超高温陶瓷(Ultra-high Temperature Ceramic,UHTC)结构材料因其在1600℃以上氧化环境中表现出优异的抗氧化/烧蚀性能、高温强度保持率和抗热冲击性能,成为航空航天、国防装备、能源动力等领域的重要候选材料。近年来,围绕UHTC结构材料...超高温陶瓷(Ultra-high Temperature Ceramic,UHTC)结构材料因其在1600℃以上氧化环境中表现出优异的抗氧化/烧蚀性能、高温强度保持率和抗热冲击性能,成为航空航天、国防装备、能源动力等领域的重要候选材料。近年来,围绕UHTC结构材料的成分调控、微观结构设计、先进制备工艺以及性能优化等方面,基础研究和技术应用均取得了显著进展。以碳化物、硼化物、氮化物等为代表的UHTC体系,正面临着温度更高、环境更复杂的服役需求。为进一步推动极端环境用UHTC结构材料的发展,本文系统综述了该领域的最新研究进展。首先,详细阐述了UHTC粉体的合成工艺;其次,深入探讨了超高温结构陶瓷的体系、致密化方法及结构调控策略;继而重点分析了超高温陶瓷基复合材料(Ultra-high Temperature Ceramic Matrix Composites,UHTCMCs)、超高温陶瓷改性碳/碳复合材料(Ultra-high Temperature Ceramics Modified Carbon/Carbon Composites,UHTCs-C/C)以及UHTC涂层的制备技术及其性能强化策略,着重探讨了其在抗氧化/烧蚀领域的最新突破。同时,本文还指出了极端环境下UHTC结构材料在长期稳定性和可靠性方面面临的主要技术挑战,并对其未来发展趋势进行了前瞻性展望。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
文摘超高温陶瓷(Ultra-high Temperature Ceramic,UHTC)结构材料因其在1600℃以上氧化环境中表现出优异的抗氧化/烧蚀性能、高温强度保持率和抗热冲击性能,成为航空航天、国防装备、能源动力等领域的重要候选材料。近年来,围绕UHTC结构材料的成分调控、微观结构设计、先进制备工艺以及性能优化等方面,基础研究和技术应用均取得了显著进展。以碳化物、硼化物、氮化物等为代表的UHTC体系,正面临着温度更高、环境更复杂的服役需求。为进一步推动极端环境用UHTC结构材料的发展,本文系统综述了该领域的最新研究进展。首先,详细阐述了UHTC粉体的合成工艺;其次,深入探讨了超高温结构陶瓷的体系、致密化方法及结构调控策略;继而重点分析了超高温陶瓷基复合材料(Ultra-high Temperature Ceramic Matrix Composites,UHTCMCs)、超高温陶瓷改性碳/碳复合材料(Ultra-high Temperature Ceramics Modified Carbon/Carbon Composites,UHTCs-C/C)以及UHTC涂层的制备技术及其性能强化策略,着重探讨了其在抗氧化/烧蚀领域的最新突破。同时,本文还指出了极端环境下UHTC结构材料在长期稳定性和可靠性方面面临的主要技术挑战,并对其未来发展趋势进行了前瞻性展望。
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.
