The ablation mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied.
本文研究了碳-酚醛材料在固体火箭发动机喷管中的烧蚀机理及性能。
The ablation experiments of silica phenolic resin material eroded by highly concentrated particles were carried out by using the high acceleration ablation simulation test motor.
利用高过载模拟烧蚀实验发动机，开展了高浓度颗粒流冲刷条件下高硅氧酚醛材料烧蚀机理的实验研究。
The ablation mechanisms of the material are volatilization of metal binder, hot chemical ablation and mechanical erosion.
梯度材料的抗烧蚀机理为金属粘接剂的挥发损失、热化学烧蚀和机械冲刷。
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