| Summary: | 碩士 === 國防大學理工學院 === 應用化學碩士班 === 97 === Thermal protection systems in space vehicles, which keep damaging heat away from spacecraft surface, are essential for the successful launch and operation of all spacecrafts. Different types of thermal protection systems have been developed to meet this necessity. Among them, ablative coating is a widely used method to protect the external surface of spacecraft from thermal damage by consumption of heat via various thermophysical and Chemical mechanisms. The ablation properties of a composite.based ablative coating depend strongly on the matrix used. Silicone resins are well known of their excellent thermal stability, aging resistance and chemical resistance.Therefore, silicone resin becomes one of the preferred matrix materials in making ablative coating. In this study, the formulation of the silicone ablative material will be developed based on the studies of ablation resistance, viscosity,curing rate at room temperature and char yield in the residue.
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