以硅橡胶为基体,添加无机填料制备的耐热涂层在耐热防腐方面有重要应用前景。采用自制改性硅橡胶作基体,添加不同配比的高岭土、二氧化硅和氧化铝,制备了复合涂层。采用扫描电子显微镜(scanning electron microscopy,SEM)观察了硅橡胶...以硅橡胶为基体,添加无机填料制备的耐热涂层在耐热防腐方面有重要应用前景。采用自制改性硅橡胶作基体,添加不同配比的高岭土、二氧化硅和氧化铝,制备了复合涂层。采用扫描电子显微镜(scanning electron microscopy,SEM)观察了硅橡胶基体中无机填料的分散状况,采用热重分析仪(thermogravimetric analyzer,TGA)对复合涂层的热解温度和失重率进行了分析。结果表明:在复合体系中,无机填料与基体的相容性较好,分散均匀;与基体材料相比,无机填料的添加可有效提高复合材料的耐热性。填料质量分数为20%的复合涂层,其在800℃时质量残留率比自制改性硅橡胶的基体提高了10%以上。展开更多
In a high heat flux ablative environment,the surface temperature of aircraft rises rapidly,leading to traditional high thermal conductivity materials being ineffective at protecting internal metal components.In this s...In a high heat flux ablative environment,the surface temperature of aircraft rises rapidly,leading to traditional high thermal conductivity materials being ineffective at protecting internal metal components.In this study,continuous carbon fiber reinforced Li_(2)O-Al_(2)O_(3)-SiO_(2)(C_(f)/LAS)glass ceramic composites doped with SiC particles(SiC_(p))were prepared by slurry immersion winding and hot pressing sintering.Effect of matrix crystallinity on ablative properties of the composites under ultra-high heat flux was investigated.By utilizing heat absorption and low thermal conductivity characteristics associated with SiO_(2)gasification within composite materials,both surface and internal temperatures of these materials are effectively reduced,thereby ensuring the safe operation of aircraft and electronic devices.Results indicate that the average linear ablation rate of composites doped with 10%(in mass)of SiC_(p)significantly decreases at a heat flux of 20 MW/m^(2).Transmission electron microscope observation reveals that the doped glass matrix exhibits increased crystallinity,reduced internal stress,and minimized lattice distortion,thereby enhancing the composites’high-temperature performance.However,excessive SiC_(p)doping leads to reduced crystallinity and deteriorated ablation performance.Ultimately,the average linear ablation rate of C_(f)/LAS composites with 10%(in mass)SiC_(p)at 20 MW/m^(2)heat flux is comparable to that of commercial carbon/carbon composites,accompanied by providing lower thermal conductivity and higher bending strength.This novel high-performance C_(f)/LAS composite is cost-effective,short-cycled,and suitable for mass production,offering promising potential for widespread application in ablation-resistant components of hypersonic vehicles.展开更多
文摘以硅橡胶为基体,添加无机填料制备的耐热涂层在耐热防腐方面有重要应用前景。采用自制改性硅橡胶作基体,添加不同配比的高岭土、二氧化硅和氧化铝,制备了复合涂层。采用扫描电子显微镜(scanning electron microscopy,SEM)观察了硅橡胶基体中无机填料的分散状况,采用热重分析仪(thermogravimetric analyzer,TGA)对复合涂层的热解温度和失重率进行了分析。结果表明:在复合体系中,无机填料与基体的相容性较好,分散均匀;与基体材料相比,无机填料的添加可有效提高复合材料的耐热性。填料质量分数为20%的复合涂层,其在800℃时质量残留率比自制改性硅橡胶的基体提高了10%以上。
基金National Natural Science Foundation of China(U23A6014,52103357)。
文摘In a high heat flux ablative environment,the surface temperature of aircraft rises rapidly,leading to traditional high thermal conductivity materials being ineffective at protecting internal metal components.In this study,continuous carbon fiber reinforced Li_(2)O-Al_(2)O_(3)-SiO_(2)(C_(f)/LAS)glass ceramic composites doped with SiC particles(SiC_(p))were prepared by slurry immersion winding and hot pressing sintering.Effect of matrix crystallinity on ablative properties of the composites under ultra-high heat flux was investigated.By utilizing heat absorption and low thermal conductivity characteristics associated with SiO_(2)gasification within composite materials,both surface and internal temperatures of these materials are effectively reduced,thereby ensuring the safe operation of aircraft and electronic devices.Results indicate that the average linear ablation rate of composites doped with 10%(in mass)of SiC_(p)significantly decreases at a heat flux of 20 MW/m^(2).Transmission electron microscope observation reveals that the doped glass matrix exhibits increased crystallinity,reduced internal stress,and minimized lattice distortion,thereby enhancing the composites’high-temperature performance.However,excessive SiC_(p)doping leads to reduced crystallinity and deteriorated ablation performance.Ultimately,the average linear ablation rate of C_(f)/LAS composites with 10%(in mass)SiC_(p)at 20 MW/m^(2)heat flux is comparable to that of commercial carbon/carbon composites,accompanied by providing lower thermal conductivity and higher bending strength.This novel high-performance C_(f)/LAS composite is cost-effective,short-cycled,and suitable for mass production,offering promising potential for widespread application in ablation-resistant components of hypersonic vehicles.
