超大直径网格加筋筒壳快速屈曲分析方法  

A rapid buckling analysis method for large-scale grid-stiffened cylindrical shells

作　　者：王博[1] 田阔[1] 郑岩冰 郝鹏[1] 张可[1] 

机构地区：[1]大连理工大学工程力学系工业装备结构分析国家重点实验室,大连116024

出　　处：《航空学报》2017年第2期178-186,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家"973"计划(2014CB049000);国家自然科学基金(11372062;11402049);中国博士后科学基金(2015T80246);高等学校学科创新引智计划(B14013)~~

摘　　要：针对新一代重型运载火箭及大型飞机中存在的超大直径网格加筋壳结构,提出了一种快速屈曲分析方法。首先,基于渐进均匀化法的快速数值实现方法和瑞利-里兹法建立了快速屈曲分析框架,并通过与算例中等效刚度法屈曲载荷结果进行比较,验证了本文方法具有较高的预测精度。然后,对比了3种结构尺寸下网格加筋壳屈曲分析效率,结果表明本文方法不受结构尺寸影响,平均计算时间仅为6s,凸显了其用于超大直径结构分析的高效性。进而,基于本文方法对4种传统加筋构型及2种新型多级加筋构型进行屈曲载荷评估,其预测误差均在3.0%以内,表现出广泛的构型适用性。在此基础上,通过优化设计的方法对比了上述6种加筋构型的承载效率,优化结果表明本文提出的多级三角型加筋构型最具承载优势,相较于初始方案取得了82.2%的承载增幅,可作为一种新型超大直径网格加筋壳结构储备。A rapid buckling analysis method is proposed in this paper for large-scale grid-stiffened cylindrical shells used in heavy-lift launch vehicles and large aircrafts. The analysis framework is established by combining asymptotic homogenization method with Rayleigh-Ritz method. A comparison with the buckling load results by smeared stiffener method demonstrates the high prediction accuracy of the proposed method. Evaluation of the analysis efficiency of grid-stiffened cylindrical shells in three different model scales shows that the average computational time by rapid buckling analysis method is only 6 s and which is not inftuenced by the model scale, highlighting the efficiency of the proposed method for large-scale structures. The widespread grid applicability of this method for four traditional grid types and two complicated hierarchical grid types is vali- dated, and their prediction errors are all below 3.0 %. Optimizations are performed to compare the load-carrying efficiency of these six grid types. Optimization results illustrate that the proposed hierarchical triangle grid type achieves an increase of load-carrying efficiency by 82.2% than the initial design, and can be considered as an innovative grid type for large-scale grid-stiffened cylindrical shells.

关 键 词：网格加筋筒壳 渐进均匀化法 瑞利-里兹法 屈曲分析 优化设计 

分 类 号：V214.4[航空宇航科学与技术—航空宇航推进理论与工程] V414.4