| 导弹轨姿控舱体的强度分析 |
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| 引用本文： | 相升海,张平,李世鹏,方蜀州.导弹轨姿控舱体的强度分析[J].固体火箭技术,2006,29(5):350-353. |
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| 作者姓名： | 相升海 张平 李世鹏 方蜀州 |
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| 作者单位： | 北京理工大学机电工程学院,北京,100081 |
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| 基金项目： | 国家高技术研究发展计划(863计划) |
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| 摘 要： | 借助NASTRAN和PATRAN有限元分析软件,对承受多种加载方式的导弹轨姿控舱体进行了有无补强措施对比的强度分析。计算结果表明,轨姿控舱体设计的安全系数高;采取施加压紧盖的补强措施后,可分别使轨姿控舱体的最大应力值和最大变形量约降低到原值的1/2。试验结果证明,这种计算分析方法有效、可靠。
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| 关 键 词： | 导弹轨姿控舱体 有限元法 强度分析 舱体结构 |
| 文章编号： | 1006-2793（2006）05-0350-04 |
| 收稿时间： | 2005-10-19 |
| 修稿时间： | 2005-11-24 |
Analysis on strength of the orbit and attitude control section body for missile |
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| XIANG Sheng-hai,ZHANG Ping,LI Shi-peng,FANG Shu-zhou.Analysis on strength of the orbit and attitude control section body for missile[J].Journal of Solid Rocket Technology,2006,29(5):350-353. |
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| Authors: | XIANG Sheng-hai ZHANG Ping LI Shi-peng FANG Shu-zhou |
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| Institution: | School of Mechano-Electronics Engineering, Beijing Institute of Technology, Beijing 100081, China |
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| Abstract: | The for orbit and attitude control section body for missile under multi-loading modes was analyzed by means of NASTRAN and PATRAN finite element softwares,and its structure strength with and without reinforcement measures was compared.The calculated results show that safety coefficient of design for the section body is high,and the maximum stress value and the maximum deformation value of the section body with cover reinforcement measures are approximately a half of those without any measures.The test results prove that the calculation analysis method is effective and reliable. |
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| Keywords: | orbit and attitude control section body for missile finite element method strength analysis section body structure |
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