摘要
将复合材料层合板理论拓展到复合材料波纹层合板,得到了其拉伸、耦合和弯曲刚度的解析表达式。其次,阐述了将波纹板刚度输入到MSC/NASTRAN材料卡中的技巧,以及如何对含波纹板结构进行有限元建模分析。最后,将波纹板的刚度计算方法及建模方法应用于对某型号的中厚蒙皮复合材料多墙结构翼盒静强度计算,得到了结构测点处的位移和应变计算值。同传统的有限元分析结果比较表明,采用本文分析方法得到的计算结果更接近于试验实测值:在纯弯工况中,位移和应变计算值相对误差的平均值从9.1%和17.4%分别下降到5.2%和4.1%;在弯扭工况中,相对误差的平均值从10.5%和18.3%分别下降到6.0%和5.7%。
By extending the classical laminate theory to the cross section of a corrugated plate with sinusoidal profile,the membrane,bending and membrane-bending coupling stiffness terms of the corrugated plate are obtained in the form of analysis formulae. Techniques are presented for implementing these stiffness terms into the material bulk data cards of MSC/NASTRAN and for modeling a corrugated plate with a single plane of shell elements. The methods given in this article are applied to obtain static solutions of a composite wing box with corrugated webs. The displacements and strains at the gauge sensor locations are acquired. Compared with the results acquired by traditional finite element analysis,the results obtained in this article agree better with those obtained by the gauge sensors. When the structure is subjected to pure bending load,the average relative errors of computed displacements and strains decrease to 5.2% and 4.1% from 9.1% and 17.4 %,respectively;when the structure is subjected to bending and twisting loads,they decrease to 6.0% and 5.7% from 10.5% and 18.3%,respectively.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第6期1570-1575,共6页
Acta Aeronautica et Astronautica Sinica
关键词
复合材料
波纹板
结构刚度
结构强度
有限元建模
composites
corrugated plate
structure stiffness
structure strength
finite element modeling
