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固体火箭喷管喉衬材料的烧蚀是化学反应与传热、传质相耦合的过程.基于气动热力学、热化学动力学和传热学,建立了热化学烧蚀模型;并对H2含量、频率因子、活化能引起喷管内热流场与化学烧蚀的变化进行了数值模拟.计算结果表明:在高温高压燃烧环境下,H2频率因子与活化能的变化引起烧蚀机制的改变,但H2频率因子的变化影响并不明显;固体火箭喷管烧蚀控制机制的判别应由喷管内燃气中H2的含量与烧蚀环境下H2活化能来决定.该研究结果为固体火箭的热防护设计提供参考.
The ablation of throat lining material of solid rocket nozzle is a process of chemical reaction coupled with heat and mass transfer.The thermochemical ablation model was established based on aerodynamic thermodynamics, thermochemical kinetics and heat transfer theory.H2 content, Frequency factor and activation energy of the nozzle are numerically simulated.The results show that the change of H2 frequency factor and activation energy causes the ablation mechanism to change under the condition of high temperature and high pressure combustion, The influence of the change of frequency factor is not obvious.The determination of the control mechanism of the solid rocket nozzle ablation should be determined by the content of H2 in the gas inside the nozzle and the activation energy of H2 under ablation environment.The results of this study provide the thermal protection design of solid rocket reference.