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A Method of Improving Test Accuracy in Wing Body Joint Test

A technology of test accuracy and wing body, applied in the direction of using a stable bending force to test material strength, strength characteristics, instruments, etc., can solve the problems of complex test, uncertain authenticity of assessment, and need for additional fixtures, so as to improve the test results. Accuracy, ease of programming, and reduced cost of experimentation

Active Publication Date: 2021-07-16
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The purpose of the present invention is: to provide a method for improving the test accuracy of the wing-body joint test, and to study the method for improving the test accuracy from the angle of correcting the load value to reduce the additional bending moment caused by the deformation of the test piece, so as to solve the problem in the current method. Technical problems that require additional fixtures, complex tests, and uncertain factors for the authenticity of the assessment

Method used

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Embodiment Construction

[0033] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0034] One, the principle of the inventive method:

[0035] 1. The wing-body joint test consists of spar 1, fuselage frame 2, loading platform 3, loading actuator A4, and loading actuator B5, see figure 1 ;

[0036] 2. When the test piece is not deformed, the total force and bending moment of the two loading points A and B to the examination point C, see figure 2 :

[0037] Total force:

[0038] F=F A +F B

[0039] Bending moment:

[0040] m 0 =F A L A -F B L B

[0041] In the formula, L A is the distance from loading point A to examination point C, L B is the distance from loading point B to examination point C,

[0042] f A is the load at loading point A, F B is the load at loading point B;

[0043] 3. When the test piece is deformed, the total force and bending moment of loading point A and loading point B on examination point C, see ...

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Abstract

The invention belongs to the field of aeronautical structure test, and relates to a method for improving the test accuracy of a wing body joint test. In the method of the invention, the objective function is to reduce the additional bending moment to zero, and whether the relative error between the corrected and calculated bending moment under the deformed condition and the bending moment under the non-deformed condition meets the requirements as the iterative condition is used as the iterative condition. The load value of each loading point can reduce the additional bending moment caused by the deformation of the test piece, thereby improving the test accuracy. The method of the invention can effectively reduce the error caused by the test deformation, the assessment is more real and effective, the calculation process is simple, and the test cost can be effectively reduced.

Description

technical field [0001] The invention belongs to the field of aeronautical structure tests, and relates to a method for improving test accuracy in wing-body joint tests. Background technique [0002] In the wing-body joint test, due to the special structural form of the wing-body joint, the distance between the loading point and the examination point is relatively long. The large deformation leads to a large additional bending moment at the assessment point of the test piece, which makes the assessment of the test piece not realistic enough. Therefore, in the design of the test, the additional moment caused by the deformation is controlled within a small range by correcting the load value, so as to provide a method to improve the test accuracy in the wing-body joint test, so that the force state of the examination point is consistent with the The real structure remains the same. At present, no foreign public information on improving the test accuracy of wing-body joints has...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N3/20
CPCG01N3/20G01N2203/0023G01N2203/0075G01N2203/021
Inventor 彭航秦剑波王新波王锋
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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