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作 者:史文锋 赵鑫 董晓阳 郭金海 章宇界 陈浩然[2] SHI Wenfeng;ZHAO Xin;DONG Xiaoyang;GUO Jinhai;ZHANG Yujie;CHEN Haoran(Shanghai Composite Technology Co.Ltd.,Shanghai 201112,China;Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
机构地区:[1]上海复合材料科技有限公司,上海201112 [2]南京航空航天大学材料科学与工程学院,江苏南京210016
出 处:《材料科学与工程学报》2020年第1期134-138,共5页Journal of Materials Science and Engineering
基 金:国家科技部863资助项目(2015AA03A201)
摘 要:基于有限元分析方法,对热压罐成型卫星贮箱安装板复合材料蒙皮热应力工艺设计方案进行仿真分析,研究了预浸料铺层区域、均压板结构、固化温度等工艺参数对蒙皮热应力的影响。结果表明,在均压板开孔结构不变,当预浸料铺层方法从整体铺层转变为开孔铺层,最大压缩热应力为-393.7MPa,增加了3.8%;最大拉伸热应力为87.9MPa,降低了62.9%。保持均压板开孔结构-预浸料开孔铺层不变,当固化最高温度从180℃降低到120℃,最大压缩热应力为-250.5MPa,最大拉伸热应力为55.9MPa,最大压缩应力和拉伸应力均降低了36.3%。降低固化温度显著降低热应力,并通过实验验证了分析结果。Thermal stress process design of composite skin for fuel tanks installation panel of satellite with autoclave curing process was simulated and analyzed based on finite element method.The influence of layup area with prepreg,structure of pressure equalizing plate and curing temperature were researched.The results show that the maximum compressive thermal stress is-393.7MPa(increase by 3.8%),and the maximum tensile thermal stress is 87.9MPa(decrease by 62.9%),when the prepreg ply method is changed from the overall ply to the open hole ply with the open hole structure of the pressure equalizing plate remaining unchanged.In addition,when the maximum curing temperature decreases from 180℃to 120℃with the opening structure of the pressure equalizing plate and the prepreg opening layer being unchanged,both the maximum compressive and tensile stress are reduced by 36.3%,the maximum compression thermal stress is-250.5MPa and the maximum tensile thermal stress is 55.9MPa.The thermal stress is significantly reduced by decreasing curing temperature,and the experimental results are in accordance with the analysis results by the verification of the sample.
分 类 号:TB332[一般工业技术—材料科学与工程]
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