CN117565406B - Aluminum alloy skin and honeycomb core gluing method - Google Patents
Aluminum alloy skin and honeycomb core gluing method Download PDFInfo
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- CN117565406B CN117565406B CN202410057400.XA CN202410057400A CN117565406B CN 117565406 B CN117565406 B CN 117565406B CN 202410057400 A CN202410057400 A CN 202410057400A CN 117565406 B CN117565406 B CN 117565406B
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 124
- 238000000034 method Methods 0.000 title claims abstract description 33
- 238000004026 adhesive bonding Methods 0.000 title claims abstract description 27
- 239000002313 adhesive film Substances 0.000 claims abstract description 42
- 239000003292 glue Substances 0.000 claims abstract description 39
- 238000005187 foaming Methods 0.000 claims abstract description 28
- 238000012360 testing method Methods 0.000 claims abstract description 14
- 238000003801 milling Methods 0.000 claims description 48
- 239000000126 substance Substances 0.000 claims description 25
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 8
- 229910052742 iron Inorganic materials 0.000 claims description 4
- 238000007373 indentation Methods 0.000 claims description 3
- 238000002955 isolation Methods 0.000 claims description 2
- 230000008439 repair process Effects 0.000 claims description 2
- 238000012795 verification Methods 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 10
- 230000008569 process Effects 0.000 description 9
- 239000000853 adhesive Substances 0.000 description 5
- 230000001070 adhesive effect Effects 0.000 description 5
- 229910052782 aluminium Inorganic materials 0.000 description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- NBIIXXVUZAFLBC-UHFFFAOYSA-N Phosphoric acid Chemical compound OP(O)(O)=O NBIIXXVUZAFLBC-UHFFFAOYSA-N 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 229910000147 aluminium phosphate Inorganic materials 0.000 description 1
- 238000007743 anodising Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 238000010409 ironing Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/02—Preparation of the material, in the area to be joined, prior to joining or welding
- B29C66/022—Mechanical pre-treatments, e.g. reshaping
- B29C66/0224—Mechanical pre-treatments, e.g. reshaping with removal of material
- B29C66/02241—Cutting, e.g. by using waterjets, or sawing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
- B29C66/122—Joint cross-sections combining only two joint-segments, i.e. one of the parts to be joined comprising only two joint-segments in the joint cross-section
- B29C66/1222—Joint cross-sections combining only two joint-segments, i.e. one of the parts to be joined comprising only two joint-segments in the joint cross-section comprising at least a lapped joint-segment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
- B29C66/122—Joint cross-sections combining only two joint-segments, i.e. one of the parts to be joined comprising only two joint-segments in the joint cross-section
- B29C66/1224—Joint cross-sections combining only two joint-segments, i.e. one of the parts to be joined comprising only two joint-segments in the joint cross-section comprising at least a butt joint-segment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/74—Joining plastics material to non-plastics material
- B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
- B29C66/7422—Aluminium or alloys of aluminium
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/80—General aspects of machine operations or constructions and parts thereof
- B29C66/81—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps
- B29C66/814—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps
- B29C66/8145—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the constructional aspects of the pressing elements, e.g. of the welding jaws or clamps
- B29C66/81455—General aspects of the pressing elements, i.e. the elements applying pressure on the parts to be joined in the area to be joined, e.g. the welding jaws or clamps characterised by the design of the pressing elements, e.g. of the welding jaws or clamps characterised by the constructional aspects of the pressing elements, e.g. of the welding jaws or clamps being a fluid inflatable bag or bladder, a diaphragm or a vacuum bag for applying isostatic pressure
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention belongs to the technical field of aviation part processing, and discloses an aluminum alloy skin and honeycomb core gluing method, wherein a chemically milled aluminum alloy skin and a milled honeycomb core are preassembled, and the matching degree between the aluminum alloy skin and the honeycomb core is judged; performing a check film test on the aluminum alloy skin and the honeycomb core, wherein the matching degree of the check film test meets the gluing requirement, and detecting the fit clearance between the aluminum alloy skin and the honeycomb core; paving a layer of adhesive film on the adhesive bonding surface of the aluminum alloy skin, and compensating the adhesive film in a region with a fit clearance larger than the thickness of the adhesive film; paving a layer of foaming glue along the chemically milled step of the aluminum alloy skin to enable the foaming glue to cover the whole chemically milled step; the honeycomb core is fitted to an aluminum alloy skin and cured in an autoclave. The method solves the problem that the gluing quality is affected by the fact that gaps are easily formed between the aluminum alloy skin and the honeycomb core at the step positions, and ensures the gluing quality between the aluminum alloy skin and the honeycomb core.
Description
Technical Field
The invention belongs to the technical field of aviation part processing, and particularly relates to an aluminum alloy skin and honeycomb core gluing method.
Background
The metal adhesive joint has the characteristics of high specific strength, uniform stress distribution, capability of remarkably reducing the weight of parts, reducing assembly stress and the like, and is widely applied to the field of aircraft processing and manufacturing. However, in some glue joint operations of aluminum alloy skins with special structures, for example, a step structure is formed on the surface of the skin according to design requirements or due to processing reasons, in the glue joint process of the aluminum alloy skin with the step structure, a larger fit clearance is generated between the step position of the aluminum alloy skin and the glue joint area of the honeycomb core, so that the glue joint quality between the aluminum alloy skin and the aluminum honeycomb core is difficult to ensure, and in severe cases, the glue joint product is debonded, so that parts are scrapped.
Disclosure of Invention
The invention aims to provide a bonding method of an aluminum alloy skin and a honeycomb core, which aims to solve the problem that the bonding quality of the aluminum alloy skin with a step structure and the honeycomb core is difficult to ensure.
The invention is realized by the following technical scheme:
the gluing method of the aluminum alloy skin and the honeycomb core comprises the following steps:
s01, pre-assembling the chemically milled aluminum alloy skin and the milled honeycomb core, and judging the matching degree between the aluminum alloy skin and the honeycomb core;
s02, performing a check film test on the aluminum alloy skin and the honeycomb core, wherein the matching degree of the check film test meets the gluing requirement, and detecting a fit clearance between the aluminum alloy skin and the honeycomb core;
s03, paving a layer of adhesive film on the adhesive bonding surface of the aluminum alloy skin, and compensating the adhesive film in the area with the fit clearance larger than the thickness of the adhesive film according to the fit clearance between the aluminum alloy skin and the honeycomb core, so that the thickness of the adhesive film at each position is consistent with or similar to the fit clearance;
s04, paving a layer of foaming glue along the chemically milled step of the aluminum alloy skin, so that the foaming glue covers the whole chemically milled step;
s05, the honeycomb core is matched and assembled on the aluminum alloy skin, and curing is carried out in an autoclave.
In some embodiments, in step S01, the positions corresponding to the chemical milling steps on the aluminum alloy skin are marked on the end surface of the aluminum alloy skin, the positions corresponding to the milling steps on the honeycomb core are marked on the end surface of the honeycomb core, after the aluminum alloy skin and the honeycomb core are preassembled, the marked positions of the chemical milling steps and the milling steps are compared, and the matching degree between the aluminum alloy skin and the honeycomb core is judged.
In some embodiments, in step S01, the degree of matching between the aluminum alloy skin and the honeycomb core is determined by comparing the degree of coincidence between the positions of the marks corresponding to the chemically milled steps and the chemically milled steps.
In some embodiments, in step S01, when the degree of matching between the aluminum alloy skin and the honeycomb core does not meet the glue joint requirement, the aluminum alloy skin is subjected to a repair treatment at the chemically milled step position.
In some embodiments, the degree of matching between the aluminum alloy skin and the honeycomb core not meeting the glue joint requirement means that the overlap ratio of the milling step and the corresponding marking position of the milling step exceeds a set value.
In some embodiments, in step S02, the operation of performing a verification film test on the aluminum alloy skin and the honeycomb core includes:
sequentially laying a honeycomb core, a check adhesive film arranged in a vacuum bag, an aluminum alloy skin, a nonporous isolation film and an airfelt on a check tool, arranging baffles on two sides of the honeycomb core, and then placing the honeycomb core into an autoclave for curing;
and after the curing is finished, taking out the check adhesive film, and judging the fit clearance between the aluminum alloy skin and the honeycomb core according to the honeycomb core cell indentation on the check adhesive film.
In some embodiments, after the check film is taken out, the thickness of each position of the check film is measured to obtain the size of the fit gap between the aluminum alloy skin and the honeycomb core.
In some embodiments, in step S04, the thickness of the foamed glue laid on the chemical milling step of the aluminum alloy skin is 2-3mm.
In some embodiments, in step S04, covering the entire chemically milled step with the foaming glue means that the foaming glue can cover the end face of the chemically milled step in the width direction and the two sides extend to the upper end face and the lower end face of the chemically milled step, respectively.
In some embodiments, in step S04, the foaming glue is ironed flat by an electric iron, and overflows to two ends of the chemical milling step.
Compared with the prior art, the invention has the following advantages:
the invention aims at the problems existing in the gluing process of the aluminum alloy skin and the honeycomb core, marks are carried out at the positions of the corresponding steps on the aluminum alloy skin and the aluminum honeycomb core, the matching positions between the steps on the aluminum alloy skin and the milling steps on the honeycomb core are prejudged by comparing the marked positions in the pre-assembly process, and the steps on the aluminum alloy skin are trimmed on the basis to preliminarily ensure the matching and assembly between the steps; then, accurately judging and detecting the fit clearance between the aluminum alloy skin step and the honeycomb core step through a check film test, and providing a reference for cementing operation between the aluminum alloy skin step and the honeycomb core step; finally, the expansion characteristic of the foaming adhesive in the curing process is utilized in the gluing operation to fill the aluminum alloy skin and the honeycomb core at the step matching position, so that the problem that the gluing quality is affected due to the fact that gaps are easily formed at the step position is solved, and the gluing quality between the aluminum alloy skin and the honeycomb core is guaranteed.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following description will briefly describe the drawings in the embodiments, it being understood that the following drawings only illustrate some embodiments of the present invention and should not be considered as limiting the scope, and that other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic diagram showing preassembly of an aluminum alloy skin and a honeycomb core in step S01 of the bonding method according to the present invention.
Fig. 2 is a schematic diagram of a test structure of an aluminum alloy skin and a honeycomb core calibration film in step S02 of the bonding method according to the present invention.
Fig. 3 is a schematic structural diagram of a foaming adhesive laid on a chemically milled step of an aluminum alloy skin in the cementing method S04 of the present invention.
Wherein:
1. the aluminum alloy coating comprises an aluminum alloy skin, 101, a chemically milling step, 2, a honeycomb core, 3, a chemically milling step mark, 4, a milling step mark, 5, a checking fixture, 6, a vacuum bag, 7, a non-porous isolating film, 8, an air felt, 9, a checking adhesive film, 10, a baffle plate, 11, an adhesive film, 12 and foaming adhesive.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention.
In the processing process of the aircraft parts, in order to meet the design requirement of the aluminum alloy skin parts, a chemical milling process is generally adopted to reduce the thickness of the skin so as to achieve the purpose of weight reduction. The chemical milling process (abbreviated as chemical milling) is a special machining process without tools, cutting and machining stress. Since the cutting stress is not generated on the parts in the chemical milling process, the method is commonly used for processing extremely thin, easily deformable and large-area parts, but steps are inevitably formed on the surface of the skin when the chemical milling processing is carried out on the skin, the height of the steps is generally determined by the thickness of the skin removed in the chemical milling operation, and generally, the aluminum alloy skin forms steps with the height of about 1mm on the skin after the chemical milling processing. This creates great difficulties in the subsequent gluing operation between the aluminium alloy skin and the honeycomb core.
In the research of the cementing performance of the aluminum alloy skin and the aluminum honeycomb core, the fact that a larger fit clearance is generated between the chemically milling step on the skin and the milling step of the honeycomb core in a cementing area due to tolerance accumulation and part deformation in the cementing operation of the aluminum alloy skin and the aluminum honeycomb core is found, so that the cementing quality is difficult to ensure. Meanwhile, based on performance test experiments of the cementing performance of the aluminum alloy skin and the aluminum honeycomb core, the cementing performance between the honeycomb core and the aluminum alloy skin is found to be difficult to meet the design requirement when the fit clearance between the honeycomb core and the aluminum alloy skin is larger than the thickness of the adhesive film.
Aiming at the problems in the bonding between the chemically milled aluminum alloy skin and the honeycomb core, the invention provides a bonding method capable of controlling the bonding quality of the aluminum alloy skin and the honeycomb core. The bonding method of the present invention will be described in detail with reference to specific examples.
The method comprises the following steps:
and S01, milling the honeycomb core 2, and milling a step-shaped milling step on the honeycomb core 2, wherein the milling step is matched with a chemical milling step 101 formed on the aluminum alloy skin 1 after chemical milling.
Marking the positions corresponding to all the chemical milling steps on the aluminum alloy skin on the end face of the aluminum alloy skin, and correspondingly obtaining chemical milling step marks 3 and milling step marks 4 at the positions corresponding to the milling steps on the honeycomb core at the positions marked by the end face of the honeycomb core, as shown in FIG. 1; the aluminum alloy skin 1 and the honeycomb core 2 are preassembled, and the matching degree between the aluminum alloy skin and the honeycomb core is judged by comparing the marking positions of the chemical milling steps and the milling steps.
Specifically, the matching degree between the aluminum alloy skin and the honeycomb core is judged by comparing the coincidence degree between the chemical milling step and the marking position corresponding to the milling step.
When the matching degree between the aluminum alloy skin and the honeycomb core does not meet the cementing requirement, the aluminum alloy skin is subjected to repairing treatment at the chemically milled step position. The fact that the matching degree between the aluminum alloy skin and the honeycomb core does not meet the bonding requirement means that the coincidence degree of the corresponding marking positions of the milling steps exceeds a set value of bonding processing. The aluminum alloy skin can be repaired by adopting the existing processing modes such as chemical milling, polishing and the like.
S02, before cementing operation, performing a check film test on the aluminum alloy skin and the honeycomb core, wherein the matching degree of the check film test meets the cementing requirement, and detecting a fit clearance between the aluminum alloy skin and the honeycomb core through the check film test;
performing a check film test operation on the aluminum alloy skin and the honeycomb core, comprising:
referring to fig. 2, a honeycomb core 2, a check adhesive film 9 arranged in a vacuum bag 6, an aluminum alloy skin 1, a non-porous isolating film 7 and an airfelt 8 are sequentially paved on a check tool, baffle plates 10 are arranged on two sides of the honeycomb core 2, and the honeycomb core 2 is packaged and then placed in an autoclave for curing; and after the curing is finished, taking out the check adhesive film, and judging the fit clearance between the aluminum alloy skin and the honeycomb core according to the honeycomb core cell indentation on the check adhesive film.
In the process, the aluminum alloy skin can generate certain deformation under the action of hot pressing to form fit with the honeycomb core so as to overcome the fit clearance with the honeycomb core. By utilizing the action principle, the check adhesive film is heated to a certain temperature, so that the check adhesive film has a certain viscosity, and at the moment, under the action of the mutual pressure between the aluminum alloy skin and the honeycomb core, the check adhesive film is extruded and deformed, so that the matching relationship between the aluminum alloy skin and the honeycomb core is displayed on the cured check adhesive film, and the matching relationship between the aluminum alloy skin and the honeycomb core can be accurately reflected.
And measuring the thickness of the cured check adhesive film by using a micrometer, and obtaining the size of a fit gap between the aluminum alloy skin and the honeycomb core according to the thickness of the check adhesive film at each position.
When the fit clearance between the two is smaller than the thickness of the check adhesive film, the check adhesive film can clearly show the core lattice marks of the honeycomb cores, and the thickness of the check adhesive film is thinned at the moment, so that the check adhesive film can fill the clearance between the two in the gluing process at the position, no gap exists between the two after the gluing, and good gluing can be formed at the position; when the fit clearance between the two is larger than the thickness of the check adhesive film, the check adhesive film is free of core lattice marks of the honeycomb core, and the thickness of the check adhesive film is thickened at the moment, and the check adhesive film cannot fully fill the clearance between the aluminum alloy skin and the honeycomb core in the gluing process at the position, so that insufficient gluing is caused, and a gluing defect occurs.
S03, carrying out phosphoric acid anodizing treatment on the aluminum alloy skin 1, and spraying primer until the primer is cured;
a layer of adhesive film 11 is paved on the adhesive bonding surface of the aluminum alloy skin, and the adhesive film 11 is compensated in the area with the matching clearance larger than the thickness of the adhesive film according to the matching clearance between the aluminum alloy skin and the honeycomb core, so that the thickness of the adhesive film at each position is consistent or similar to the matching clearance;
s04, paving a layer of foaming glue 12 with the thickness of 2-3mm along the chemically milled step of the aluminum alloy skin, wherein the thickness of the foaming glue 12 is preferably 2.5mm, and the width of the foaming glue 12 is 4-5mm, so that the foaming glue can cover the whole chemically milled step in the width direction, and referring to FIG. 3, the foaming glue is in a step shape matched with the chemically milled step, so that the foaming glue covers the end face of the chemically milled step in the width direction and the two sides of the foaming glue extend to the upper end face and the lower end face of the chemically milled step respectively.
And ironing the foaming glue by adopting an electric iron, and overflowing the foaming glue to two ends of the chemical milling step.
S05, assembling the honeycomb core on the aluminum alloy skin in a matching way, and solidifying in an autoclave to finish the gluing between the aluminum alloy skin and the honeycomb core.
When in glue joint forming, as the foaming glue generally has an expansion ratio of 2-3 times, the foaming glue plays a role in supporting and transmitting pressure to the glue film when expanding, and meanwhile, the expansion force of the foaming glue expansion is utilized to increase the thickness of the glue film to overcome the influence of a fit clearance on the glue joint quality, and ensure that the glue film and the aluminum alloy skin can be fully pressed to form better adhesion; and the foaming adhesive is introduced in the adhesive film bonding process, so that the bonding of the aluminum alloy skin and the honeycomb core and the service performance of the part are not affected.
In the description of the present invention, it should be noted that, as the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are used to indicate orientations or positional relationships based on those shown in the drawings, or those that are conventionally put in use in the product of the present invention, they are merely used to facilitate description of the present invention and simplify description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "horizontal," "vertical," and the like in the description of the present invention, if any, do not denote absolute levels or overhangs, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless explicitly stated and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
The foregoing description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and any simple modification, equivalent variation, etc. of the above embodiment according to the technical matter of the present invention fall within the scope of the present invention.
Claims (10)
1. The gluing method of the aluminum alloy skin and the honeycomb core is characterized by comprising the following steps of:
s01, pre-assembling the chemically milled aluminum alloy skin and the milled honeycomb core, and judging the matching degree between the aluminum alloy skin and the honeycomb core;
s02, performing a check film test on the aluminum alloy skin and the honeycomb core, wherein the matching degree of the check film test meets the gluing requirement, and detecting a fit clearance between the aluminum alloy skin and the honeycomb core;
s03, paving a layer of adhesive film on the adhesive bonding surface of the aluminum alloy skin, and compensating the adhesive film in the area with the fit clearance larger than the thickness of the adhesive film according to the fit clearance between the aluminum alloy skin and the honeycomb core, so that the thickness of the adhesive film at each position is consistent with or similar to the fit clearance;
s04, paving a layer of foaming glue along the chemically milled step of the aluminum alloy skin, so that the foaming glue covers the whole chemically milled step;
s05, the honeycomb core is matched and assembled on the aluminum alloy skin, and curing is carried out in an autoclave.
2. The method for bonding an aluminum alloy skin and a honeycomb core according to claim 1, wherein in step S01, positions corresponding to all chemical milling steps on the aluminum alloy skin are marked on the end face of the aluminum alloy skin, positions corresponding to the milling steps on the honeycomb core are marked on the end face of the honeycomb core, and after the aluminum alloy skin and the honeycomb core are preassembled, the matching degree between the aluminum alloy skin and the honeycomb core is judged by comparing the marked positions of the chemical milling steps and the milling steps.
3. The method for bonding an aluminum alloy skin and a honeycomb core according to claim 2, wherein in step S01, the degree of matching between the aluminum alloy skin and the honeycomb core is determined by comparing the degree of coincidence between the positions of the marks corresponding to the chemical milling step and the milling step.
4. The method for bonding an aluminum alloy skin to a honeycomb core according to claim 1 or 2, wherein in step S01, when the degree of matching between the aluminum alloy skin and the honeycomb core does not meet the bonding requirement, the aluminum alloy skin is subjected to a repair treatment at the chemically milled step position.
5. The method for bonding an aluminum alloy skin to a honeycomb core according to claim 4, wherein the fact that the degree of matching between the aluminum alloy skin and the honeycomb core does not meet the bonding requirement means that the overlap ratio of the corresponding mark positions of the chemical milling step and the milling step exceeds a set value.
6. The method of bonding an aluminum alloy skin to a honeycomb core according to claim 1, wherein in step S02, the operation of performing a verification film test on the aluminum alloy skin and the honeycomb core comprises:
sequentially laying a honeycomb core, a check adhesive film arranged in a vacuum bag, an aluminum alloy skin, a nonporous isolation film and an airfelt on a check tool, arranging baffles on two sides of the honeycomb core, and then placing the honeycomb core into an autoclave for curing;
and after the curing is finished, taking out the check adhesive film, and judging the fit clearance between the aluminum alloy skin and the honeycomb core according to the honeycomb core cell indentation on the check adhesive film.
7. The method for bonding an aluminum alloy skin to a honeycomb core according to claim 6, wherein after the calibration film is taken out, the thickness of each position of the calibration film is measured to obtain the size of the fit gap between the aluminum alloy skin and the honeycomb core.
8. The method of bonding an aluminum alloy skin to a honeycomb core according to claim 1, wherein in step S04, the thickness of the foaming glue laid on the chemical milling step of the aluminum alloy skin is 2-3mm.
9. The method for bonding an aluminum alloy skin to a honeycomb core according to claim 1 or 8, wherein in step S04, covering the entire chemically milled step with the foamed glue means that the foamed glue can cover an end face of the chemically milled step in a width direction and both sides extend to an upper end face and a lower end face of the chemically milled step, respectively.
10. The method for bonding an aluminum alloy skin and a honeycomb core according to claim 1, wherein in step S04, an electric iron is used to iron the foaming glue to be flat, and the foaming glue overflows to two ends of the chemical milling step.
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