摘要
曲板的屈曲问题与材料的弹性模量和泊松比有关,对于机身蒙皮材料2060-T8E30,曲板临界剪切应力系数曲线的适用性有待研究。基于Abaqus的线性静力分析中的Buckle算法,以机身蒙皮材料2060-T8E30建立了多种构型曲板,对比有限元分析值和曲板临界剪切应力系数曲线,通过分析误差,得出结论:对于2060-T8E30材料,可以认为d/h=1.5的ks(曲板临界剪切应力系数)曲线相比有限元分析值偏高,误差不大于15%;d/h=2的ks曲线相比有限元分析值偏高,误差不大于20%;d/h=3.5的ks曲线相比有限元分析值偏高,误差不大于35%。在飞机机身结构常用的参数,即d/h=3.5,Z≤20的情况下,当Z<10时,ks曲线的适用性较好,误差不大于10%;当10<Z≤20时,ks曲线相比有限元分析值偏高,误差不大于20%。
The modulus and poisson＇ s ratio of material is bound up with problems of buckling in curved panels. The material named 2060-T8E30 is applied in skins of fuselage panels. Applicability of critical shear-stress coefficients curves of curved panels with the material 2060-T8E30 needs research. Based on Abaqus Buckle method in linear statics analysis, dozens types of curved panels with the material 2060-T8E30 were modeled. A comparison between numerical value of finite element analysis and critical shear-stress coefficients curves was conducted. By analyzing errors, the results were attained that for the material 2060-T8E30, ks （ critical shear-stress coefficients of curved panels） curve of d/h = 1.5 is relatively higher than ksyEA （ ks of finite element analysis） and the error is below 15%. ks curve of d/h =2 is relatively higher than ksyEA and the error is below 20%. ks curve of d/h =3.5 is relatively higher than ks^FEA and the error is below 35%. In case of normal parameters of fuselage structures of airplanes, as d/h = 3.5 and Z ≤20, ks curve has a good applicability when Z 〈 10 but is relatively higher than ks^FEA, with the error below 20% , when 10 〈Z≤20.
出处
《民用飞机设计与研究》
2017年第2期74-79,共6页
Civil Aircraft Design & Research
关键词
曲板
临界剪切应力系数曲线
有限元
适用性
curved panel
critical shear-stress coefficients curve
finite element
applicability
