多梁式中央翼盒下壁板压缩稳定性研究  

Stability Study of Buckling on Stiffened Lower Panel for Center Wing Box with Multi-beam

作　　者：龚德志[1] 王新栋 叶聪杰[1] 

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《民用飞机设计与研究》2017年第4期88-94,共7页Civil Aircraft Design & Research

摘　　要：研究多梁式翼盒加筋壁板在压缩载荷作用下的稳定性。针对端部支持、侧边支持、本身曲率以及上述因素的综合作用对加筋壁板压缩失稳临界应力的影响进行分析,对目前文献资料中关于加筋壁板压缩稳定性临界应力计算公式中端部支持系数进行适当修正,以得到适合的壁板屈曲应力。研究发现,端部夹持、侧边梁支持和蒙皮自身曲率对加筋壁板的压缩稳定性有较大影响,对于蒙皮较厚的加筋曲板(如机翼壁板),建议的等效端部支持系数为1.5~2.0。This paper studies the buckling of stiffened lower panel of center wing box with multi-beam under compressive loading. For the effect of end support, lateral support and curvature for the buckling of panel, the end support fact of critical compressive stress formula of stiffened panel in current design manual was analyzed, and proper buckling stress of stiffened panel was obtained. The result shows that the end support , lateral support and curvature of skin make a significant effect on the stabilization of stiffened panel under compressive loading, and for the stiffened panel with thick shin, the end support fact is advised to be 1.5 - 2.0.

关 键 词：多梁式翼盒 加筋板 屈曲 端部支持系数 

分 类 号：V224[航空宇航科学与技术—飞行器设计]