Stability and post-buckling carrying capacity of aeronautic composite stiffened panel under shear loading
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摘要: 开展了复合材料加筋板剪切稳定性试验,研究了加筋板在承剪状态下的屈曲载荷、屈曲模态、后屈曲承载性能及破坏模式。试验结果表明,加筋板在剪切屈曲载荷下形成的屈曲波长轴线与加强件轴线夹角约45°,当屈曲比达到1.2时,存在二次屈曲行为,最终破坏载荷约为屈曲载荷的1.28倍;加筋板在二次屈曲失稳前,加强件几乎保持直线,起"屈曲分隔"的作用。结合试验现象,进行了加筋板剪切屈曲及后屈曲性能理论分析,得出的理论屈曲载荷与试验屈曲载荷的相对误差为7.2%,后屈曲阶段的理论载荷-应变曲线与试验结果的相对误差在10%以内,并确定了后屈曲角随屈曲比的变化规律。Abstract: Shear stability experiments on aeronautic composite stiffened panel were conducted to investigate the buckling load, buckling mode, post-buckling carrying capacity and failure characterization. The results show the centric lines of buckling waves have an angle of 45° with the direction of stiffeners under shear buckling load. The re-buckling behaviors will occur when the buckling ratio reaches 1.2. Failure load is 1.28 times of the buckling load. The stiffeners work as 'skin buckling separated' before re-buckling, and have little deformation. Theoretical analysis on the buckling and post-buckling behaviors was carried out. The buckling load by theoretical analysis is in a good agreement with experimental results with an error of 7.2%. Additionally, the slope of load-strain curve in post-buckling stage by theoretical analysis also leads an error less than 10% compared with experimental data. Finally, the variation law of the post-buckling angle and buckling ratio was determined.
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Key words:
- composite stiffened panel /
- shear /
- buckling /
- post-buckling /
- theoretical analysis
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