目的 通过双层涂层材料结构，获得综合性能优良的适用于火箭发射台表面的热防护涂层材料。方法 以环氧树脂为底层基体材料，加入不同的助剂，再以有机胶为表层基体材料，加入填料和助剂，制备出一种用于火箭发射台的热防护涂层材料。通过附着力和弹性模量对热防护涂层的力学性能进行研究，通过小型发动机烧蚀试验对热防护涂层的热学性能进行研究。最后，通过将热防护涂层涂覆在火箭发射台上，考察研制的热防护涂层经火箭发射后的实际使用效果。结果 经测试，热防护涂层材料的附着力达到5.35 MPa，弹性模量为446.72 MPa。当涂层厚度为15 mm时，金属背面温度最高不超过40 ℃。热防护涂层材料线烧蚀率的平均值为0.515 mm/s。将所研制的热防护涂层材料在国内某火箭发射台上进行使用，使用结果表明，该热防护涂层材料能够承受火箭发射时尾焰的燃气流冲刷，涂层的脱落面积不超过总涂覆面积的10%。结论 所研制的热防护涂层材料可以在火箭发射台上使用，并且使用效果良好，起到了保护火箭发射台的作用。

The work aims to prepare a heat-resistant coating of excellent overall performance for rocket launching pad by bilayer coating materials. A kind of heat-resistant coating material for rocket launching pad use was prepared by adding several kinds of adjuvants with epoxy resin as base substrate material, and then adding fillers and adjuvants with organic gel as the surface base material. Mechanical properties of the heat-resistant coating were studied based on adhesive force and elastic modulus. Thermal performance of the heat-resistant coating was studied by performing small engine ablation experiment. Finally, practical using effect of the heat-resistant coating after rocket launching was investigated by depositing the heat-resistant coating on a rocket launching pad. The results showed that adhesive force was up to 5.35 MPa and elastic modulus 446.72 MPa. Maximum temperature on the reverse side was no more than 40 ℃ when the heat-resistant coating material was 15 mm thick. Average linear ablation rate of the heat-resistant coating was 0.515 mm/s. The results of using the developed heat-resistant coating material on a rocket launching pad showed that the heat-resistant coating material could bear the scour by combustion-gas stream when a rocket was launched, the falling-off area of the coating was less than 10% of the whole coated area. The developed heat-resistant coating material is suitable for rocket launching pad with a favourable using effect and plays an important role in the protecting rocket launching pad.