Method for repairing large-area damage of honeycomb sandwich structural part

A technology of honeycomb interlayer and structural parts, which is applied to household components, household appliances, weight reduction, etc., can solve the problem of small repair area, achieve the effect of avoiding secondary damage and reducing the risk of scrapping

Active Publication Date: 2021-05-04
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above repair methods can generally repair damage with a small area (generally no more than 400mm in diameter)

Method used

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  • Method for repairing large-area damage of honeycomb sandwich structural part
  • Method for repairing large-area damage of honeycomb sandwich structural part
  • Method for repairing large-area damage of honeycomb sandwich structural part

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0058] The tail beam of a certain type of helicopter has a honeycomb sandwich structure. The outer panel is made of aluminum alloy 2024T3 with a thickness of 0.4mm, the inner panel is made of aluminum alloy 5052H19 with a thickness of 0.1mm, and the sandwich is made of aramid paper honeycomb DHS251-142 with a thickness of 12mm. Due to a power failure, the plastic conduit inside the tail beam caught fire, and the tail beam suffered a large area of ​​ablation damage, with a damage area of ​​about 950×300mm. Heat up to 165°C with a hot-filler (hot-pressing blanket), evacuate (vacuum pump) and pressurize to 0.07Mpa, and then cure twice and splice two pieces of aramid paper honeycomb DHS251-142- with areas of 450×300mm and 500×300mm. 12. Aluminum alloy patch 5052H19 with a final curing area of ​​1050×400mm and a thickness of 0.4mm, such as Figure 5 shown.

[0059] Visible, this application:

[0060] 1) It breaks through the size limit of repairing damage by the conventional hone...

Embodiment 2

[0065] The floor of a certain type of UAV fuel tank is a honeycomb sandwich structure. The upper panel is made of aluminum alloy LY12 CZ with a thickness of 0.4mm, the lower panel is made of LY12 CZ with a thickness of 0.6mm, and the sandwich is made of aramid paper honeycomb NH-1-1.83 with a thickness of 12mm. Due to the excessive tightening torque of the bolts during equipment installation, the upper panel and the honeycomb collapsed in a large area, and the damage area was 750×350mm. Heat it to 110°C with a heat patching instrument (hot press blanket), and vacuumize it (vacuum pump) to pressurize it to 0.07Mpa , two pieces of aramid paper honeycomb NH-1-1.83-12 with an area of ​​350×350mm and 400×350mm were spliced ​​twice, and finally an aluminum alloy patch LY12 CZ with an area of ​​850×450mm was cured and the thickness was 0.4mm.

[0066] To sum up, the present invention provides a method for heating with a heat repair instrument (hot press blanket), vacuuming (vacuum pum...

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PUM

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Abstract

The invention provides a method for repairing large-area damage of a honeycomb sandwich structural part. The method comprises the steps of dividing a damage zone (9) into N parts according to the area of the damage zone (9); placing corresponding honeycombs at the N parts of the damage zone (9) in sequence, and curing the honeycombs according to a preset curing condition to form a spliced honeycomb; and sequentially placing a structural adhesive film (7) and a patch (8) on the upper surface of the spliced honeycomb from bottom to top, and curing the patch (8) according to a preset curing condition.

Description

technical field [0001] The invention relates to the field of aviation composite material thermal repair instrument and vacuum pump, in particular to a method for repairing large-area damage of a honeycomb sandwich structure. Background technique [0002] The honeycomb sandwich structure for aviation is usually composed of a high-strength, high-modulus upper panel (1) and a lower panel (2) sandwiching a thick, low-density original structure honeycomb (3), through a structural adhesive film (7) in a certain A monolithic structure formed by curing the bond under temperature and pressure conditions. The panel material includes aluminum alloy plate or composite material plate of carbon fiber, glass fiber and aramid fiber, and the honeycomb has aluminum alloy honeycomb or aramid paper honeycomb. During the production, use and maintenance of the honeycomb sandwich structure, one or more combinations of damage such as panel scratches, dents, honeycomb collapse, and slippage are pro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C73/10B29C73/12B29C73/34B29C73/24B29C73/32B29L31/60
CPCB29C73/10B29C73/12B29C73/34B29C73/245B29C73/32B29L2031/608Y02T50/40
Inventor 章强王珺孔凡路郝钢凝
Owner HARBIN
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