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为扩充航空复合材料结构稳定性设计手段,基于Levy形式级数和有限差分法,提出了面内纯弯曲载荷作用下两边简支两边固支(SSCC)复合材料层合板临界屈曲载荷的数值解法。首先,应用有限差分法将挠度函数进行离散化处理;然后利用边界条件扩充方程组,最后将临界屈曲载荷的求解转化为广义特征值问题。通过数值算例分别在各向同性板和复合材料层合板上验证了本文方法,并与有限元方法(FEM)进行了比较。结果表明,本文方法具有很高的精度,为复合材料层合板的屈曲分析开辟了新的途径。
Based on the Levy formal series and the finite difference method, a numerical solution to the critical buckling load of composite simply supported (SSCC) composite laminates under in-plane pure bending loads is proposed to increase the structural stability of the aerospace composite. First, the finite difference method is used to discretize the deflection function. Then, the boundary conditions are used to expand the system. Finally, the solution of the critical buckling load is transformed into the generalized eigenvalue problem. The numerical method is used to validate the proposed method on isotropic and composite laminates respectively and to compare it with the finite element method (FEM). The results show that the proposed method has high accuracy and opens up a new way for the buckling analysis of composite laminates.