改性C/SiC-ZrC复合材料热化学烧蚀仿真研究

Simulation of thermochemical ablation of modified C/SiC-ZrC composites

基于C/SiC复合材料基体改性制备超高温陶瓷基复合材料,是满足高超音速飞行器对热防护系统材料所需更高要求的有效途径。基于热化学平衡理论构建了C/SiC-ZrC复合材料的烧蚀模型,选取文献中相同制备方式下两组不同体积分数的C/SiC-ZrC复合材料,并利用MATLAB计算出两组材料的无量纲烧蚀率,然后在COMSOL多物理场分析软件中建立数值仿真,将仿真结果与文献实验结果进行对比,误差分别为8.7%~16.9%和1.05%~11.07%,验证了模型的有效性。

Ultra-high temperature ceramic matrix composites prepared based on matrix modification of C/SiC composites are an effective way to meet the higher requirements for thermal protection system materials required by hypersonic aircrafts.The ablation model of C/SiC-ZrC composites is constructed based on thermochemical equilibrium theory,and two sets of C/SiC-ZrC composites with different volume fractions under the same preparation method in the literature were selected,and the dimensionless ablation rates of the two sets of materials were calculated using MATLAB,and then numerical simulations were established in COMSOL multiphysics field analysis software,and the simulation results were compared with the experimental results in the literature,and the errors were 8.7%~16.9%and 1.05%~11.07%,respectively,which verifies the validity of the model.