复合材料双曲机身蒙皮铺层角度偏差分析

Research on the Deviation of Skin Plies of Composite Double Curvature Fuselage Stiffened Panel

民用飞机中后机身收缩段和后机身段由于收缩和修形,机身壁板为双曲,蒙皮与长桁之间可能发生10°以上的铺层角度偏差。以某型飞机的复合材料双曲机身壁板为例,从设计和制造两方面分析了产生角度偏差的原因。采用适当的工程算法,评估了偏差对蒙皮轴压屈曲、剪切屈曲和壁板轴压屈曲稳定性的影响。分析结果显示,在0~15°偏差范围内,蒙皮轴压屈曲载荷最大下降可达7%,需要在设计和试验中予以关注。

The deviation may reach 10°between skin plies and stringer of composite stiffened panel on the mid-after fuselage and after fuselage which have a double curvature profile by shaping.Taking civil aircraft composite panel as an example,the design and manufacturing considerations are analyzed in this paper.The stability of stiffened panel is also analyzed by choosing appropriate engineering method.The results show that the maximum reduction of the buckling load of the skin under compression can reach 7%within the deviation range of 0°to 15°,which needs to be paid attention to in the design and test.