT, SiC, Al2O3). The samples were exposed to a mixture of hot gases at a temperature of over 1000 degrees C for a period of approximately 180 s. The most important parameter determined on the basis of experimental research was the temperature of the rear surface of the sample. The average loss of mass and the mass ablation rate of the tested material were also analysed. Based on the analysis of the temperature rise on the back of the sample surface, it is possible to observe a clear downward tendency for a hybrid composite modified with powder by 60 degrees C, as opposed to samples without the addition of powder.