Vibration testing device and vibration simulation method for aircraft airfoil structure

Abstract

The invention discloses a vibration test device and a vibration simulation method for an aircraft airfoil structure, the device comprises a U-shaped piece, a left transmission mechanism and a right transmission mechanism which are respectively arranged on two sides of the U-shaped piece, a vibration exciter for driving the U-shaped piece to vibrate is arranged on the U-shaped piece, and a dynamic force sensor is arranged on the outer side of the left side of the U-shaped piece. The left transmission mechanism comprises a pin, a lug plate and a left conical part, the right transmission mechanism comprises a threaded ejector rod and a right conical part, the left conical part and the right conical part are clamped on the two sides of the airfoil structure respectively, and the device can achieve vibration transmission, can also clamp airfoil structures of different thicknesses and cannot cause abrasion to the skin surface of the airfoil structure. The method comprises the following steps: 1, installing a vibration testing device; 2, vibration simulation test is carried out on the airfoil structure, the vibration simulation test is carried out on the airfoil structure of the airplane, the accuracy of vibration simulation is high, and the effect is good.

Description

technical field [0001] The invention belongs to the technical field of vibration testing of aircraft airfoil structures, and in particular relates to a vibration testing device and a vibration simulation method for aircraft airfoil structures. Background technique [0002] Airfoils refer to various aerodynamic surfaces of aircraft, including wings, tails, rudder surfaces and ailerons, etc. For the vibration test of the aircraft airfoil structure, the vibration loading method is mainly to force the airfoil structure through the excitation rod. Vibration, the exciter rod needs to be connected and tightened with the airfoil structure during the specific operation. The conventional bolt connection requires prefabricated bolt holes on the airfoil structure, but the bolt holes will destroy the integrity of the airfoil structure, so there are many existing connection methods. Adhesion and connection with vacuum suction cups are adopted. [0003] On the one hand, although the bondi...

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Problems solved by technology

[0003] On the one hand, although the bonding method will not destroy the integrity of the airfoil structure, it will leave glue marks on the surface of the airfoil structure, and the exciting rod is only connected to the skin of the airfoil structure during bonding. It is easy to cause the load-bearing structures such as the skin and the internal beams and ribs to pull off, resulting in unexpected damage to the airfoil structure; the connection method of the vacuum suction cup cannot withstand large tensile loads, and it is difficult to carry out large-scale vibration loading

[0004] On the other hand, when the airfoil structure is forced to vibrate directly through the excitation rod, the excitation rod is installed at the normal position of the airfoil structure. During the vibration loading process, the airfoil structure will be bent or twisted due to the load. The loading surface of connection, bonding or vacuum suction cup connection will bend or twist with the deformation of the airfoil structure, so that the excitation rod will be subjected to bending moment, which will not only easily cause damage to the excitation rod, but also affect the vibration loading accuracy

[0005] Therefore, there is a lack of a vibration test device and a vibration simulation method that can protect the device itself and ensure the accuracy of vibration loading, so as to facilitate the vibration test of the aircraft wing surface structure

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