Thermal protection is one of the key problems to be solved in the design of the hypersonic vehicles.In the early and middle stages of thermal protection material development, material formulation screening and process optimization progress can be greatly accelerated and cost can be reduced by simulation ablation test.Based on hypersonic aircraft thermal protection material requirements, a method of simulation ablation test based on small plasma multiphase flow is presented.A simulation ablation test system with precise control of each parameter was developed based on automation technology.The plasma jet produced by the experimental system is high enthalpy, high temperature and high heat flux.Moreover, special solid particles can be injected into the plasma jet to simula-tion the flight environment of the hypersonic vehicles.Based on this, the ablation/erosion flow filed was character-ized by measurement and numerical simulation which can provide theoretical basis for selection and optimization of operating parameters.Finally, the ablation/erosion performance test of three-dimensional and four-directional brai-ded C/C composites was implemented and their properties were analyzed.The results indicate that this system pro-vides a reliability approach for the formula selection of the thermal protection materials and the optimal design of the thermal structure components.%在高超声速飞行器的研制过程中,热防护技术是急需攻克的关键问题之一.在热防护材料研发的初期和中期,通过模拟烧蚀试验可大大加快材料配方筛选与工艺优化进度、降低成本.针对高超声速飞行器热防护材料的使用要求,提出了基于小型等离子体多相流的模拟烧蚀试验方法;基于自动化技术开发了参数精确控制的模拟烧蚀试验系统;该系统可产生高焓、高温和高热流密度的等离子射流,射流中可注入固相粒子,模拟高超声速飞行器飞行过程中的热力环境.在此基础上,运用测量表征与数值计算相结合的手段研究了系统流场特性,为试验参数的选取与优化提供了理论依据.最后,运用系统对某型三维四向C/C复合材料进行了耐烧蚀性能测试和分析.结果表明,该试验系统可为热防护材料的配方筛选、热结构部件的优化设计和性能评价提供实用可靠的途径.
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