【摘要】 高性能固体火箭发动机 ( SRM)对喉衬材料的烧蚀率提出了更高的要求 ,传统的炭 /炭 ( C/C)材料有待于进一步发展。讨论了含有难熔金属碳化物 ( Zr C、Ta C)的多元基体 C/C复合材料及其耐烧蚀性能 ,通过微观结构分析 ,探讨该种材料抗烧蚀性能提高的机理 ,展示了这种材料作为高温烧蚀材料的良好前景更多还原

【Abstract】 Throat material of advanced solid rocket motor (ASRM) has to withstand 3 700 K. After five years of continuous research, we produced in the laboratory a new kind of multi matrix C/C that looks promising to satisfy the requirements on anti ablation property. We used resin impregnating process to make the carbon matrix of our laboratory produced multi matrix C/C contain difficult to fuse metal carbide such as ZrC or TaC. We employed the well known arc heater stagnation ablating test to measure the anti ablation property. We obtained optimum anti ablation improvement with 5% ZrC in the matrix when the pressure was 2.0 or 4.5 MPa. After the analysis of the microstructure and the ablated morphology, we deem that the improvement in anti ablation property comes from that the refractory ZrC restrains oxidation in the following three respects: (1) the ZrC containing matrix can withstand the high temperature and the abrasion of SRM (solid rocket motor) firing gas; (2) ZrC can react with oxidizing gas; (3) the oxidized ZrC forms a melted oxide film to reduce the gas diffusing.更多还原