面内弯曲载荷作用下两边简支两边固支复合材料层合板的屈曲  

Buckling of SSCC Composite Laminates Under In-plane Bending Load

作　　者：袁坚锋 尼早[1] 陈保兴[1] 

机构地区：[1]中国商飞上海飞机设计研究院,上海201210

出　　处：《航空学报》2014年第4期1026-1033,共8页Acta Aeronautica et Astronautica Sinica

摘　　要：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。In order to provide a stability analysis method of composite airframe structures, this paper presents a numerical solution method for the buckling of SSCC composite laminates （laminates having two parallel edges simply supported and the remaining parallel edges clamped） based on the Levy form series and finite-difference method. First, the deflection function is transformed to a discrete form by the finite-difference method; then, the system of equations is supplemented by the boundary conditions; finally, the critical buckling load is obtained through solving a generalized eigenvalue problem. Numeri- cal examples are utilized to verify the present method on both isotropic and composite plates. The comparison of the present method and a finite element method （FEM） is conducted as well. The result shows that the present method has high accuracy and provides a new way for the buckling analysis of composite plates.

关 键 词：复合材料层合板 面内纯弯曲载荷 有限差分法 屈曲 临界屈曲载荷 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程] TB332[一般工业技术—材料科学与工程]