复合材料曲面帽形加筋壁板在内压-轴压联合载荷下的屈曲及承载性能  

Buckling and Post-Buckling of Curved Hat-Stiffened Composite Panels Under Combined Internal Pressure and Axial Compression

作　　者：汪厚冰[1] 李新祥[1] 魏景超 雷安民[1] 成李南 WANG Houbing;LI Xinxiang;WEI Jingchao;LEI Anmin;CHENG Linan(Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure Static and Fatigue,Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室,西安710065

出　　处：《航空制造技术》2020年第18期55-64,81,共11页Aeronautical Manufacturing Technology

基　　金：民机科研项目(MJ-2015-F-038)。

摘　　要：为研究碳纤维增强树脂基复合材料(CFRP)曲面帽形加筋壁板在内压-轴压联合载荷下的屈曲及承载性能,对7长桁、4框的复合材料曲面帽形加筋壁板进行了试验研究。结果表明,内压能提高复合材料曲面帽形加筋壁板轴压屈曲载荷,联合载荷试验中加筋壁板破坏前无屈曲。以复合材料扁壳线性稳定性理论为基础,采用瑞利-里兹法和Kirchhoff假设得到了复合材料曲面加筋壁板在侧压、轴压、内压-轴压联合情况下的屈曲载荷解析表达式,并针对复合材料曲面帽形加筋壁板的结构特点和破坏模式提出一种在内压-轴压联合载荷下轴压破坏载荷的工程估算方法。将解析表达式和工程估算方法的计算结果与试验结果进行了对比,结果表明,解析表达式和工程估算方法与试验结果吻合,表明轴压、内压-轴压联合情况下的屈曲载荷解析表达式能用于屈曲载荷的预测,工程估算方法结构形式简洁,便于在复合材料曲面加筋壁板的设计中应用。Experiments on curved hat-stiffened composites panel with 7 stringers and 4 frames were conducted to investigate the buckling load,buckling mode,post-buckling carrying capacity and failure characterization under combined internal pressure and axial compression.The results show that the axial buckling load of the curved hat-stiffened composites panel is increased by the internal pressure when the panel is subjected to combined mechanical loads,and the panel has no buckle before failure.Based on the linear stability theory of shallow composites shell,the analytical methods for the buckling load of the curved hat-stiffened composites panel were presented by utilizing Rayleigh-Ritz method and Kirchhoff hypothesis under internal pressure,axial compression,combined internal pressure and axial compression,an empirical method was proposed to estimate the failure load of the curved hat-stiffened composites panel under combined internal pressure and axial compression.The results by both the present methods and experiments agree very well,the empirical method is clear and concise,which is easy to be applied in design of curved hat-stiffened composites panel.

关 键 词：复合材料 帽形加筋壁板 联合载荷 屈曲 后屈曲 瑞利-里兹法 

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]