Repairing method of airplane composite material foam interlayer structure

A composite material and sandwich structure technology, applied in the field of repair, can solve the problems of panel bulging stiffness, unevenness, increase in weight, etc., and achieve the effects of simple operation, uniform stiffness, and flexible application.

Pending Publication Date: 2017-05-10
R&D INST OF CHINA AVIATION IND GENERAL AIRCRAFT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The invention provides a repair method suitable for aircraft composite material foam sandwich structure, which is used to solve the problems of traditional repair methods such as large weight gain, padding easily causing panel swelling and uneven rigidity

Method used

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  • Repairing method of airplane composite material foam interlayer structure
  • Repairing method of airplane composite material foam interlayer structure
  • Repairing method of airplane composite material foam interlayer structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] Example 1 : Repair of non-penetrating damaged composite foam interlayers.

[0026] Non-penetrating damage means that the lower panel is not damaged, only the upper panel and the foam core are removed, such as figure 2 shown. For example, the excavated area of ​​the damaged area is a circular area with a diameter of 15 mm. Specific repairs include the following steps:

[0027] Step 1: Remove the foam and panel from the damaged part, and sand the panel;

[0028] Step 2: Cut and repair the foam, the foam is of the same model as the original structure, and the size is a cylindrical block with a diameter of 13mm, which is slightly smaller than the size of the excavated foam, which is easy to put into the damaged area;

[0029] Step 3: Grind the upper panel to form a certain bevel; the slope of the bevel is 1:20; the bevel is beneficial to the transmission of the load and to improving the flatness of the upper panel;

[0030] Step 4: Lay glue film on the upper surface of...

Embodiment 2

[0033] Example 2: Repair of penetrated composite foam sandwich structures

[0034] Penetrating damage refers to the damage that the entire sandwich (including the lower panel) is penetrated, and the upper and lower panels and the foam core need to be excavated. For example, the excavation area of ​​the damaged area is a circular area with a diameter of 20mm, such as image 3 shown. Specific repairs include the following steps:

[0035] Step 1: Remove the foam and panel from the damaged part, and sand the panel;

[0036] Step 2: Press the panel layup form to produce the patch (the patch material is the same as the original structure), and cut and repair the foam, the diameter of the foam is 18mm;

[0037] Step 3: Glue the patch to the bottom of the lower panel. The adhesive adopts the adhesive used in the body structure. The backing plate is used to support the patch during the gluing process. Bonding quality; the patch material is the same as the original structure;

[00...

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PUM

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Abstract

The invention relates to a repairing method of an airplane composite material foam interlayer structure. The repairing method comprises the following steps that 1, foam and a panel on the damaged portion are removed, and the panel is grinded; 2, a sticking patch is produced by laying a lower panel, and foam is cut and repaired; 3, the sticking patch is glued to the lower portion of the lower panel and supported through a backer board; 4, an upper panel is grinded to form an oblique angle of a certain degree; 5, a glue film is laid on the upper surface of the lower panel; and 6, repairing layers are laid and pasted to the upper panel, the boundary of the first layer needs to be larger than that of the damaged portion, and steps are reserved between every two adjacent repairing layers. The method is easy to implement and can be flexibly applied, the strength and rigidity of the airplane foam interlayer structure can restore, bumping is avoided, and rigidity is uniform.

Description

technical field [0001] The invention relates to a repair method, in particular to a repair method for an aircraft composite foam sandwich structure. Background technique [0002] During the use of the aircraft, various accidents will cause damage to the foam sandwich structure. Therefore, corresponding repairs are required to restore the structure to its original function and bearing capacity. The traditional repair method is to inject filler after digging out the damaged foam, which increases the weight greatly, and because the foam sandwich panel is generally thin, the filler easily leads to the bulging and uneven stiffness of the panel. SUMMARY OF THE INVENTION [0003] The present invention provides a repair method suitable for an aircraft composite foam sandwich structure, which is used to solve the problems of large weight gain, bulging of the panel and uneven rigidity caused by the filler in the traditional repair method. [0004] The technical scheme adopted in t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/40
Inventor 邵俊欣鲁礼菊李仁鹏刘海涛吴昊杨鉴威张凌虎
Owner R&D INST OF CHINA AVIATION IND GENERAL AIRCRAFT
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