基于 Abaqus 的太阳能飞机翼肋撑杆分布快速设计

太阳能飞机对于质量十分敏感,在结构设计上力求达到同等质量下承载能力最强,给出的方法可对多种外形的翼肋进行撑杆分布位置的初步优化设计分析,以达到减重增效的目的。以太阳能飞机翼肋外形为基础模型,给出了一种基于 Abaqus Toca模块的翼肋撑杆分布位置优化方法,这种方法以渐进结构优化方法为理论基础,将结构中无效或低效的单元在分析计算中逐渐去除,剩余结构将渐趋优化,显著提高翼肋单位质量承载能力。给出的优化算例中,用相同质量材料设计出的翼肋,在相同载荷工况下,最大腹板应力及撑杆应力分别为优化前的 90.4%及 68.6%,优化后的撑杆分布使翼肋整体承载能力都有提升,其中撑杆承载能力提升较大,且应力在各撑杆分布更为接近。

Rapid Design of Solar Aircraft Wing Rib Struts Distribution Based on Abaqus

Solar aircraft is very sensitive to weight, and the structural design strives to achieve thestrongest bearing capacity under the same mass. The method given in this paper can conduct prelimi.nary optimal design analysis on the distribution position of the struts for various shapes of wing ribs.so as to achieve weight reduction and increase efficiency. In this paper, based on the shape of the so-lar aircraft wing rib, a method for optimizing the distribution position of the rib struts using theAbaqus ''Toca module is given. This method is theoretically based on the Evolutionary Structural Opti-mization method ( ESO) ,that is ,the ineffective or inefficient elements in the structure are graduallyremoved during the analysis calculation , and the remaining structure will be gradually optimized,which will significantly improve the bearing capacity of the rib per unit mass. In the optimization cal-culation example given in this paper ,the ribs designed with the equal mass ,under the same load con-ditions ,the maximum web stress and strut stress are 90.4% and 68.6% of those before optimization. The optimized strut distribution improves the overall bearing capacity of the ribs, in which thebearing capacity of the struts is greatly improved,and the stress distribution in each strut is closer.