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Large plane panel deformation control and restoration method based on local rigidity enhancement

A technology of aircraft siding and reset method, which is applied in aircraft assembly, aircraft parts, ground installations, etc., and can solve problems such as large stress, low precision, and impact on aircraft fatigue strength and service life

Inactive Publication Date: 2012-10-24
ZHEJIANG UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the domestic aircraft manufacturing industry is developing vigorously in the assembly of fuselage panels and gradually adopting digital assembly technology to replace the original forced assembly tools such as bandages. Low, often resulting in forced extrusion assembly, resulting in greater stress, thus affecting the fatigue strength and service life of the aircraft

Method used

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  • Large plane panel deformation control and restoration method based on local rigidity enhancement
  • Large plane panel deformation control and restoration method based on local rigidity enhancement
  • Large plane panel deformation control and restoration method based on local rigidity enhancement

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Effect test

Embodiment Construction

[0059] Such as figure 1 , figure 2 As shown, the large aircraft panel 1 is mainly composed of parts such as a bulkhead 2, a skin 3, and a stringer 4.

[0060] Such as image 3 As shown, the numerical control positioner is mainly composed of X-axis 6 , Y-axis 7 , Z-axis 8 and other parts, and each axis can move independently, and can be manipulated and controlled by the control system computer 27 .

[0061] Such as Figure 4 As shown, the sub-figures A, B, and C use thick solid lines to represent the deformation of the large aircraft panel 1, where A is the deformation of the large aircraft panel 1 before the process joint 9 is installed, and the deformation is relatively large and irregular ; B is that after the process joint 9 is installed on the wall 1 of the large aircraft, its deformation has been effectively suppressed, and it is relatively regular. 1, and through the coordinated movement of the numerical control locator group 11, the deformed reset is realized.

[...

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Abstract

The invention discloses a large plane panel deformation control and restoration method based on local rigidity enhancement. The method includes the following steps that: (1) process connectors are mounted to enhance the local rigidity of a large plane panel and inhibit the deformation of the large plane panel; (2) process ball head centre measurement data are recorded in a database computer, and the large plane panel is then taken down and hoisted away; (3) each axis of numerically controlled positioners and settling devices are controlled to settle and support the large plane panel, and the current positions of the numerically controlled positioners are uploaded to an integrated management system computer; (4) according to the restoration data sent by the integrated management system computer, a control system computer instructs the numerically controlled positioners to move to restore the large plane panel. The method has the following advantages that: (1) by mounting the process connectors, the local rigidity of the large plane panel is enhanced and the deformation of the large plane panel is inhibited; (2) the numerically controlled positioners move to restore the large plane panel; (3) toolings become equipment, and the system is easy and reliable to operate; (4) the positioning efficiency is increased by multiple times.

Description

technical field [0001] The invention relates to a deformation control and reset method of a large aircraft wall plate based on local rigidity strengthening. Background technique [0002] Digital assembly is an inevitable development trend of aircraft assembly, and digital assembly of large aircraft panels (1) is an important part of it. Large aircraft are generally assembled from several fuselage sections, and the fuselage sections are spliced ​​from several panels. During the digital assembly process of the fuselage section, it was found that the actual shape of the large aircraft panel (1) was quite different from the theoretical model, which often made it difficult for the digital tooling to connect the panel into an ideal fuselage section according to the data of the measurement points , Some parts even cannot be docked at all. In addition, the large aircraft panel (1) has a complex structure, low overall rigidity, numerous coordination relationships, and great influen...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64F5/10
Inventor 柯映林严伟苗毕运波梁青霄何胜强杨国荣
Owner ZHEJIANG UNIV
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