| Citation: | SHI Shengbo, ZHANG Yuntian, HU Li, et al. Ablation mechanism and coupling pyrolysis/conduction model of a silicone rubber matrix thermal protection coating[J]. Journal of Aerospace Power, 2023, 38（9）：2049-2061 doi: 10.13224/j.cnki.jasp.20220897
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Thermogravimetric analysis was carried out by using synchronous thermal analyzer. The temperature range, activation energy and reaction mechanism function for the thermal decomposition reaction of the coating were determined. Thermal exposure experimental tests were conducted using a quartz lamp radiant heating platform. The mechanism of microstructure evolution and energy dissipation of thermal protection coating at high temperatures were revealed. Based on the principle of energy conservation, a coupling model for predicting the pyrolysis and thermal conduction of the thermal protection coating was established. The energy conversion relationships, which were caused by pyrolysis reaction, thermal diffusion of decomposition gas and mass ejection effect, were considered. The mass loss and temperature response of the silicone rubber matrix thermal protection coating under a typical thermal environment were calculated. After thermal exposure, the specimen surface remained basically flat, and the temperature at back surface was 151.4 ℃ while the mass loss rate was 0.28 g/s. The deviation between the calculated mass loss rate and its measured value was only 7.1%. This can meet the requirements of thermal protection design in engineering applications. The results showed that the silicone rubber matrix thermal protection coating has good ablation resistance and thermal insulation properties in medium heat flux environment, so it has excellent potential for the large area thermal protection application of aerospace vehicles.
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