CN114294308B - Glue overflow control method for aviation structure glue joint piece - Google Patents
Glue overflow control method for aviation structure glue joint piece Download PDFInfo
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- CN114294308B CN114294308B CN202111680638.0A CN202111680638A CN114294308B CN 114294308 B CN114294308 B CN 114294308B CN 202111680638 A CN202111680638 A CN 202111680638A CN 114294308 B CN114294308 B CN 114294308B
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Abstract
The invention belongs to the technical field of aviation structure gluing, and particularly relates to a glue overflow control method for aviation structure gluing pieces. The aviation structural component comprises an outer skin, a honeycomb core, an inner skin and an edge sealing piece; the outer skin and the inner skin are respectively coated with glue solution, the upper part of the honeycomb core is bonded with the inner skin, the lower part of the honeycomb core is bonded with the outer skin, the side edges of the honeycomb core are sealed and bonded with the outer skin and the inner skin through the edge sealing piece, and the whole aviation structural part is formed by adopting a vacuum bag through hot press; the glue overflow control method comprises the following steps: before hot press molding of a vacuum bag, arranging an isolation structure on the surface of the bonding transition position of the inner skin and the edge sealing piece and the surface of the bonding transition position of the outer skin and the edge sealing piece; after hot press forming, the isolation structure is removed. The manufacturing level of the aviation structure gluing component can be improved, and the surface quality and the manufacturing efficiency of the structure gluing component are improved.
Description
Technical Field
The invention belongs to the technical field of aviation structure gluing, and particularly relates to a glue overflow control method for aviation structure gluing pieces.
Background
In the curing process of the aviation structure cementing piece, the temperature is increased to enable the adhesive to be changed into adhesive liquid in a viscous state, the adhesive liquid is extruded along the material under the action of pressure, the extruded adhesive liquid is subjected to the constant temperature and temperature reduction process, and the extruded adhesive liquid is changed into solid adhesive tumors again to be remained at the joint of the edge of the aviation structure cementing piece and the die.
The aviation structure cementing piece is characterized in that the 'glue' is used, so that the 'glue overflow problem' is necessarily existed in the curing process, and the glue overflow is the normal curing phenomenon of the structure cementing piece. A small amount of glue overflow is generally acceptable when the appearance and lap joint assembly of the surface of the aviation structure glue joint piece are not affected; and a large amount of or ultra-thick overflow glue in the lap joint area needs to be subjected to additional processing treatment.
The traditional repair processing mode of a large amount of glue overflows of the aviation structure glue joint piece is as follows: and (5) polishing the surplus glue nubs by using sand paper, and cleaning the surface by using butanone.
For the large-amount and ultra-thick (more than 0.3 mm) hard glue tumors, the traditional repair processing method is long in time, and the problems that the aviation structure glue joint part is easily scratched and knocked in the cleaning process, and the part surface oxidation protection layer is excessively polished and the like are easily caused. Therefore, the method cannot thoroughly solve the problem that a large amount of glue overflows from the structural adhesive joint part and the quality requirement of the aviation structural adhesive joint part is not met.
The aviation structure cementing piece is formed by firstly positioning a metal skin with adhesive paved on a forming tool; then sequentially positioning and mounting honeycomb core materials and angle edge sealing pieces paved with adhesives; after the assembly according to the drawing is completed, paving a breathable material on the surface of the air structure cementing piece and preparing a vacuum bag by a vacuum film; sending the packaged aviation structure cementing piece and the tooling into an autoclave, and completing cementing molding at high temperature and high pressure; cooling down to room temperature and reducing pressure to standard atmospheric pressure, discharging the tank, and finally opening the die and cleaning to finish the preparation.
The structure drawing of the aviation structure cementing part of a certain aircraft structure cementing part is shown in figure 1, and the aviation structure cementing part is formed by adhering a metal outer skin 1, an angled honeycomb core material 2, an angled metal edge sealing part 3 and a metal inner skin 4 into a closed sandwich structure by adhesive. The angle edge sealing piece is formed by bonding adhesive between the two pieces after being overlapped with the inner skin, and the adhesive is extruded under the action of pressure in the process of resolidification and forming of the adhesive due to the height difference between the two pieces after being overlapped, and a part of the adhesive is cooled along the inner skin after flowing, so that the A-type adhesive tumor in the figure 1 is formed; the other part flows to the upper part of the angle sealing piece under the action of the surface ventilation material to form the B-type glue tumor in the figure 1. The adhesive between the angle edge sealing piece and the outer skin is extruded under the pressure action in the curing process, and a part of the adhesive forms a C-shaped glue tumor in the figure 1 along the outside of the component; the other part flows to the upper surface of the lower part of the angle sealing piece under the action of the surface ventilation material to form the D-shaped rubber tumor in the figure 1.
Technical difficulty of aeronautical structure cementing piece rubberizing tumor problem:
1. the adhesive quality requirement should be met. Therefore, the glue overflow is necessary and should be uniform.
2. The assembly area of the aviation structure cementing piece (such as the right side area of the class A cementing piece) should not have glue overflow. Therefore, the area of the glue overflow area must be controlled.
3. The non-assembly area (such as the class A glue joint area) of the aviation structure glue joint piece can be provided with glue overflow, but the surface quality of the aviation structure glue joint piece is not affected by attractive appearance. Therefore, the surface shape of the flash must be controlled.
4. The painting and surface quality of the aerospace structural adhesive (such as B, D type glue puddle area) are not affected, so B, D type glue puddles must be removed or not produced.
5. Glue tumor (C type glue tumor area) at the joint of the aviation structure glue joint part and the tool affects the die opening of the aviation structure glue joint part, and the problems of deformation, surface scratch and the like of the aviation structure glue joint part are easily caused. Therefore, the smoothness of the mold opening of the air structure adhesive joint piece must be ensured.
Disclosure of Invention
The purpose of the invention is that: the invention provides a glue overflow control method for an aviation structure glue joint piece, which aims at the problems that after a carrier-free adhesive is added to a certain type of airplane structure glue joint piece, when the aviation structure glue joint piece is molded, a large number of hard A, B, C, D glue tumors are formed by overflowing and solidifying the surface of the adhesive aviation structure glue joint piece, so that the aviation structure glue joint piece is difficult to open, poor in appearance quality and low in glue tumor cleaning efficiency, and hidden quality risks such as gouging and scratch exist. The invention can improve the manufacturing level of the aviation structure cementing component and improve the surface quality and the manufacturing efficiency of the structure cementing component.
The technical scheme of the invention is as follows: the aviation structural component comprises an outer skin, a honeycomb core, an inner skin and an edge sealing piece; the outer skin and the inner skin are respectively coated with an adhesive film, the upper part of the honeycomb core is adhered to the inner skin, the lower part of the honeycomb core is adhered to the outer skin, the side edges of the honeycomb core are sealed and adhered to the outer skin and the inner skin through the edge sealing piece, and the whole aviation structural part is formed by adopting a vacuum bag through hot press; the glue overflow control method comprises the following steps: before hot press molding of a vacuum bag, arranging an isolation structure on the surface of the bonding transition position of the inner skin and the edge sealing piece and the surface of the bonding transition position of the outer skin and the edge sealing piece; after hot press forming, the isolation structure is removed.
In one possible embodiment, the bonding transition position of the inner skin and the edge sealing member comprises an inner skin upper surface and an edge sealing member inner skin side upper surface; the isolation structure arranged on the upper surface of the inner skin is a class A isolation structure, and the isolation structure arranged on the upper surface of the inner skin side of the edge sealing piece is a class B isolation structure; the bonding transition position of the outer skin and the edge sealing piece comprises the upper surface of the outer skin and the side upper surface of the outer skin of the edge sealing piece; the isolation structure arranged on the upper surface of the outer skin is a C-type isolation structure, and the isolation structure arranged on the upper surface of the outer skin side of the edge sealing piece is a D-type isolation structure; the B-type isolation structure is adhered to the upper surface of the inner skin side of the edge sealing piece; the C-type isolation structure is adhered to the upper surface of the outer skin; and the D-type isolation structure is adhered to the upper surface of the outer skin side of the edge sealing piece.
In one possible embodiment, the B-class isolation structure, the C-class isolation structure, and the D-class isolation structure are made of high temperature resistant adhesive tape.
In one possible embodiment, the high temperature resistant tape is capable of withstanding high temperatures above 180 ℃.
In one possible embodiment, the class a isolation structure comprises a first layer of high temperature resistant tape, a conductive layer, and a second layer of high temperature resistant tape; the first layer of high-temperature-resistant adhesive tape is adhered to the upper surface of the inner skin, the guide layer is arranged on the first layer of high-temperature-resistant adhesive tape, and the second layer of high-temperature-resistant adhesive tape is adhered to the upper surface of the inner skin side of the edge sealing piece and the upper surface of the guide layer.
In one possible embodiment, the thickness of the guiding layer is equal to the thickness of the edge seal itself.
In one possible embodiment, an isolation film is laid on the upper surface of the aeronautical structural component before the whole is placed in the vacuum bag, so as to prevent glue solution from overflowing to the tool surface to form glue nubs.
In one possible embodiment, the separator film is a nonporous separator film.
The invention has the advantages that: the thickness of the glue tumor in the glue overflow range of the aviation structure glue joint piece meets the requirement of the aviation structure glue joint piece, and the appearance is smooth and attractive; the cleaning time of the glue tumor in the non-glue overflow range of the aviation structure glue joint piece is reduced from 30 minutes before improvement to less than 3 minutes after improvement.
Drawings
FIG. 1 is a schematic view of an aircraft structural adhesive member in the form of an overflow
FIG. 2 is a schematic diagram of a class A isolation structure according to a preferred embodiment of the present invention
FIGS. 3 (a), (b) and (c) are photographs showing the removal process of the A-type isolation structure according to an embodiment of the invention
FIG. 4 is a photograph of a preferred embodiment of the present invention using a nonporous separator film
FIG. 5 (a) is a photograph of flash for an aerospace structure without flash control; FIG. 5 (b) is a photograph showing the post-treatment of the flash in the comparative example using the conventional repair process
FIG. 6 (a) is an untreated photograph of example 1; FIG. 6 (b) photograph of example 1 treated by the method of the present invention
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The structure diagram of the aviation structure cementing part of a certain type of aircraft is shown in figure 1, and the aviation structure cementing part is formed by adhering a metal outer skin 1, an angled honeycomb core material 2, an angled metal edge sealing part 3 and a metal inner skin 4 into a closed sandwich structure by using adhesive. The angled metal edge sealing piece 3 is bonded with the metal inner skin 4 by adhesive between the two after being lapped, and the adhesive is extruded under the pressure effect in the hot pressing and curing forming process of the vacuum bag due to the height difference between the two, and one part of the adhesive is flowed along the metal inner skin 4 to be cooled and then is arranged on the metal inner skin 4 to form an A-type adhesive tumor in the figure 1; the other part flows to the upper part of the angled metal edge sealing member 3 under the action of the surface air-permeable material, so as to form the B-type glue tumor in fig. 1. The adhesive between the angled metal edge sealing piece 3 and the metal outer skin 1 is extruded under the pressure action in the curing process, and a part of the adhesive forms a C-shaped adhesive tumor in the figure 1 along the upper surface of the component metal outer skin 1; the other part flows to the upper surface of the lower part of the angular honeycomb core material 2 under the action of the surface air-permeable material to form D-shaped glue tumor in the figure 1.
The technical scheme of the invention is characterized in that the glue overflow is controlled by human intervention, glue overflow isolation and glue overflow control by a guide means. The method comprises the following steps:
1. human intervention and isolation of glue overflow. Aiming at B, C, D type glue tumors, a B type isolation structure, a C type isolation structure and a D type isolation structure are respectively arranged. The scheme is mainly divided into two aspects of 'isolating aviation structure cementing pieces' and 'isolating tools'. The surface of the cementing piece of the aviation structure or the surface of the tooling is isolated from the adhesive mainly by paving the isolating material, so that the glue overflow cleaning time is shortened, and the production efficiency is improved. The B-type isolation structure, the C-type isolation structure and the D-type isolation structure adopt high-temperature resistant adhesive tapes. The high temperature resistant adhesive tape should meet the following requirements:
(1) High temperature resistance. The molding temperature of the aviation structure cementing piece in the autoclave is 180 ℃ high, so the high-temperature resistant adhesive tape has high-temperature resistant performance.
(2) The stability is good. The aviation structure cementing piece is molded at high temperature and high pressure in an autoclave. Therefore, the high-temperature resistant adhesive tape should be stable at high temperature and high pressure, and not react and generate volatile substances which affect the performance of the aviation structure adhesive joint.
(3) No residue. The high temperature resistant adhesive tape should be easily removed from the aerospace structural adhesive after the aerospace structural adhesive is formed, and should not leave any material.
The scheme of the 'isolated aviation structure cementing piece' is as follows: the high-temperature-resistant adhesive tape which meets the performance requirement after the test is used for protecting the B, C, D type adhesive tumor area of the aviation structure adhesive part, so that the surface of the aviation structure adhesive part is prevented from forming adhesive tumor. After the aeronautical structure glued piece is formed, the high-temperature resistant adhesive tape is removed.
The scheme of the isolation tool is as follows: as shown in figure 4, the auxiliary material 'non-porous isolation film' special for structural cementing after the test is used for protecting and forming the tool, so that glue liquid is prevented from overflowing to the surface of the tool to form glue tumors, and the mold opening is prevented from being influenced. After the aeronautical structural adhesive is formed, the aeronautical structural adhesive is removed and the 'nonporous insulation film' is removed.
2. The guiding means controls glue overflow. Aiming at the type A glue tumor, a type A isolation structure is arranged. The A-type isolation structure comprises a first layer of high-temperature-resistant adhesive tape, a guide layer and a second layer of high-temperature-resistant adhesive tape; the first layer of high-temperature-resistant adhesive tape is adhered to the upper surface of the inner skin, the guide layer is arranged on the first layer of high-temperature-resistant adhesive tape, and the second layer of high-temperature-resistant adhesive tape is adhered to the upper surface of the inner skin side of the edge sealing piece and the upper surface of the guide layer. The thickness of the guide layer is equal to the thickness of the edge sealing piece. The proposal mainly depends on tools, materials and the like to artificially influence and control the solidification form of the overflow glue solution, so that the glue solution has thinner thickness and is easier to clean, or has the desirable surface form, which is divided into an UP guide type and a DOWN guide type.
(1) The UP guide type glue overflow control scheme is shown in figure 2. Wherein the 5 indication position is the glue overflow range of the aviation structure glue joint piece; and 6, indicating that the position is a non-glue overflowing range of the aviation structure gluing piece, wherein the reason that the glue overflowing range of the aviation structure gluing piece exists at the position 5 is that a certain range of glue overflowing is allowed for ensuring the gluing. The A-shaped glue tumor is positioned on the upper surface of the inner skin, and a method for manufacturing a special guide layer and paving an isolation material is adopted, so that in the assembly process of the structural glue joint piece: laying a first layer of appointed high-temperature-resistant adhesive tape at a position 7 of the attached figure 2, and playing a role in protecting the surface of the metal skin and isolating glue overflow; the guiding layer is paved at the position 8 of the figure 2, is made of glass fiber prepreg cloth, has certain strength and good bonding performance with the surface of the aviation structure bonding part, has a specified thickness (0.1-0.3 mm), can play roles of dispersing glue flow, controlling the glue tumor range and limiting the glue layer thickness, and simultaneously can not cause bridging and influence the vacuum pressure to be transmitted to the surface of the aviation structure bonding part when the vacuum bag is manufactured; a second layer of high temperature resistant adhesive tape is laid at the position 9 in fig. 2, and the adhesive tape plays roles in preventing glue overflow on the surface of the angle sealing part, controlling the thickness of the glue tumor and controlling the surface quality of the glue tumor. After the aviation structure cementing piece is solidified and molded: as shown in fig. 3 (a), the second layer of high temperature resistant tape at tear-off location 9; as shown in fig. 3 (b), the conductive layer is removed; as shown in fig. 3 (c), the first layer of high temperature resistant tape at location 7 is torn off.
(2) And (3) a DOWN guide type glue overflow control scheme. The A-shaped glue tumor is positioned between the aviation structure glue joint piece and the tooling, and the glue tumor interacts with the tooling to influence the mold opening of the aviation structure glue joint piece. Therefore, the special high-temperature-resistant 'demolding cloth' is paved and stuck on the rubber tumor area of the forming die of the DOWN type part, so that the smooth and flat surface of the tool at the rubber tumor forming part is ensured, and the rubber tumor is not adhered; and a high-temperature-resistant adhesive tape is paved on the surface of the angle edge sealing piece 3 of the aviation structure adhesive joint piece. And after the aviation structure cementing piece is molded, the aviation structure cementing piece is taken down from the molding tool, and the high-temperature-resistant adhesive tape is torn off.
Comparative example 1:
after the carrier-free adhesive is added to the 39 structural adhesive pieces of a certain type, a large amount of ultra-thick and hard spilled adhesive is generated after curing, as shown in fig. 5 (a). The conventional repair processing method is adopted, the time is more than 30 minutes, and the "oxidation protection layer" of the aviation structure adhesive joint is damaged, as shown in fig. 5 (b).
Example 1
As shown in fig. 6 (a), for a class B glue tumor of a glued aviation structure, a "high-temperature-resistant adhesive tape" is paved on the surface of an angled edge sealing member 3 of the glued aviation structure, and after the glued aviation structure is cured and molded, the high-temperature-resistant adhesive tape is torn off.
Aiming at C-type glue nubs of a gluing piece of an aviation structure with a certain structure, a 'non-porous isolating film' is paved between the tooling and the gluing piece of the aviation structure, the surface of the tooling is protected, and the glue nubs are prevented from forming on the surface of the tooling. After the aviation structure cementing piece is molded, the aviation structure cementing piece is detached from the tool, and the isolation film is removed.
Aiming at a certain structural adhesive joint aviation structure adhesive joint A type adhesive joint,
(1) Manufacturing a special conductive layer. Laying glass fiber prepreg fiber cloth with a specified layer number on a flat tool according to a specified thickness; preparing a vacuum bag, and solidifying in an autoclave according to specified technological parameters; cutting the solidified glass fiber board into a special guide layer according to a specified size.
(2) When the structural adhesive joint is assembled, laying a layer 1 of high-temperature resistant adhesive tape at the position 1 of the inner skin; laying a special guide layer; and laying a layer 2 of high-temperature-resistant adhesive tape on the angle edge sealing piece and the special guide layer.
(3) Removing the layer 2 high-temperature-resistant adhesive tape after molding; removing the special guide layer; the layer 1 high temperature resistant tape was removed.
After the scheme is implemented, the effect of 39 structural cementing pieces of a certain type machine is as shown in fig. 6 (b), and no glue tumor residue exists in the area where the aviation structural cementing pieces do not accept glue overflow; the surface of the tool is free of glue nubs; the aviation structure cementing piece can accept the glue overflow area glue tumor beautiful and meet the technical requirements.
Claims (6)
1. A glue overflow control method for an aviation structure glue joint piece is characterized in that,
the aviation structural component comprises an outer skin, a honeycomb core, an inner skin and an edge sealing piece; the outer skin and the inner skin are respectively coated with an adhesive film, the upper part of the honeycomb core is adhered to the inner skin, the lower part of the honeycomb core is adhered to the outer skin, the side edges of the honeycomb core are sealed and adhered to the outer skin and the inner skin through the edge sealing piece, and the whole aviation structural part is formed by adopting a vacuum bag through hot press; the glue overflow control method comprises the following steps: before hot press molding of a vacuum bag, arranging an isolation structure on the surface of the bonding transition position of the inner skin and the edge sealing piece and the surface of the bonding transition position of the outer skin and the edge sealing piece;
after hot press forming, removing the isolation structure;
the bonding transition position of the inner skin and the edge sealing piece comprises the upper surface of the inner skin and the side upper surface of the inner skin of the edge sealing piece;
the isolation structure arranged on the upper surface of the inner skin is a class A isolation structure, and the isolation structure arranged on the upper surface of the inner skin side of the edge sealing piece is a class B isolation structure; the bonding transition position of the outer skin and the edge sealing piece comprises the upper surface of the outer skin and the side upper surface of the outer skin of the edge sealing piece;
the isolation structure arranged on the upper surface of the outer skin is a C-type isolation structure, and the isolation structure arranged on the upper surface of the outer skin side of the edge sealing piece is a D-type isolation structure; the B-type isolation structure is adhered to the upper surface of the inner skin side of the edge sealing piece; the C-type isolation structure is adhered to the upper surface of the outer skin; the D-type isolation structure is adhered to the upper surface of the outer skin side of the edge sealing piece; the A-type isolation structure comprises a first layer of high-temperature-resistant adhesive tape, a guide layer and a second layer of high-temperature-resistant adhesive tape; the first layer of high-temperature-resistant adhesive tape is adhered to the upper surface of the inner skin, the guide layer is arranged on the first layer of high-temperature-resistant adhesive tape, and the second layer of high-temperature-resistant adhesive tape is adhered to the upper surface of the inner skin side of the edge sealing piece and the upper surface of the guide layer.
2. The method for controlling glue overflow of an aviation structure glue joint part according to claim 1, wherein,
the B-type isolation structure, the C-type isolation structure and the D-type isolation structure adopt high-temperature resistant adhesive tapes.
3. The method for controlling glue overflow of an aviation structure glue joint part according to claim 2, wherein,
the high-temperature-resistant adhesive tape can resist the high temperature of more than 180 ℃.
4. The method for controlling glue overflow of an aviation structure glue joint part according to claim 1, wherein,
the thickness of the guide layer is equal to the thickness of the edge sealing piece.
5. The method for controlling glue overflow of an aviation structure glue joint part according to claim 1, wherein,
and paving an isolating film on the upper surface of the aviation structural component before integrally placing the aviation structural component into a vacuum bag.
6. The method for controlling glue overflow of an aircraft structural adhesive according to claim 5, wherein,
the isolation film is a nonporous isolation film.
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| CN202111680638.0A CN114294308B (en) | 2021-12-30 | 2021-12-30 | Glue overflow control method for aviation structure glue joint piece |
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| CN112951808A (en) * | 2021-03-25 | 2021-06-11 | 深圳博元新材科技有限公司 | LED light-emitting module packaging method and device |
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| EP2055877A1 (en) * | 2007-11-05 | 2009-05-06 | Adler S.A. | Method of gluing a mounting element on a surface |
| CN103140058A (en) * | 2011-11-23 | 2013-06-05 | 无锡江南计算技术研究所 | Glue overflow control method of laminar structure |
| CN105845762A (en) * | 2016-03-31 | 2016-08-10 | 太仓海润太阳能有限公司 | Novel double-glass solar module and edge sealing method thereof |
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| CN114294308A (en) | 2022-04-08 |
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