剪切载荷作用下复合材料机翼梁腹板开口分析

Analysis on openings of composite laminated aircraft wing beam web under shear load

通过对某民用飞机复合材料机翼梁腹板开口的研究,总结出了一套可行、高效、经济的开口设计方法。首先,根据复合材料层压板的设计原则,确定翼梁的铺层顺序和铺层比,继而将梁腹板与梁缘条整体铺设成型;然后,通过利用经典层压板理论计算翼梁的等效材料属性,推导出了计算不同厚度的复合材料层压板等效弹性模量的方法;最后,分析了剪切载荷作用下开口形状、角度对复合材料机翼梁腹板强度的影响。该研究方法不仅解决了具体的工程设计问题,而且总结设计过程,提出一套切实可行、经济高效的复合材料开口形状的设计方法,具有一定普遍性,能够有效削减研发成本和缩短开发周期,同时还可应用到其他类型的复合材料层压板开口问题中。

A feasible,efficient and economical opening design method was obtained by the study of composite laminated wing beam web for certain a civil aircraft. Firstly,the layer sequence and layer ratio of the wing beam were determined based on design principle of the composite laminate,and then the beam web and beam flange were solidified into an integer. Secondly,the equivalent material property of the wing beam was calculated by the classical laminate theory. During the calculating process,s method was further deduced to calculate the equivalent elastic modulus of the composite laminate with different thickness. Finally,effects of opening shape and angle on strength of the composite wing beam web under shear loading were analyzed.The research method not only solves the problems of specific engineering design,but also summarizes the design process. The research presents a set of feasible,economic and efficient design method of composite material opening shape,which has a certain universality,and can reduce development costs effectively and shorten the development cycle. While it also can be applied to solve the opening problems of other types of composite laminate.