考虑帽型加筋包覆层的机身曲板后屈曲设计研究  

Research on Postbuckling Design of Hat-stringer Stiffened Fuselage Panels

作　　者：张昭[1] 袁菲[1] 林国伟[1] Zhang Zhao;Yuan Fei;Lin Guowei(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi'an,Shaanxi,710065,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,西安710065

出　　处：《飞行器强度研究》2024年第2期10-21,共12页Aircraft Strength Research

摘　　要：复合材料加筋壁板结构广泛应用于现代飞机中,此类结构在工作状态下容易发生屈曲,大量试验表明飞机复合材料加筋薄壁结构具有可观的后屈曲承载能力。本文提出了含内包层和无内包层帽型加筋机身曲板设计方案.采用分析软件计算了有内包层和无内包层的两种曲板在轴压载荷、纯剪切载荷、压剪复合载荷下的屈曲载荷、承载能力以及破坏模式。模型中蔡-吴准则作为复合材料失效判据,损伤演化采用子程序USDFLD实现。分析发现帽型筋条的内包层可以显著提高结构的后屈曲承载能力,延长后屈曲历程。Stiffened composite panels are widely used in modern aircraft.Such structures tend to buckle under working conditions.It has been proved that this kind of structures has a considerable post-buckling load-bearing history.The influ-ence of internal cladding layer on buckling and postbuckling of large curved fuselage panel is investigated in this paper.Two kinds of curved panels(with and without internal cladding layer)under compression,shear and combined load are simulated with ABAQUS.Buckling behavior and damage process are researched.Tsai-Wu criterion is adopted to determine the dam-age initiation of composite layers.Cohesive elements are used to simulate the adhesive layer between skin and flange.Cladding layer can improve failure load of hat-stringer stiffened composite panels.

关 键 词：复合材料 机身曲板 内包层 帽型筋条 后屈曲 

分 类 号：TB3[一般工业技术—材料科学与工程]