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。
Numerical simulation of high temperature thermal chemical ablation for carbon composite material was done and the ablation results were calculated.
对炭基复合材料在不同环境下热化学烧蚀过程进行了数值模拟，对烧蚀产物进行了计算。
Experimental method for ablation of throat liner material in a high pressure gas launch device is introduced.
介绍一种高压燃气发射装置喷管喉衬材料的烧蚀试验方法。
The test result showed that sepiolite fibre reinforced phenolic resin-based composite was a new ablation-resistant material for heat protection.
试用结果表明，海泡石纤维增强酚醛复合材料是一种新型耐烧蚀绝热防护材料。
The results show that the axis linear ablation rate of the material has a great change and the linear ablation increases along the gas flux direction.
结果表明：导流管轴向线烧蚀率变化较大，沿气流方向呈上升趋势。
The ablation mechanisms of components are particles erosion and mechanical denudation. Material failure is mainly caused by the thermal stress.
同时，材料所受到的热应力是引起材料失效的主要原因。
The ablation mechanisms of components are particles erosion and mechanical denudation. Material failure is mainly caused by the thermal stress.
同时，材料所受到的热应力是引起材料失效的主要原因。
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