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A test method for the selection of torsion springs for aircraft

A torsion spring, torsion test technology, applied in the testing of mechanical components, the testing of machine/structural components, and the use of repetitive force/pulse force to test the strength of materials, etc., to achieve the effect of a reliable design method

Active Publication Date: 2020-12-18
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The torsion spring selection test method for aircraft of the present invention can solve or overcome at least one problem existing in the prior art

Method used

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  • A test method for the selection of torsion springs for aircraft
  • A test method for the selection of torsion springs for aircraft
  • A test method for the selection of torsion springs for aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] Step 1. Select the torsion spring with rectangular cross-section of test piece No. 1 and the circular cross-section torsion spring of test piece No. 2. The inner diameter, outer diameter, free height, and cross-sectional area of ​​the two selected test pieces are close to the same (due to actual manufacturing tolerances, they cannot be completely Consistent), the initial parameters measured in the table below.

[0036]

[0037] Step 2: Carry out the torsion test under 0 compression for the two test pieces, see figure 2 is the relationship curve between the torsion angle and torque of the two test pieces under 0 compression. It can be seen from the figure that the rectangular cross-section spring is better than the circular cross-section spring, so the rectangular cross-section spring with higher torsional stiffness is selected for step three, and the The torsion spring with rectangular cross-section of the selected test piece number 1 was subjected to torsion tests ...

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Abstract

The invention relates to a parameter selection test method of a torsional spring for an airplane. The parameter selection test method comprises the steps of 1, measuring initial parameters of at leasttwo different types of test pieces with same material; 2, performing torsional test on the two different types of test pieces under same compression quantity, and selecting the test piece with maximum torsional rigidity; 3, selecting a first test piece to perform torsional test under different compression quantities, and performing compression test on the first test piece at different torsional angles; 4, selecting compression quantity when the rigidity of the first test piece is approximate to stability, rotating the first test piece at a preset torsional angle, and repeating torsional testfor 1,000 times; 5, performing ultimate torque measurement on the first test piece to obtain maximum stress of the first test piece; and 6, selecting the final torsional spring with good torsional rigidity repeatability and maximum press value for parameter selection test according to the repeated torsional test.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, and in particular relates to a parameter selection test method for torsion springs used in aircraft structures. Background technique [0002] Rectangular cross-section torsion springs have never been used in existing aircraft, so a test method is needed to compare the performance of rectangular cross-section torsion springs and prototype cross-section torsion springs, and select materials with higher yield strength or newly developed materials for manufacturing and testing to verify Manufacture of spring wire material, process feasibility of spring production, correctness of spring stiffness calculation and stability of spring repeated loading. There is not a kind of torque and torsion angle relationship curve, force value and compression amount relationship curve of measuring different materials and different sizes of rectangular cross-section torsion springs and circular cross-section t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N3/26G01N3/32G01M13/00
CPCG01M13/00G01N3/26G01N3/32G01N2203/0005G01N2203/0021G01N2203/0085G01N2203/0288
Inventor 苑强波李志鹏吕伟
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA