开展了高压强条件下的喷管烧蚀试验研究，揭示了压强对喷管烧蚀率的影响规律。
The relation between pressure and instantaneous linearity erosion rate was obtained through nozzle ablation experiments under high pressure.
采用该方法开展了变粒子流量的喷管烧蚀试验，获得了粒子流量对喷管烧蚀率的影响规律。
Nozzle ablation experiments using the method mentioned above were carried out, and the influence of particle-flux on the erosion-rate of nozzle was obtained.
本文针对这种情况开展了喷管喉衬的烧蚀试验研究。
Experiments research were carried out for the throat of nozzle.
固体火箭发动机喷管的烧蚀预示是喷管结构分析的重要一环。
Ablation prediction of solid rocket motor nozzle is an important link for nozzle structure analysis.
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 mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied.
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。
Experimental method for ablation of throat liner material in a high pressure gas launch device is introduced.
分析了喷管收敛段绝热层及喉衬的局部烧蚀问题；
The local ablation of thermal insulation barrier in nozzle convergence region and of throat insert is analysed.
分析了喷管收敛段绝热层及喉衬的局部烧蚀问题；
The local ablation of thermal insulation barrier in nozzle convergence region and of throat insert is analysed.
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