Asymmetric load buffer and parameter determination method

A buffer and asymmetric technology, applied in the field of aircraft strength test loading, can solve problems such as overrun stop, feedback and command error, poor loading response characteristics, etc., to avoid commutation impact, reduce stiffness, and ensure loading accuracy.

Active Publication Date: 2021-03-12
HARBIN
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  • Application Information

AI Technical Summary

Problems solved by technology

[0002] When performing fatigue tests on aircraft components, it is necessary to apply tensile and compressive loads to the test piece through actuators, loading mechanisms, sensors, etc. Unstable, frequent over-limit stops
The reason for the above phenomenon is that there is a hysteresis recovery zone in the servo loading system when the zero-point commutation occurs, and such a small load is just near the hysteresis recovery zone, which causes the response speed of the servo control system to slow down, and errors occur in feedback and commands. When the error exceeds When the error limit is set, the test will automatically stop to ensure the accuracy of the test load

Method used

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  • Asymmetric load buffer and parameter determination method

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Embodiment 1

[0051] The actuator test loading stroke should be adjustable between 5mm-10mm, and the maximum tensile load is F 拉 =1530N, the maximum pressure load is F 压 =4630N. Determine the parameters of the spring according to the tension and compression load and the required deformation (see Table 1). During use, it is required that there should be no gap between the large spring and the small spring to ensure the continuity of the feedback load curve.

[0052] Table 1 Spring parameter table

[0053]

[0054] According to F 压 =4630N, when the large spring is compressed, the small spring is fully extended, and the compression amount of the large spring is f n =F 压 / F'=4630N / 433N / mm=10.7mm, when the spring is installed, the total compression of the two springs is 10.7mm. When the two springs are assembled and press against each other:

[0055] f 小 ’ X1=F 大 '·X2 and X1+X2=10.7

[0056] where F 小 '=178N / mm, F 大 ’=433N / mm

[0057] Obtain: X1=7.6mm, X2=3.1mm, that is, the compr...

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Abstract

The invention belongs to the technical field of aircraft strength test loading, and discloses an asymmetric load buffer and a parameter determination method, and the asymmetric load buffer comprises aforce transmission end cover, a locking large nut, an outer cylinder, a locking small nut, a sliding bearing bracket, a locking small nut, a sliding bearing, a large spring, a small spring, a loadingmandrel, a sliding bearing, a sliding bearing bracket and an end cover. Through the application of the invention, the rigidity of the loading system can be reduced, a lag recovery area of the servo loading system is avoided, the loading command curve and the feedback command curve are highly superposed, the loading precision is ensured, and meanwhile, the reversing impact on the loading of a testpiece is avoided. The stroke requirements of actuators of different load levels can be met by adjusting the compression amount of the spring.

Description

technical field [0001] The invention belongs to the technical field of aircraft strength test loading, in particular to an asymmetric load buffer and a parameter determination method. Background technique [0002] When performing fatigue tests on aircraft components, it is necessary to apply tensile and compressive loads to the test piece through actuators, loading mechanisms, sensors, etc. Unstable and frequent overrun stops. The reason for the above phenomenon is that there is a hysteresis recovery zone in the servo loading system when the zero-point commutation occurs, and such a small load is just near the hysteresis recovery zone, which causes the response speed of the servo control system to slow down, and errors occur in feedback and commands. When the error exceeds When the error limit is set, the test will automatically stop to ensure the accuracy of the test load. The above problems are also common problems in hydraulic servo loading control. To solve this probl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00
CPCG01M13/00
Inventor 沈铁军李黎明佟强杨库于国庆王久龙孙玉峰张健峰赵聪聪蔡明程孙天航
Owner HARBIN
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