THE ITERATION DESIGN METHOD OF AN UNMANNED AIRCRAFT COMPOSITE WING BEAM AND STRENGTH CHECK BY FINITE ELEMENT METHOD

Abstract

Abstract: The inner forces of web and caps of an unmanned aircraft composite wing beam under uniformly distributed air lift is calculated based on the loading characteristics of the beam. The layer structure of the composite wing beam is designed using iterative method through Matlab programming. The design procedure is based on the classical laminate theory and maximum stress strength criterion. The finite element model of the composite wing beam is built, based on which the strength check is done using maximum stress criterion. The safety margin coefficient of each layer is given. It shows that the layer structure of composite wing beam can be properly designed by iteration method based on classical laminate theory. The iteration procedure is convergent. The least margin of safety of each layer is 0.981, which is greater than 0.5. Therefore, the design of the composite wing beam is a success which gives enough strength and light weight.

Key words: composite material, wing beam, iteration method, finite element method, strength

CLC Number:

TB332

ZHANG Cheng-lei, LIU Feng, MA Jia. THE ITERATION DESIGN METHOD OF AN UNMANNED AIRCRAFT COMPOSITE WING BEAM AND STRENGTH CHECK BY FINITE ELEMENT METHOD[J]. COMPOSITES SCIENCE AND ENGINEERING, 2014, 0(1): 72-75.

References

[1] Pora J. Hinrichsen J. Material and technology developments for the A380[C]Proceedings of the 22^nd International SAMPE Europe Conference, 2001.1232134.
[2] Brosius D. Boeing 787 update [J]. High Performance Composite, 2007,(05):56259.
[3] 王亚妮,袁昌盛,孔德拴.复合材料工字梁结构分析[J]. 兵器材料科学与工程,2012,(04):7-83.
[4] 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. 11-23.
[5] Li R, Kelly D, Crosky A. Strength improvement by fibre steering around a pin loaded hole [J]. Composite Structures, 2002, 57(1): 377-383.
[6] 高轩能,张建文.工字钢梁腹板的弹塑性屈曲强度研究及其高厚比计算[J]. 钢结构,1999,(02):54-58.
[7] 王星,王凡,蔡思远.板锥网壳结构复合材料层合板的屈曲分析[J]. 玻璃钢/复合材料,2009,(04):6-10.
[8] 中国航空研究院编.复合材料结构稳定性分析指南[M].北京:航空业出版社,2002.5-9.
[9] 王耀东,何景武,夏盛来.复合材料叶片结构设计中的几个关键问题探讨[J]. 玻璃钢/复合材料,2012,(01):34-38.
[10] 牛春匀(美).实用飞机复合材料结构设计与制造[M]. 北京:航空工业出版社,2010.357-362.
[11] Le Riche R, Haftka R T. Optimization of laminate stacking sequence for buckling load maximization by genetic algorithm[J]. AIAA journal, 1993, 31(5): 951-956.
[12] 刘博,黄争鸣.复合材料风机叶片结构分析与铺层优化[J]. 玻璃钢/复合材料,2012,(01):3-7.
[13] 矫桂琼,贾普荣.复合材料力学[M]. 西安:西北工业大学出版社,2008.89-98.
[14] Hart-Smith L J. Analysis and Design of Advanced Composite Bonded Joints[Z]. NASA CR-2218,1973.
[15] Nugis R G. Longevity of structures made from glassy plastics and having a margin of safety[J]. Polymer Mechanics, 1970, 6(2): 306-309.