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Push-back type vibration excitation control system and control method in aircraft vibration fatigue test

A vibration fatigue and vibration excitation technology, applied in the field of aircraft testing, can solve the problems of restricting the effective conduct of aircraft vibration fatigue testing tests, inability to load vibration loads, and fixed connections, and achieve reasonable structural design, improved stability, and uniform application effects.

Active Publication Date: 2022-07-05
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Vibration fatigue is one of the main problems of failure of aeronautical structural parts, so it is necessary to carry out vibration fatigue test on structural parts. During aircraft vibration fatigue test, structural parts are generally fixed on the foundation through the root, in order to effectively control the top of structural parts. To apply the expected vibration load, the vibration excitation of large aeronautical structural parts is usually loaded by response control method; considering the requirements of protecting structural parts, the vibration exciter and the test piece cannot be fixedly connected by bolts or other methods, and the vibration excitation loading needs to use The flexible connection method is movably connected with the test piece; however, for the large-load vibration fatigue test, the flexible connection method has the problem that it is easy to fall off when subjected to a large tensile load, resulting in the failure of the vibration load to be loaded, which limits the scope of the aircraft vibration fatigue test. carry out effectively

Method used

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  • Push-back type vibration excitation control system and control method in aircraft vibration fatigue test
  • Push-back type vibration excitation control system and control method in aircraft vibration fatigue test
  • Push-back type vibration excitation control system and control method in aircraft vibration fatigue test

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] like figure 2 , 3 The push-back vibration excitation control system in the aircraft vibration fatigue test shown in , 6 includes a base 1, a vibration exciter 2, a flexible connector 3, a fixed component 4, a test piece 5 and a PLC controller; the vibration exciter 2 is provided with Two, the two vibration exciters 2 are respectively arranged on both sides of the upper end face of the base 1, and the opposite sides of the two vibration exciters 2 are provided with vibration excitation rods 20, and the two vibration excitation rods 20 are sleeved with vibration excitation rods 20. plate 21;

[0042] like figure 2 , 3 , 9, there are two flexible connectors 3, the flexible connector 3 includes a docking rod 30, a flexible disk 31 and a vacuum suction cup 32; the two flexible disks 31 are respectively sleeved on the two docking rods 30 in one-to-one correspondence, Six push rods 311 sleeved with damping springs 310 are slidably clamped in the circumferential direction...

Embodiment 2

[0047] What this embodiment records is the control method of the push-back vibration excitation control system in the aircraft vibration fatigue test of embodiment 1, comprising the following steps:

[0048] S1. Place the test piece 5 on the positioning seat 42. The positioning seat 42 moves downward under the pressure of the test piece 5 and then compresses the buffer spring 420; during the movement of the positioning seat 42, the two movable splints are pulled by the two pulling plates 410. 41 are close to each other, and the test piece 5 is fixed by the clamping rollers 411 on the two movable splints 41;

[0049] S2. Rotate the two rotation adjustment seats 334 respectively, and use the adjustment gear 335 to drive the ring gear 333 to rotate, so that the adjustment part 330 drives the screw rod 332 to rotate, thereby adjusting the distance between the two vacuum suction cups 32 and the test piece 5, Make the two vacuum suction cups 32 close to the two side walls of the tes...

Embodiment 3

[0052] This embodiment differs from Embodiment 1 in that:

[0053] like figure 2 , 4 As shown, a lift seat 10 is slidably connected inside the base 1, the top of the lift seat 10 penetrates the base 1, the vibration exciter 2 and the fixing component 4 are both arranged on the lift seat 10, and the left and right ends of the lift seat 10 are provided with through the base 1 The support column 100 of the base 1 is provided with a chute 101 for providing a moving space for the support column 100 and a hydraulic cylinder 11 for providing power for the support column 100 on both the left and right side arms of the base 1;

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Abstract

The invention discloses a push-back type vibration excitation control system and method in an aircraft vibration fatigue test, and belongs to the technical field of aircraft testing. The two vibration exciters are arranged on the base and provided with vibration excitation rods respectively, the flexible connecting pieces are movably connected with the two vibration exciters respectively, the fixing assembly is arranged in the middle of the base, the test piece is arranged between the two flexible connecting pieces and connected with the fixing assembly in a clamped mode, and the PLC is electrically connected with the vibration exciters. The control system is reasonable in structural design, vibration excitation can be alternately loaded on the left side and the right side of the test piece, the purpose of applying vibration excitation is achieved while the test piece is protected, and the control system is suitable for application and popularization.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to a push-back vibration excitation control system and a control method in aircraft vibration fatigue testing. Background technique [0002] During use, the aircraft will be subjected to repeated loads caused by rollout, gust, maneuver, landing impact and cabin pressurization. Due to these repeated loads, the local stress concentration areas and defective areas of the aircraft structure Fatigue cracks caused by alternating stress will occur in other parts, and the continuous action of alternating stress will cause fatigue cracks to continue to expand and lead to fatigue damage, which is often referred to as the fatigue of aircraft structures. [0003] The vibration fatigue problem is one of the main problems of the failure of aeronautical structural parts, so it is necessary to conduct a vibration fatigue test on the structural parts. During the aircraft vibration fatigue t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M7/02B64F5/60
CPCG01M7/022G01M7/027B64F5/60
Inventor 代承霖李凯翔黄文超刘小川何石
Owner CHINA AIRPLANT STRENGTH RES INST