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针对结构参数对高平尾布局尾翼振动横态局部化影响进行了研究。考虑到失调本身的不可预知性,在实际结构的基础上设计了质量正失调、质量负失调、刚度正失调、刚度负失调四种可能出现的失调尾翼模型。当失调量为±0.5时,通过模态分析法得到了翼梁和翼肋厚度不同的情况下结构的振动模态局部化度,并讨论了结构自身参数对不同失调原因引起的模态局部化的影响。结果表明:垂尾梁厚度的增加会提高振动模态局部化程度,而平尾梁厚度的影响与之相反,翼肋参数对模态局部化基本无影响;与前梁厚度相比,后梁厚度对结构振动模态局部化的影响较大;当垂尾后梁厚度增加到2.0mm时,0.5kε=-的失调模型的局部化度从0.342变为0.971,这种显著变化在结构设计中需引起注意;此外,结构参数对质量正失调和刚度负失调产生的模态局部化的影响强于质量负失调和刚度正失调。
The influence of structural parameters on the localization of the transverse vibration of the tail of the tail-tail structure is studied. Considering the unpredictability of the imbalance itself, four kinds of possible imbalanced tail models are designed based on the actual structure, including positive imbalance of mass, negative imbalance of mass, positive imbalance of stiffness and negative imbalance of stiffness. When the misalignment amount is ± 0.5, the modal localization degree of the structure with the different thickness of the spar and the rib is obtained by modal analysis, and the effect of the structure parameters on the modal localization caused by different offset causes is discussed . The results show that the increase of the thickness of vertical tail beam can increase the localization degree of vibration mode, while the effect of flat tail beam thickness is opposite. In contrast, the wing parameters have no effect on modal localization. Compared with the front beam thickness, When the thickness of vertical tail beam is increased to 2.0 mm, the localization degree of 0.5 k ε = - is changed from 0.342 to 0.971. This significant change should be paid attention to in structural design In addition, the influence of structural parameters on modal localization caused by positive and negative stiffness imbalances is stronger than negative and negative stiffness imbalances.