帽型加筋机身曲板后屈曲设计研究  

RESEARCH ON POST-BUCKLING DESIGN OF HAT-STRINGER STIFFENED FUSELAGE PANELS

作　　者：袁菲[1] 林国伟[1] 李新祥[1] 陈向明[1] YUAN Fei;LIN GuoWei;LI XinXiang;CHEN XiangMing(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi'an 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：《机械强度》2024年第6期1408-1418,共11页Journal of Mechanical Strength

基　　金：民机科研项目(MJ-2015-F-038,MJ-2016-F-01)资助。

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。提出了含内包层和无内包层帽型加筋机身曲板设计方案,使用Abaqus计算了有内包层和无内包层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。模型中使用蔡-吴准则作为复合材料的失效判据,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,延长结构的后屈曲历程。Composite stiffened panel structure is widely used in modern aircraft,which is prone to buckling under working conditions.A large number of tests show that the aircraft composite stiffened thin-wall structure has considerable post-buckling bearing capacity.The design scheme of the stiffened fuselage curved panel with inner cladding and without inner cladding was proposed.The buckling load,bearing capacity and failure mode of the two kinds of curved panels with inner cladding and without inner cladding were calculated by using Abaqus under axial compressive load,pure shear load and compressive shear combined load.In the model,the Tsai-Wu criterion was used as the failure criterion of composite materials,and the damage evolution was realized by the subroutine Usdfld.It is found that the inner cladding of the hat stringer can significantly improve the post-buckling capacity of the structure and prolong the post-buckling process.

关 键 词：复合材料 机身曲板 内包层 帽型筋条 后屈曲 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]