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随着现代科学技术的不断发展,振动和噪声的控制日益成为一个迫切的问题。尤其是空间技术的迅速发展,飞行器系统的功率和速度都有极大地提高,在飞行器结构中,由于各阶振型有时会被同时激发,从而产生强烈地宽带随机振动和噪声。上面的电子仪器设备,常常因为这些宽带随机振动和噪声的作用,将会同时激发各阶振型,形成许多共振峰,产生多峰共振。这些共振往往能够引起很大的破坏应力,使结构产生预期之外的损坏,引起仪器设备的失灵,甚致造成飞行失败。为了解决在宽带随机振动和噪声环境下多自由度系统的结构多峰共振响应,应用我们以往在实际工程设计中所采用的大阻尼隔振系统设计技术,虽然尚能满足要求,但是它存在的严重缺点是不能忽视的。例如:体积大、笨重、散热性能差等。因此一种从增加结构阻尼着手,采用结构阻尼减振技术控制振动的方法便提到日程上来了。
With the continuous development of modern science and technology, the control of vibration and noise is increasingly becoming an urgent issue. In particular, with the rapid development of space technology, both the power and the speed of the aircraft system have been greatly improved. In the aircraft structure, the vibration modes of all the stages are sometimes excited at the same time, resulting in intense broadband random vibration and noise. The above electronic equipment, often because of these broadband random vibration and noise effects, will simultaneously stimulate the various modes, forming a number of resonance peaks, resulting in multi-peak resonance. These resonances can often cause significant damage stresses, cause unexpected damage to the structure, cause equipment malfunctions and even cause flight failures. In order to solve the structural multi-peak resonance response of a multi-degree-of-freedom system in a wide-band random vibration and noise environment, the application of the design technology of the large damping vibration isolation system that we used in the actual engineering design can meet the requirements. However, Serious shortcomings can not be ignored. For example: bulky, bulky, poor thermal performance. Therefore, starting from increasing the structural damping, the method of using the structural damping vibration control vibration control will be mentioned on the agenda.