| 固体发动机包覆层与推进剂界面脱粘裂纹稳定性分析 |
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| 引用本文： | 蒙上阳,唐国金,雷勇军.固体发动机包覆层与推进剂界面脱粘裂纹稳定性分析[J].固体火箭技术,2004,27(1):46-49,72. |
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| 作者姓名： | 蒙上阳 唐国金 雷勇军 |
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| 作者单位： | 国防科技大学航天与材料工程学院,长沙,410073 |
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| 基金项目： | 国防科大预研基金项目(JC02 01 004)，湖南省自然科学基金资助项目(02JJY2009)。 |
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| 摘 要： | 为了判断固体发动机药柱包覆层与推进剂界面脱粘裂纹在燃气内压和轴向过栽联合作用下的稳定性，以翼锥药型并含前后伞盘的固体发动机为例，应用有限元方法，建立界面脱粘的三维有限元计算模型，在界面脱粘裂纹尖端设置三维奇异裂纹元，模拟裂纹扩展。通过在包覆层与推进剂界面上设置不同深度的脱粘，分别计算不同深度时脱粘裂纹的应力强度因子，得到裂纹应力强度因子随脱粘深度的变化规律，由此判断裂纹的稳定性。
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| 关 键 词： | 固体发动机 包覆层 推进剂 界面脱粘裂纹 稳定性分析 应力强度因子 |
| 文章编号： | 1006-2793(2004)01-0046-04 |
Stability analysis of the interfacial debonded crack between propellant and liner of solid rocket motor grains |
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| Abstract: | In order to judge the stability of the interfacial debonded crack between propellant grain and liner under joint action of internal pressure and axial acceleration load in solid rocket motors(SRM), three-dimension finite elements calculation models of the interfacial debonded crack are established and the three-dimension singular crack elements near the crack tip are set up to simulate the interfacial debonded crack propagation. A SRM with the grain configuration of fin cone and fore and aft umbrella-type trays is taken as example. Aimed at different inerface debonded depthes, the stress intensity factors are calculated respectively and the calculated results can be used to judge the crack stability. |
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| Keywords: | solid propellant rocket engine finite element method stress-intensity factor singular crack element interfacial debonded crack |
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