Study on Vibration Characteristics of Composite Laminated Plate with Coupled Concentrated Mass

本文针对新能源飞机复合材料层合板结构在耦合附加集中质量下的刚柔耦合振动问题开展研究。在薄板假设基础上，推导耦合附加集中质量的复合材料层合板的动力学控制方程。通过对比有无耦合附加集中质量的复合材料层合板的固有频率和模态振型，分析了附加集中质量对复合材料层合板振动特性的影响。结果表明，附加集中质量显著改变了复合材料层合板的部分振动特性。本研究为新能源飞机的复合材料层合板结构设计提供理论支撑。The rigid-flexible coupled vibration problem of new energy aircraft composite composited plate structure under coupled additional concentrated mass is studied. Based on the thin plate hypothesis, the dynamic governing equation of coupled additional concentrated mass composite laminated plate (CLPCM) is derived. By comparing the natural frequencies and mode shapes of the composite laminated plates with or without coupled additional concentrated mass, the influence of additional concentrated mass on the vibration characteristics of the composite laminated plate is analyzed. The results show that the addition of concentrated mass significantly changes the partial vibration characteristics of composite laminated plates. This study provides theoretical support for the design of composite laminate structures for new energy aircraft.