本文選題：材料失效　切入點：結構破壞　出處：《復合材料學報》2017年07期 　論文類型：期刊論文

【摘要】：針對復合材料層合加筋結構的后屈曲問題,開發(fā)出自編Fortran程序,并嵌入Patran進行前后處理。采用該程序計算出線性屈曲模態(tài),將其作為后屈曲非線性計算的初始撓度;采用增量迭代技術、弧長控制及能量收斂準則求解非線性方程;最后引入復合材料Tsai-Hill失效準則,對單元的損傷進行判斷及剛度折減。采用復合材料加筋板的壓縮試驗對該系統(tǒng)進行初步驗證。針對不同加載方式、選材及結構型式的機翼盒段,利用該系統(tǒng)進行后屈曲計算和分析,數值結果與試驗數據吻合較好。
[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)大學航空學院;沈陽飛機設計研究所;
【分類號】：TB33

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本文編號：1651315