Aircraft panel vibration device under free boundary excited by aircraft sound waves and application method thereof

Abstract

The invention belongs to the vibration test technology field and particularly relates to an aircraft panel vibration device under the free boundary excited by aircraft sound waves and an application method thereof. The device comprises an auxiliary positioning device, an omnidirectional measuring device, an automatic adjusting suspension device, a movable sound wave excitation device and an auxiliary tool device, wherein the auxiliary tool device is used for supporting other four devices and providing the auxiliary function of a test device, the automatic adjusting suspension device is used for suspending aircraft panels before a vibration test and adjusting height of the aircraft panels, the movable sound wave excitation device is a vibration source of the vibration test device, the omnidirectional measuring device is used for measuring and collecting vibration data of the aircraft panels, and the auxiliary tool device ensures that the aircraft panels can return to a measuring originafter each vibration process. The device is suitable for measuring dynamic characteristics of various aircraft panels, the relevant vibration data of the aircraft panels can be directly obtained through aircraft sound wave excitation, the data can be then analyzed through computer software, the device is simple and efficient, and the data is accurate.

Description

technical field [0001] The invention belongs to the technical field of vibration testing, and in particular relates to a plane acoustic wave excitation-based vibration device for an aircraft wall panel under a free boundary and a use method thereof. Background technique [0002] With the continuous improvement of aircraft performance, the impact of the strong noise environment of the aircraft on its structure is becoming more and more serious. Acoustic vibration leads to fatigue damage of the aircraft structure, which seriously threatens the safety of the aircraft. Therefore, it is an important subject of aircraft design to study the mechanism of acoustic fatigue and the effective control method to prevent acoustic fatigue damage. The factors affecting the acoustic fatigue damage of aircraft structure are complex, and it is difficult to predict the anti-acoustic fatigue life of the structure correctly by pure theoretical calculation methods. [0003] The aircraft panel is o...

AI Technical Summary

Problems solved by technology

On the one hand, the vibration exciter will be affected by the additional mass caused by the force sensor of the front-end ejector rod. On the other hand, the hammer also has the phenomenon that the excitation force is difficult to control and "double-click", and it is easy to cause excessive local force and structural deformation. , thus affecting the test accuracy

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