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Anti-corrosion sealing method for internal cavity of covering cap

An internal cavity, anti-corrosion technology, used in aircraft accessories and other directions, can solve the problems of difficulty in maintaining sealing, easy accumulation of corrosive liquids, corrosion, etc. Effect

Active Publication Date: 2021-11-05
XIAN AIRCRAFT IND GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of this application is to provide an anti-corrosion sealing method inside the cover that can not only meet the long-term sealing requirements of the internal cavity of the cover, but also ensure the structural safety of the cover. , Caustic liquid is easy to accumulate in the cavity, causing corrosion problems, which seriously affects the technical problems of the safety of the mouth cover structure

Method used

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  • Anti-corrosion sealing method for internal cavity of covering cap
  • Anti-corrosion sealing method for internal cavity of covering cap
  • Anti-corrosion sealing method for internal cavity of covering cap

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Embodiment Construction

[0013] Referring to the accompanying drawings, an anti-corrosion sealing method for the inside of a cover of the present application includes an outer skin 1, an inner skin 2, a blind rivet 3, a sealant 4, a quick-release lock 5, a rotating bracket 6, a reinforced profile 7, an ordinary Rivet 8.

[0014] In practice, the inner skin 2 is provided with a ring-shaped reinforcing dimple 10 , and the outer skin 1 and the inner skin 2 are fixedly connected by rivets 8 on the outside of the ring-shaped reinforcing dimple 10 to form an integral structure of the cover body. In order to seal the inner cavity of the reinforcement nest and prevent rainwater from pouring into the corroded opening cover structure, the application provides a glue filling hole 9 on the top of the reinforcement nest 10 of the inner skin 2; inject liquid sealant into the reinforcement nest 10 through the glue filling hole 9; After injecting the liquid sealant, turn the posture of the cover body so that the liqu...

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Abstract

The invention provides an anti-corrosion sealing method for the inner cavity of a covering cap, the covering cap comprises an outer skin and an inner skin, the inner skin is provided with an annular reinforcing nest, the outer skin and the inner skin are fixedly connected into a covering cap body of an integrated structure through rivets on the outer side of the annular reinforcing nest, and a glue pouring hole is formed in the top of the reinforcing nest of the inner skin; liquid sealant is injected into the reinforcing nest through the sealant filling hole; the posture of the covering cap body is rotated to enable the liquid sealant to flow into the interlayer cavity between the outer skin and the inner skin to form a sealant layer; and after the liquid sealant is cured in the interlayer cavity of the outer skin and the inner skin to form the sealant layer, the sealant pouring hole is sealed.

Description

technical field [0001] The application relates to aircraft anticorrosion design, in particular to an anticorrosion sealing method for an inner cavity of a flap. Background technique [0002] The flap used on the aircraft is generally composed of an inner skin, an outer skin, a reinforced profile, a rotating bracket, and a quick release lock. The inner skin, outer skin and reinforced profiles are fixedly connected to form the cover body; the rotating bracket base is fixed on the edge of the cover body, and the swivel joint is fixed on the body; the quick release lock is fixed on the other edge of the cover body to fix the cover to the body superior. The existing technology and the existing problems are: the inner and outer skins are connected by rivets, which causes the cavity between the inner skin reinforcement socket and the inner surface of the outer skin to be unsealed, and water or other corrosive liquids are very easy to It penetrates into the cavity and accumulates ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/14
CPCB64C1/14
Inventor 李耀赵树军孟要伟
Owner XIAN AIRCRAFT IND GROUP
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