| 摘要: |
| 作为固体火箭发动机燃烧室壁面绝热层的ＥＰＤＭ是一种炭化型热防护材料，受热时形成炭化层和热解层，在燃气和粒子冲蚀下不断减薄并带走热量，有效地保护燃烧室壁。采用气动热化学烧蚀机理，扩散和化学动力学双控制机制，并计入气流与粒子的侵蚀，建立了ＥＰＤＭ的烧蚀模型；同时将烧蚀与移动边界下的传热相耦合进行烧蚀率预示。根据模型预示的烧蚀率与试验结果吻合很好。 |
| 关键词: 固体推进剂火箭发动机 防热 隔热涂层 烧蚀性能 |
| DOI： |
| 分类号:V250.1 |
| 基金项目:航天基础性研究基金 |
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| ABLATION MODEL OF EPDM |
|
He Hongqing, Yan Hong
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Coll of Astronautics,Northwestern Polytechnical Univ.,Xi′an,710072
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| Abstract: |
| EPDM(Ethylene Propylene Diene Monomer)is used as the insulation on chamber wall of SPRM.It is a good protective material of charring type.During being heated it formed the charring and pyrolytic layers.Under ablation and attack of gas and particle,it gradually thinned out and took off great quantity of heat,and the chamber wall was effectively protected.The ablation model of EPDM was built using the aerodynamic thermochemical ablation mechanism and the double control mechanism of diffusion and chemical dynamics.The erosion of gas and particle is regarded also.Simultaneously,the ablative rate was predicted by coupling of ablation with heat conduction under moving boundaries.The predicted ablative rate by the model is good agreement with test results |
| Key words: Solid propellant rocket motor Thermal protection Barrier coating Ablation property |
