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在民用飞机的设计阶段,需要对整机进行模态分析,而如何准确地得到机身、机翼等主要结构部件的刚度数据就显得尤为重要。工程上一般采用闭室结构的刚度计算方法计算各截面刚度,并在此基础上对某些特殊截面的刚度进行修正。为了能让修正后的结果更加接近实际情况,有必要对客舱窗、登机门以及货舱门等局部开口对截面刚度的影响进行研究。本文借助有限元软件PATRAN/NASTRAN,对机身有限元模型进行加载,根据变形结果反推截面的扭转刚度,并将此得到的扭转刚度与闭室结构的计算结果进行比较。通过比较发现,客舱窗对机身扭转刚度有较明显的影响,为工程计算中的修正提供了参考。
In the design stage of civil aircraft, it is necessary to carry out modal analysis of the complete machine, and how to accurately obtain the rigidity data of the main structural components such as the fuselage and the wings is particularly important. Engineering generally used closed-cell structure stiffness calculation method to calculate the stiffness of each section, and on this basis, the stiffness of some special sections to be amended. In order to make the corrected result closer to the actual situation, it is necessary to study the influence of the partial opening such as cabin window, boarding gate and cargo door on the section stiffness. In this paper, finite element software PATRAN / NASTRAN is used to load the finite element model of the fuselage, and the torsional stiffness of the cross section is deduced according to the deformation result. The calculated torsional stiffness obtained from this method is compared with that of the closed structure. By comparison, it is found that the cabin window has obvious influence on the torsional stiffness of the fuselage, which provides a reference for the correction in engineering calculation.