【摘要】：針對(duì)復(fù)合材料真實(shí)結(jié)構(gòu)與有限元理論模型剛度偏差較大的問(wèn)題,提出了基于遺傳優(yōu)化算法進(jìn)行模型剛度修正的方法。以某復(fù)合材料彈翼為例,采用遺傳算法對(duì)模型鋪層角度和鋪層厚度進(jìn)行優(yōu)化,使模型彎曲剛度和扭轉(zhuǎn)剛度精度分別提升9.5%和8.4%,模型精度達(dá)到工程分析要求,驗(yàn)證了該方法的有效性和實(shí)用性。
[Abstract]:In order to solve the problem that the stiffness deviation between the real composite structure and the finite element model is large, a method of model stiffness modification based on genetic optimization algorithm is proposed. Taking a composite missile wing as an example, genetic algorithm is used to optimize the lamination angle and thickness of the model. The bending stiffness and torsional stiffness accuracy of the model are improved by 9.5% and 8.4% respectively, and the model precision meets the requirements of engineering analysis. The validity and practicability of the method are verified.
【作者單位】： 中國(guó)人民解放軍91550部隊(duì);北京機(jī)電工程研究所;
【分類(lèi)號(hào)】：TJ760;TP18

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