摘要
机翼壁板一般是航空薄壁加筋结构,筋条对蒙皮提供弹性支持,不同的桁条-蒙皮刚度对加筋板的支持效率不同,存在最优点。本文基于有限元分析方法,研究复合材料加筋壁板的不同桁条-蒙皮刚度对其屈曲模式的影响规律。由于复合材料各向异性的力学性能特点,设计参数较多,在机翼壁板的优化设计中,通常采用分级优化的思想。在蒙皮铺层优化结果的基础上,可将机翼结构模拟成盒段结构,并将其参数化,通过桁条-刚度比例系数(加筋比,厚度比),可以计算出盒段结构上筋条的细节尺寸。将桁条-蒙皮刚度比例系数作为变量,利用PCL参数化建模手段,短时间内建立不同桁条-蒙皮刚度对应的有限元模型,并进行稳定性分析。通过不同的桁条-蒙皮刚度比例和对应的加筋壁板结构承载效率,做出经验曲线,然后根据经验曲线可以实现机翼壁板的快速化设计。
Wing panel usually use thin stiffened panels, with elastic support of stringers. The different stringer-panel stiffness ratio has the different support efficiency in stiffened panel with an optimal value in all the ratios. Based on FEM a research of the relationship between stringer-panel stiffness ratio and the buckling models of the composite stiffened panel is done in this paper. Because the composite materials are typically anisotropic with more design parameters, the hierarchy optimized design method is frequently used in the wing optimized design. On the basis of stacking sequence of the laminated, we can use a box structure to simulate wing structure and parameter define the box. Then the dimensions of stringers can be calculated by the stringer-panel stiffness ratio （ratio of the area of stringer cross-section and wing panel cross-section, ratio of thickness）. Then a lot of Finite Element Model will be created by PCL with the variable of stringer-panel stiffness ratio and be analyzed in bucking. The experience curve in which the efficiency of stiffened panel is plotted against the stringer- panel stiffness ratio can be got. At last, the rapid design can be achieved by the experience curve.
出处
《飞机设计》
2013年第4期25-30,共6页
Aircraft Design
基金
南京航空航天大学基本科研业务费专项科研项目NS2011003
关键词
加筋板
复合材料
机翼盒段结构
参数化建模
屈曲
stiffened panel
composite materials
wing box structure
parametric building model
buckling
