Influence of Mineral Fillers And Hollow SiO2 Microsphere on Thermal Property Of Epoxy resin

The Today, among with the development and progress of thermal power plants, space navigation and aerospace technology, thermal protection materials must meet higher temperature, more stringent requirements in recent years. For example, when spacecraft fly with very high speed or re-enter the atmosphere with supersonic speed, the surface temperature of spacecraft could reach as high as 1000 to 3000 ◦C. To protect these vehicles from the heat generated and noise attenuation for surfaces during flight time, various arrangements utilizing ablative materials have been heretofore proposed. Multilayer thermal protection composite based on mineral fillers applied to the spacecraft components would be more effective and economically feasible among other thermal protection methods. In the present research, insulation layer thermal protection composite formulated and applied to the Aluminum substrates components was characterized by, thermo gravimetrical analysis (TGA), differential scanning calorimetry (DSC) and Thermal diffusivity (XFA) analysis. For evaluation of ablation behavior of this layer, oxyacetylene flame test was performed and thermal diffusivity measurements were used to investigate the thermal insulation performance of polymer composite According to These tests, it was found that the best results of ablation behavior were obtained by coatings containing about 80 wt % filler. The results of thermal diffusivity measurements showed that the thermal diffusivity at room temperature of the composite Epoxy / mineral fillers contains 80 wt% filler was 0.0034 cm2 /s According to high amount of mineral fillers, results revealed that thermal diffusivity values for polymer composites was low and the polymer composite are placed in thermal insulation coating category.