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作为一种典型的航空航天结构,复合材料格栅圆柱筒的轴压稳定性决定了航天器结构的极限承载能力。现有的均匀化等效法和梁-壳有限元法模拟均存在一定的不足。考虑到肋条的局部应力和稳定性问题,将肋条等效为壳单元,提出了全壳有限元法。结合某型号飞行器复合材料格栅承力筒,分别采用这3种方法进行了轴压稳定性研究,同时设计了全尺寸轴压破坏试验。对比数值计算和试验结果得知两者的一致性较好,并且验证了该型号飞行器设计的合理性。均匀化等效法、梁-壳有限元法和全壳有限元法得到的结果与试验值的偏差分别为14.9%、9.5%和5.2%。全壳有限元法精度最高,并且能准确预测结构破坏位置,为同类结构的设计提供了参考。
As a typical aerospace structure, the axial compression stability of the composite grid cylindrical shell determines the ultimate bearing capacity of the spacecraft structure. The existing equalization method and beam-shell finite element method have some shortcomings. Considering the local stress and the stability of the rib, the whole shell finite element method is proposed by using the rib as the shell element. Combined with a certain type of aircraft composite grid grille, the three methods were respectively used to study the stability of the axial compression. At the same time, the full-scale axial compression failure test was designed. Comparing the numerical calculation and the test results, it is found that the consistency between the two is better and the rationality of the design of this model aircraft is verified. Homogenization equivalent method, beam-shell finite element method and the whole shell finite element method results and experimental values deviation of 14.9%, 9.5% and 5.2%. Full shell finite element method has the highest accuracy, and can accurately predict the location of structural damage, providing reference for the design of similar structures.