中空复合材料结构件模态分析
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摘要
提出了2种中空结构的碳纤维复合材料结构件,包括通孔结构[结构件(1)]和在结构件(1)通孔的最高处增加1个4mm宽的筋结构[结构件(2)]。利用ANSYS有限元软件对2种结构件进行模态分析,得到了结构件在不同结构形状下层压材料的应力应变云图,通过模态扩展,得到了对应结构件的变形量。结果表明,结构件的最大应力发生在靠近根弦的地方,对比2种结构件,中空孔添加4mm的支撑筋后,最大变形量从57.3mm减小到13.9mm,刚度提高了75.77%。
The two different hollow structures made of carbon fiber composite were put forwarded. The one was a throughhole,and the other was the structure which was added 4mm wide beam at the highest point of through-hole. Meanwhile,the modal analysis was carried out on the structure by means of ANSYS finite element software. And the laminate stress and strain cloud image was generated. Furthermore,the deformation of corresponding structure was obtained by modal expansion. The results showed that the maximum stress occurred in the structure root chord. Compared with the two kinds of structures,when the supporting rib of 4mm wide was added into the hollow hole,the maximum deformation was reduced from 57. 3mm to 13. 9mm,and the structure rigidity could be increased by than 75. 77%.
The two different hollow structures made of carbon fiber composite were put forwarded. The one was a throughhole,and the other was the structure which was added 4mm wide beam at the highest point of through-hole. Meanwhile,the modal analysis was carried out on the structure by means of ANSYS finite element software. And the laminate stress and strain cloud image was generated. Furthermore,the deformation of corresponding structure was obtained by modal expansion. The results showed that the maximum stress occurred in the structure root chord. Compared with the two kinds of structures,when the supporting rib of 4mm wide was added into the hollow hole,the maximum deformation was reduced from 57. 3mm to 13. 9mm,and the structure rigidity could be increased by than 75. 77%.
引文
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[4]修英姝,崔德刚.复合材料层合板稳定性的铺层优化设计[J].工程力学,2005,22(6):212-216.
[5]谷良贤,温炳恒.导弹总体设计原理[M].西安:西北工业大学出版社,2004,8-92.
[6]Wang Wei,Yang Wei,Chang Nan.Integration shape and sizing optimization of composite wing structure based on response surface method[J].Transactions of Nanjing University of Aeronautics&Astronautics,2008,25(2):94-100.
[7]赵美英,陶梅贞.复合材料结构力学与结构设计[M].西安:西北工业大学出版社,2007,6-98.
[8]沈真.复合材料结构设计手册[M].北京:航空工业出版社,2001,10-86.
[9]王丽伟.复合材料T型尾翼结构的优化设计研究[D].南京:南京航空航天大学,2012.
[10]岳珠峰,王福生,王佩艳,等.飞机复合材料结构分析与优化设计[M].北京:科学出版社,2011,16-95.
[11]冯刚,张铎,张彦考,等.复合材料弹翼——弹身组合结构强度计算[J].强度与环境,2001(4):49-54.
[12]赵群.复合材料翼面结构布局优化设计方法研究[D].南京:南京航空航天大学,2010.
[13]王天舒.蜂窝复合材料舱体及其结构件的仿真与优化[D].哈尔滨:哈尔滨工业大学,2013.
[14]聂毅,余雄庆.翼面隐身结构在飞航导弹模型上的数值仿真研究[J].宇航学报,2006,27(6):1369-1372.
[15]范宇.复合结构飞行器翼面RCS的数值计算[D].成都:电子科技大学,2004.
[16]周鹏展,肖加余,曾竞成,等.基于ANSYS的大型复合材料风力机叶片结构分析[J].国防科技大学学报,2010,32(2):46-50.