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采用基于水溶性型芯的RTM成型技术制备了整体化的复合材料翼盒,并对翼盒进行了自由振动模态试验;采用三维壳单元,建立了翼盒固有模态及稳定性有限元分析模型,该模型分析的翼盒固有模态与试验结果吻合很好,验证了有限元模型的有效性;为研究翼盒固有模态及稳定性的铺层效应,采用该模型分析计算了4种铺层方案的翼盒的固有模态及稳定性。研究结果表明:对称铺层蒙皮有利于提高翼盒轴向压缩与轴向扭转屈曲载荷及固有频率,而不利于面外弯曲和弯扭组合情况;腹板减薄和增加腹板45°铺层均不利于提高,甚至会大幅度降低屈曲载荷及固有频率,弯扭组合加载最容易导致失稳。
The integrated composite wing box was prepared by RTM molding technology based on water-soluble core. The wing box was subjected to free vibration mode test. The three-dimensional shell element was used to establish the finite element analysis of wing box inherent mode and stability Model. The natural mode of the wing box analyzed by the model is in good agreement with the experimental results, which verifies the validity of the finite element model. In order to study the ply effect of the natural modes and stability of the wing box, four models Natural modes and stability of the wing box of the ply scheme. The results show that the asymmetrical skin layer can improve the axial compression and axial torsional buckling load and the natural frequency of the wing box, which is not conducive to the combination of out-of-plane bending and bending-torsion. The web thinning and increasing the web 45 ° shop Layer are not conducive to improve, or even significantly reduce the buckling load and natural frequency, the combination of bending and torsion most likely to lead to instability.