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在对民用飞机机身门框开口角部进行裂纹扩展分析时,工程算法求解开口角部应力虽然计算结果可靠,但公式繁多,过程复杂。本文提出了针对粗网格有限元模型求解开口角部应力的有限元算法,并通过一个具体算例,证明了该算法计算的开口角部应力是正确的,且过程更简单。同时应用NASGRO软件进行了裂纹扩展分析,结果表该方法适用于工程分析。
In the civil aircraft fuselage frame corner crack crack growth analysis, engineering algorithm to solve the opening corner stress although the calculation results are reliable, but the formula is numerous and the process is complicated. In this paper, a finite element method is proposed for solving the stress in the corner of a coarse grid based on the finite element model. A numerical example is given to show that the calculated stress at the corner is correct and the process is simpler. At the same time, the application of NASGRO software crack propagation analysis, the results of this method is suitable for engineering analysis.