工程科学学报，第40卷，第7期：857-863,2018年7月 Chinese Journal of Engineering,Vol.40,No.7:857-863,July 2018 DOI:10.13374/j.issn2095-9389.2018.07.012;http://journals.ustb.edu.cn 薄铺层复合材料薄壁管轴压屈曲行为研究 黄春芳，肖加余，黄展鸿，张鉴炜，鞠苏，江大志区 国防科技大学材料科学与工程系，长沙410073 区通信作者，E-mail:jiangdz(@nudt.cdh.cm 摘要在薄壁结构的应用中，屈曲稳定性是影响其承载性能的关键因素，为研究减薄铺层厚度对复合材料薄壁结构局部屈 曲行为的影响，本文采用不同厚度(0.1250.055和0.020mm)的预浸料制备复合材料薄壁管，实验测试了其在轴压下的局部 屈曲行为.实验结果表明，随着铺层厚度减薄，实验采用的正交和均衡两种铺层方式的复合材料薄壁管局部屈曲载荷均随之 提高，而屈曲失效模式没有发生改变.力学分析表明，铺层厚度减薄后，管壁弯曲刚度的改变和层间剪切应力分布对薄壁管局 部屈曲载荷提高有重要影响.采用薄铺层制备复合材料薄壁结构件能够有效提高其局部屈曲能力. 关键词复合材料：薄铺层；薄壁管；压缩；屈曲载荷 分类号TB332 Buckling of composite cylindrical shells fabricated using thin-ply under axial compres- sion HUANG Chun-fang,XIAO Jia-yu,HUANG Zhan-hong,ZHANG Jian-wei,JU Su,JIANG Da-zhi Department of Materials Science and Engineering,National University of Defense Technology,Changsha 410073,China Corresponding author,E-mail:jiangdz@nudt.edu.cn ABSTRACT Carbon-fiber reinforced polymer (CFRP)composites possess high specific stiffness and strength and have been widely used as structural materials in aerospace and aircraft engineering.In many practical applications,such as wing skin,loading condition is a complexity of tension,bending,and torsion.Therefore,fabricating CFRP composite laminates of multiple-angled plies is necessary to achieve balanced mechanical properties and meet the loading requirements under different working conditions.However,considering the size and weight limitations,designing a quasi-isotropic laminate with standard ply thickness (0.125 mm)is difficult.The recently developed spread-tow technique has provided a promising strategy to fabricate composite laminates of thin and light plies for the produc- tion of thinner and lighter laminates and structures and improvement of mechanical performance.Laminates fabricated using thin plies exhibit much higher strength in tension,compression,and impact as compared with standard-ply laminates because of the associated positive size effects.In the thin-walled structure,buckling stability is the primary factor determining the mechanical performance.In this study,composite cylindrical shells with different ply thickness (0.125,0.055,and 0.020mm)were fabricated via cross-ply and balanced stacking using the spread-tow technique,and their buckling behaviors under axial compression were studied.The experimen- tal results show that with decreasing ply thickness,the critical buckling loads of composite cylindrical shells with cross-ply and bal- anced stacking under axial compression increase,whereas the buckling mode of composite cylindrical shells remains constant.Mechan- ical analysis indicates that the bending stiffness variation and interlaminar shear stress distribution play a key role in increasing the criti- cal buckling load of the composite cylindrical shells,and the application of thin plies effectively improves the local buckling perform- ance of the thin-walled composite structures. KEY WORDS composites;thin-ply;thin-walled cylindrical shell;compression;critical buckling load 收稿日期：2018-03-29 基金项目：国家自然科学基金资助项目(11202231，U1537101,51403235)工程科学学报,第 40 卷,第 7 期:857鄄鄄863,2018 年 7 月 Chinese Journal of Engineering, Vol. 40, No. 7: 857鄄鄄863, July 2018 DOI: 10. 13374 / j. issn2095鄄鄄9389. 2018. 07. 012; http: / / journals. ustb. edu. cn 薄铺层复合材料薄壁管轴压屈曲行为研究 黄春芳, 肖加余, 黄展鸿, 张鉴炜, 鞠 苏, 江大志苣 国防科技大学材料科学与工程系, 长沙 410073 苣 通信作者,E鄄mail: jiangdz@ nudt. edu. cn 摘 要 在薄壁结构的应用中,屈曲稳定性是影响其承载性能的关键因素,为研究减薄铺层厚度对复合材料薄壁结构局部屈 曲行为的影响,本文采用不同厚度(0郾 125、0郾 055 和 0郾 020 mm)的预浸料制备复合材料薄壁管,实验测试了其在轴压下的局部 屈曲行为. 实验结果表明,随着铺层厚度减薄,实验采用的正交和均衡两种铺层方式的复合材料薄壁管局部屈曲载荷均随之 提高,而屈曲失效模式没有发生改变. 力学分析表明,铺层厚度减薄后,管壁弯曲刚度的改变和层间剪切应力分布对薄壁管局 部屈曲载荷提高有重要影响. 采用薄铺层制备复合材料薄壁结构件能够有效提高其局部屈曲能力. 关键词 复合材料; 薄铺层; 薄壁管; 压缩; 屈曲载荷 分类号 TB332 收稿日期: 2018鄄鄄03鄄鄄29 基金项目: 国家自然科学基金资助项目(11202231,U1537101,51403235) Buckling of composite cylindrical shells fabricated using thin鄄ply under axial compres鄄 sion HUANG Chun鄄fang, XIAO Jia鄄yu, HUANG Zhan鄄hong, ZHANG Jian鄄wei, JU Su, JIANG Da鄄zhi 苣 Department of Materials Science and Engineering, National University of Defense Technology, Changsha 410073, China 苣 Corresponding author,E鄄mail: jiangdz@ nudt. edu. cn ABSTRACT Carbon鄄fiber reinforced polymer (CFRP) composites possess high specific stiffness and strength and have been widely used as structural materials in aerospace and aircraft engineering. In many practical applications, such as wing skin, loading condition is a complexity of tension, bending, and torsion. Therefore, fabricating CFRP composite laminates of multiple鄄angled plies is necessary to achieve balanced mechanical properties and meet the loading requirements under different working conditions. However, considering the size and weight limitations, designing a quasi鄄isotropic laminate with standard ply thickness (0郾 125 mm) is difficult. The recently developed spread鄄tow technique has provided a promising strategy to fabricate composite laminates of thin and light plies for the produc鄄 tion of thinner and lighter laminates and structures and improvement of mechanical performance. Laminates fabricated using thin plies exhibit much higher strength in tension, compression, and impact as compared with standard鄄ply laminates because of the associated positive size effects. In the thin鄄walled structure, buckling stability is the primary factor determining the mechanical performance. In this study, composite cylindrical shells with different ply thickness (0郾 125, 0郾 055, and 0郾 020 mm) were fabricated via cross鄄ply and balanced stacking using the spread鄄tow technique, and their buckling behaviors under axial compression were studied. The experimen鄄 tal results show that with decreasing ply thickness, the critical buckling loads of composite cylindrical shells with cross鄄ply and bal鄄 anced stacking under axial compression increase, whereas the buckling mode of composite cylindrical shells remains constant. Mechan鄄 ical analysis indicates that the bending stiffness variation and interlaminar shear stress distribution play a key role in increasing the criti鄄 cal buckling load of the composite cylindrical shells, and the application of thin plies effectively improves the local buckling perform鄄 ance of the thin鄄walled composite structures. KEY WORDS composites; thin鄄ply; thin鄄walled cylindrical shell; compression; critical buckling load