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本文对在气动加热和剪切力作用下的高硅氧增强塑料的烧蚀问题进行了理论探讨,分析了这种材料在烧蚀中所产生的物理,化学过程特性。以高超音速再入大气层的头锥体,其烧蚀表面具有熔化、气化、塑料分解和表面化学反应等过程,二氧化硅形成流动的液态层,树脂的气体产物通过多孔的碳化层和液态层进入附面层中。质量引射到附面层的效应降低了气动热交换和剪切力。 烧蚀理论由电弧加热器的层流驻点实验所证实,驻点烧蚀速度和表面温度的理论值与实验值相差在15％以内。
In this paper, the problem of ablation of silicone-reinforced plastic under aerodynamic heating and shearing force is theoretically discussed, and the physical and chemical process characteristics of the material during ablation are analyzed. The hypersonic reentry head cone has an ablated surface with processes such as melting, gasification, plastic decomposition and surface chemical reactions. Silica forms a flowing liquid layer through which the gas product of the resin passes through the porous carbonized layer and the liquid phase Layer into the surface layer. The effect of mass projectile on the coating reduces the aerodynamic heat exchange and shear forces. The ablation theory is verified by the laminar flow stagnation experiment of the arc heater. The theoretical values of the ablation speed and the surface temperature of the stagnation point are within 15% of the experimental ones.