| 材料性能对固体发动机结构完整性的影响 |
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| 引用本文： | 蒙上阳,唐国金,雷勇军.材料性能对固体发动机结构完整性的影响[J].国防科技大学学报,2002,24(5):10-15. |
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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,湖南,长沙,410073 |
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| 基金项目： | 国防科技大学基础研究资助项目 (JC0 2 -0 1-0 0 4) |
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| 摘 要： | 基于描述粘弹性材料特性的Burgers模型的本构关系以及基于该本构关系下的有限元方法 ,根据温度载荷和内压载荷的特点 ,分别建立了分析某固体发动机材料性能参数对结构完整性影响的有限元模型。应用MSC/NAS TRAN结构分析软件 ,详细分析了在温度和内压载荷作用下固体发动机材料性能参数对结构完整性的影响。在温度载荷的作用下 ,主要影响结构完整性的是推进剂的泊松比与热膨胀系数 ;在内压载荷作用下 ,主要影响结构完整性的是包覆层和推进剂的泊松比以及推进剂的初始模量。所得的结论可为固体发动机的生产设计提供参考
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| 关 键 词： | 固体发动机 粘弹性 有限元法 结构完整性 |
| 文章编号： | 1001-2486(2002)05-0010-06 |
| 收稿时间： | 3/5/2002 12:00:00 AM |
| 修稿时间： | 2002年3月5日 |
Effects of Solid Rocket Motor Material Properties on the Structure Integrity |
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| MENG Shangyang,TANG Guojin and LEI Yongjun.Effects of Solid Rocket Motor Material Properties on the Structure Integrity[J].Journal of National University of Defense Technology,2002,24(5):10-15. |
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| Authors: | MENG Shangyang TANG Guojin and LEI Yongjun |
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| Affiliation: | College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073,China;College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073,China;College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073,China |
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| Abstract: | Based on the constitutive relationship of viscoelastic material using the Burgers model and the corresponding viscoelastic finite element method, the finite computational models are established to value the effects of solid rocket motor material parameters on the structure integrity. They include the three dimension model and the plane strain model. In the case of thermal loading, the three dimension model is necessary, but the plane strain model is accurate enough in the case of internal pressure. Then, the effects of solid rocket motor material parameters on its structure integrity are respectively compared and analyzed under internal pressure and thermal loading by the use of MSC/NASTRAN software system. Under thermal loading, the main factors affecting the motor structure integrity are the propellant Poission's ratio and thermal expansion coefficient. Under the internal pressure, the main factors are the motor liner Poission's ratio, propellant initial elastic modulus and Poission's ratio. These conclusions would be useful for to the design of solid rocket motors. |
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| Keywords: | solid rocket motor viscoelasticity finite element method structure integrity |
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