铺层对复合材料层合板力学性能影响的研究

Research on the Effect of Layup on the Mechanical Properties of Composite Laminates

为了研究不同铺层角和铺层厚度对复合材料层合板力学性能影响,通过转换复合材料刚度矩阵,得到复合材料层合板等效弹性常数,利用Matlab软件将计算复合材料层合板等效为计算等厚度各向异性板,研究不同铺层角对层合板力学性能影响;基于此等效方法,利用Fortran程序计算机翼剖面刚度,研究不同铺层厚度对层合板力学性能影响。结果表明:铺层角对复合材料层合板有较大影响,其中以45°铺层角作为最外层的层合板力学性能最佳,其次为90°和0°铺层角;随铺层厚度增加,机翼剖面的剪切刚度、弯曲刚度和扭转刚度几乎呈线性增大。研究成果为分析与设计飞机复合材料结构提供参考。

In this paper,the equivalent elastic constants of composite laminates are obtained through the conversion of composite stiffness matrix.Using Matlab,the calculation of the composite laminated material equivalent to the anisotropic board of equal thickness was realized,and the impact of plyangle on the mechanical properties of the laminated was studied.The results show that the plyangle has a greater impact on composite laminates.Among them,the mechanical properties of the laminates with 45°as the outermost layer are the best,followed by 90°and 0°;with the increase of the thicknesses of the laminates,the shear,bending,and torsional stiffness of the wing cross section increases almost linearly.The research results provide references for the analysis and design of aircraft composite materials.