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机翼是飞行器结构中非常重要的组成部分。在工程实际中,由于各种因素的影响,经常会产生机翼结构的局部损伤。如果局部损伤没有被及时发现、诊断、并做出相应的补救措施,则很有可能会导致机翼严重破坏,并带来灾难性的后果。本文将模态曲率差方法应用于机翼结构故障诊断中,并用ANSYS有限元分析软件对一种机翼模型进行了模拟分析,模拟分析结果表明模态曲率差方法能对机翼结构故障进行精确定位,并能定性的判断出损伤程度。
The wing is a very important part of the aircraft’s structure. In engineering practice, due to various factors, local damage to the wing structure often occurs. If the local injury is not detected, diagnosed and remedial measures are taken, it is very likely that the wing will be severely damaged with disastrous consequences. In this paper, the modal curvature difference method is applied to the wing structure fault diagnosis, and a wing model is simulated by the ANSYS finite element analysis software. The simulation results show that the modal curvature difference method can accurately identify the wing structure faults Positioning, and can qualitatively determine the extent of injury.