国产T800H复合材料加筋壁板压缩破坏试验研究及数值仿真分析  

Destruction Test and Numerical Simulation Analysis of Homegrown T800H Composite Stiffened Panel under Compression

作　　者：胡嘉桐 余明 HU Jiatong;YU Ming(AVIC the First Aircraft Institute,Xian 710089,China)

机构地区：[1]航空工业第一飞机设计研究院,西安710089

出　　处：《机械设计与研究》2022年第6期98-103,109,共7页Machine Design And Research

摘　　要：国内外飞机结构是朝着轻质、高效这一趋势发展的,复合材料加筋板因其优异的承载特性被广泛应用于飞机结构中。针对复合材料加筋板的后屈曲问题展开研究分析。通过典型国产T800H复合材料加筋板压缩破坏试验,得出其平均压缩屈曲载荷为192.5 kN、平均破坏载荷为426.5 kN,呈现出强大的后屈曲强度。因此充分利用加筋板的后屈曲特性,可以有效的提高材料利用效率。其次,采用了准静态法对加筋板从加载直至破坏这一过程进行非线性仿真分析,计算得出压缩屈曲载荷、破坏载荷与试验值误差分别为8.64%和7.57%,典型位置的应变—载荷仿真曲线、屈曲载荷、后屈曲模态与试验结果基本吻合,验证了准静态法的合理性和准确性。The development trend of aircraft structure is toward light weight and high efficiency at home and abroad.Composite stiffened panels are widely used in aircraft structural design because of their excellent load-bearing characteristics.In this paper,the post-buckling problem of composite stiffened panels is studied and analyzed.Destruction test on T800H composite stiffened panels under compression is carried out.The conclusion is that the average compressive buckling load is 192.5 kN,and the average failure load is 426.5 kN,showing the strong post-buckling strength of the stiffened panels.Therefore,making full use of the post-buckling characteristics of the stiffened panels can effectively improve the material utilization efficiency.The quasi-static method is used to conduct nonlinear simulation on the process from loading to failure of the stiffened panel.Compared with the experimental results,the error of buckling load and the error of failure load are 8.64%and 7.57%,respectively.The strain-load simulation curves,buckling load and post-buckling mode of the typical positions are in good agreement with the test results,which verifies the rationality and accuracy of the quasi-static method.

关 键 词：复合材料加筋板 屈曲载荷 破坏载荷 后屈曲 准静态法 

分 类 号：V224[航空宇航科学与技术—飞行器设计]