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Engineering Calculation Method of Assembly Stress

A technology of engineering calculation and assembly stress, applied in the direction of calculation, computer-aided design, design optimization/simulation, etc., can solve problems such as large errors, and achieve the effect of avoiding fatigue problems

Active Publication Date: 2019-02-22
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the relationship between assembly clearance and assembly stress, which involves boundary conditions and nonlinear relationship simulation, the current engineering algorithm and finite element algorithm have large errors

Method used

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  • Engineering Calculation Method of Assembly Stress
  • Engineering Calculation Method of Assembly Stress
  • Engineering Calculation Method of Assembly Stress

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Embodiment Construction

[0024] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

the application discloses an engineering Calculation Method of Assembly Stress which includes that following steps: obtaining a relationship between strain at a root chamfer of a first component and deflection of a free end; Carrying out test measurements on a plurality of groups of the first members having the same shape but having different numbers and positions of fixing bolts thereon, and obtaining an average test strain value of the first members in each group; Calculating the calculated strain values of the first member respectively under the condition that the distance from the root chamfer of the first member to the application point of the pre-tightening force takes different predetermined values; Comparing the test strain values in step 2 and step 3 with the calculated strain values, the predetermined value of the distance corresponding to the target result is selected to modify the relationship. The assembly stress engineering calculation method of the present application modifies the classical cantilever beam calculation method according to the test measurement results, so that the assembly stress of the assembly part can be quickly evaluated, the fatigue performance ofthe part can be analyzed, and the basis for other calculation analysis can be provided.

Description

technical field [0001] The application belongs to the field of assembly stress calculation, and in particular relates to an engineering calculation method of assembly stress. Background technique [0002] Because a certain structural part was found to be severely cracked and the number of cracks was large during the fault inspection stage of an overhauled aircraft; specifically, the structural part was similar to figure 1 The typical assembly structure shown may include two clamps 11 and a first member 12 that is fitted and connected, wherein the cross section of the first member 12 is approximately L-shaped. After preliminary analysis, it is mainly due to the assembly stress caused by the accumulation of tolerances in the assembly process of aircraft structural parts, resulting in stress corrosion cracking. The large number of cracks affects the structural integrity and brings safety hazards to the aircraft. [0003] Currently, stress corrosion cracking control measures i...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F2119/06G06F30/20
Inventor 李兆远李伟闫雨哲
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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