摘要
大展弦比复合材料机翼结构的稳定性问题突出,需对结构进行屈曲和后屈曲分析。由于后屈曲分析需要考虑几何非线性对结构的影响,计算量大、收敛难,因此在飞机结构工程应用中受到限制。文中介绍了Msc.Marc所采用的两种计算非线性屈曲方法的计算原理,并分别运用这两种方法对机翼模型进行后屈曲分析,最后将两种计算结果作比较,得到的结果对类似的分析有一定的指导意义。以某机翼为实例的计算表明,本分析方法在今后飞机结构设计中有一定的应用价值。
The finite element analysis in buckling and post-buckling is required adopted because of the high aspect ratio wing structures＇ stability problem. Post-buckling analysis calculation will be very complex on account of material and geometrical nonlinear factors, so it is restricted on the large and complex structure due to the spending and convergence. Two calculation principles are introduced for calculating nonlinear buckling adopted in the Msc/Mare and Post-buckling analysis is made for wing model by Msc/Mare. Making simple comparison between the analysis results, from which conclusions gained, is helpful for similar analysis. The calculation of the wing implies that the method of the analysis is valuable in the aircraft structures design in the future.
出处
《飞机设计》
2008年第1期28-32,共5页
Aircraft Design
关键词
大展弦比
复合材料
后屈曲
几何非线性
high aspect ratio
composite material
post-buckling
geometrical nonlinear
