硬壳式导弹舱段的动力学特性分析  

DYNAMIC CHARACTERISTIC ANALYSIS OF SHELL - SHAPED MISSILE CABIN

作　　者：黄鹏[1] 王立伟 王妍[3] 

机构地区：[1]哈尔滨工程大学,黑龙江哈尔滨150001 [2]哈尔滨水暖器材厂,黑龙江哈尔滨150020 [3]黑龙江大学,黑龙江哈尔滨150080

出　　处：《南阳理工学院学报》2012年第6期69-72,共4页Journal of Nanyang Institute of Technology

摘　　要：导弹舱段的动力学特性分析是导弹设计中的一个重要环节。由于导弹舱段主要承受集中力和集中质量的特点,本文首先建立了舱段的简化分析模型,采用传递矩阵法对该简化了的舱段模型进行理论分析,同时对该模型进行有限元法模拟,对比可知,两种方法获得的舱段振型相符。在以上分析的基础上,为使计算接近舱段实际结构,利用ANSYS建立完整舱段的有限元计算模型,对该模型进行动力学仿真后得出其5阶振型及其对应的振动频率。本文的分析结果为完整舱段的振动特性提供了直观的认识,可以为舱段结构的实际设计提供理论参考,具有一定的借鉴意义。The dynamic characteristic analysis of missile cabin plays an important role in design of a missile. As missile cabin mainly subjects the concentrated mass and force,the simple model of it was built firstly in this paper. The results calculated on this model by transfer matrix method matched well with that of finite element way,and the vibration mode nearly the same. According to that,the whole model of missile cabin was calculated by ANSYS in purpose to study the real cabin,five modes and their frequencies were got in the paper. The results of our study can provide a visual cognition and give a reference to the practical design of missile.

关 键 词：导弹舱段 动力特性 ANSYS 

分 类 号：O326[理学—一般力学与力学基础]