本文選題：材料失效　切入點(diǎn)：結(jié)構(gòu)破壞　出處：《復(fù)合材料學(xué)報(bào)》2017年07期 　論文類型：期刊論文

【摘要】：針對(duì)復(fù)合材料層合加筋結(jié)構(gòu)的后屈曲問(wèn)題,開發(fā)出自編Fortran程序,并嵌入Patran進(jìn)行前后處理。采用該程序計(jì)算出線性屈曲模態(tài),將其作為后屈曲非線性計(jì)算的初始撓度;采用增量迭代技術(shù)、弧長(zhǎng)控制及能量收斂準(zhǔn)則求解非線性方程;最后引入復(fù)合材料Tsai-Hill失效準(zhǔn)則,對(duì)單元的損傷進(jìn)行判斷及剛度折減。采用復(fù)合材料加筋板的壓縮試驗(yàn)對(duì)該系統(tǒng)進(jìn)行初步驗(yàn)證。針對(duì)不同加載方式、選材及結(jié)構(gòu)型式的機(jī)翼盒段,利用該系統(tǒng)進(jìn)行后屈曲計(jì)算和分析,數(shù)值結(jié)果與試驗(yàn)數(shù)據(jù)吻合較好。
[Abstract]:Aiming at the post-buckling problem of composite laminated stiffened structures, a self-made Fortran program is developed and embedded in Patran to deal with the post-buckling problem. The linear buckling mode is calculated by the program, which is used as the initial deflection of nonlinear post-buckling calculation. The incremental iterative technique, arc length control and energy convergence criterion are used to solve nonlinear equations. Finally, the composite Tsai-Hill failure criterion is introduced. The damage of the element is judged and the stiffness is reduced. The compression test of composite stiffened plate is used to verify the system. The calculation and analysis of post-buckling by this system show that the numerical results are in good agreement with the experimental data.
【作者單位】： 西北工業(yè)大學(xué)航空學(xué)院;沈陽(yáng)飛機(jī)設(shè)計(jì)研究所;
【分類號(hào)】：TB33

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