| SRM壳体/绝热层脱粘的XFEM |
| |
| 引用本文： | 李明,关正西.SRM壳体/绝热层脱粘的XFEM[J].上海航天,2007,24(4):34-37,61. |
| |
| 作者姓名： | 李明 关正西 |
| |
| 作者单位： | 第二炮兵工程学院,陕西,西安,710025 |
| |
| 摘 要： | 将扩展有限元法(XFEM)用于研究固体火箭发动机(SRM)壳体/绝热层的脱粘。将层隙型和紧贴型脱粘等效为双材料界面裂纹,建立了XFEM的双材料界面裂纹分析模型,并给出了其中核心算法——应变矩阵的求解,通过相互作用积分求出应力强度因子和能量释放率。算例结果表明,XFEM的计算结果与理论值的差异较小,可用于有效求解脱粘问题。
|
| 关 键 词： | 固体火箭发动机 脱粘 扩展有限元法 界面裂纹 应变矩阵 相互作用积分 |
| 文章编号： | 1006-1630（2007）04-0034-04 |
| 收稿时间： | 2006-09-04 |
| 修稿时间： | 2006-10-08 |
XFEM for Study on Debonds Between Case and Insulation in SRM |
| |
| LI Ming,GUAN Zheng-xi.XFEM for Study on Debonds Between Case and Insulation in SRM[J].Aerospace Shanghai,2007,24(4):34-37,61. |
| |
| Authors: | LI Ming GUAN Zheng-xi |
| |
| Abstract: | The extended finite element method(XFEM) was applied on the study of debonds between case and insulation in solid rocket motor in this paper.The layered and appress debonds were equivalent to bimaterial interface crack.The analysis model of bimaterial interface crack using XFEM was established.The strain matrix that was the core of the algorithm was presented.The stress intensity factor and energy release rate was solved via the interaction integral method.The calculation results showed that the difference between XFEM and theoretic value was rather small.The XFEM could be used in solving the debonds problem of SRM. |
| |
| Keywords: | Solid rocket motor Debond Extended finite element method Interface crack Strain matrix Interaction integral |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
|
