CN114801214B - Secondary cementing forming process for aviation composite material structural component and component structure - Google Patents
Secondary cementing forming process for aviation composite material structural component and component structure Download PDFInfo
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- CN114801214B CN114801214B CN202210499198.7A CN202210499198A CN114801214B CN 114801214 B CN114801214 B CN 114801214B CN 202210499198 A CN202210499198 A CN 202210499198A CN 114801214 B CN114801214 B CN 114801214B
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- 239000002131 composite material Substances 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 title claims abstract description 25
- 230000008569 process Effects 0.000 title claims abstract description 23
- 239000003292 glue Substances 0.000 claims abstract description 20
- 238000005187 foaming Methods 0.000 claims abstract description 17
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 11
- 238000011049 filling Methods 0.000 claims abstract description 9
- 238000000748 compression moulding Methods 0.000 claims abstract description 4
- 239000006260 foam Substances 0.000 claims abstract description 4
- 238000001035 drying Methods 0.000 claims description 78
- 239000002184 metal Substances 0.000 claims description 48
- 230000000670 limiting effect Effects 0.000 claims description 20
- 230000001070 adhesive effect Effects 0.000 claims description 19
- 239000000853 adhesive Substances 0.000 claims description 18
- 238000003825 pressing Methods 0.000 claims description 17
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 14
- 238000004140 cleaning Methods 0.000 claims description 9
- 239000004744 fabric Substances 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000007664 blowing Methods 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 238000005057 refrigeration Methods 0.000 claims description 4
- 238000002156 mixing Methods 0.000 claims description 3
- 238000003756 stirring Methods 0.000 claims description 3
- 238000010257 thawing Methods 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- 239000000428 dust Substances 0.000 claims description 2
- 239000002313 adhesive film Substances 0.000 description 23
- 238000004519 manufacturing process Methods 0.000 description 8
- 238000010030 laminating Methods 0.000 description 7
- NBIIXXVUZAFLBC-UHFFFAOYSA-N Phosphoric acid Chemical compound OP(O)(O)=O NBIIXXVUZAFLBC-UHFFFAOYSA-N 0.000 description 6
- 238000004381 surface treatment Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 239000004820 Pressure-sensitive adhesive Substances 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 229910000147 aluminium phosphate Inorganic materials 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000011347 resin Substances 0.000 description 3
- 229920005989 resin Polymers 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
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- 206010028980 Neoplasm Diseases 0.000 description 1
- 244000137852 Petrea volubilis Species 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 238000007743 anodising Methods 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000007665 sagging Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000002966 varnish Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Classifications
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- 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
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
- B08B3/04—Cleaning involving contact with liquid
- B08B3/08—Cleaning involving contact with liquid the liquid having chemical or dissolving effect
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B5/00—Cleaning by methods involving the use of air flow or gas flow
- B08B5/02—Cleaning by the force of jets, e.g. blowing-out cavities
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F26—DRYING
- F26B—DRYING SOLID MATERIALS OR OBJECTS BY REMOVING LIQUID THEREFROM
- F26B21/00—Arrangements or duct systems, e.g. in combination with pallet boxes, for supplying and controlling air or gases for drying solid materials or objects
- F26B21/004—Nozzle assemblies; Air knives; Air distributors; Blow boxes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- 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)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
Abstract
The invention discloses a secondary gluing and forming process of an aviation composite material structural component and a component structure, wherein the gluing and forming process comprises the following steps: s1: assembling the front edge cushion block, the main beam, the rear wall and the rear edge cushion block with the main joint and the wing tip to form a framework; s2: filling foam cores formed by foaming glue into the inner cavity of the framework; s3: and (3) cementing the framework, the front edge fairing and the skin by adopting a compression molding process of a hot press to form the combined closed structural member. The invention provides a secondary hinging and forming process of an aviation composite material structural component and the component structure, which can rapidly produce the aviation composite material structural component meeting the requirements.
Description
Technical Field
The present invention relates to the field of aerospace composite structural components.
Background
When producing aviation composite material structural component, need carry out special processing to the part of production, wherein need wash the metalwork according to specific mode to wash the back and still need to dry the metalwork, dry at specific temperature, and follow-up standing cooling treatment, can have good compactness when guaranteeing that the glued membrane is attached to the metalwork, avoid producing the bubble, influence the use of the structural component after the assembly.
Disclosure of Invention
The invention aims to: in order to overcome the defects in the prior art, the invention provides a secondary gluing and forming process of an aviation composite structural component and the component structure, which can rapidly produce the aviation composite structural component meeting the requirements.
The technical scheme is as follows: in order to achieve the above purpose, the technical scheme of the invention is as follows:
the secondary gluing and forming process of the aviation composite structural component comprises the following steps:
s1: assembling the front edge cushion block, the main beam, the rear wall and the rear edge cushion block with the main joint and the wing tip to form a framework;
s2: filling foam cores formed by foaming glue into the inner cavity of the framework;
s3: and (3) cementing the framework, the front edge fairing and the skin by adopting a compression molding process of a hot press to form the combined closed structural member.
Further, the framework in the step S1 is subjected to framework gluing, and compressed air is used for carrying out surface dust removal treatment on the main joint, the wing tips, the front edge cushion block, the main girder, the rear wall and the rear edge cushion block before the framework gluing; and cleaning the area needing to be glued by acetone.
Further, preparing adhesive glue for framework bonding, heating the component A to 45-60 ℃ for softening, then mixing the component A with the component B according to the proportion, and uniformly stirring; the mixture ratio is A: b=100: 12.5; and (3) coating the prepared adhesive on a bonding area, and waiting for curing and forming of the adhesive.
And (2) taking the foaming glue out of the refrigeration house, placing the foaming glue in room temperature for thawing, filling the foaming glue into the cavity of the framework, and filling the framework into a die.
Further, the die with the framework is sent into a press machine to apply pressure to a die closing state; setting the pressure of the press machine at 175+/-5 ℃ and keeping the constant temperature and the constant pressure for 2-2.5 hours when curing.
In the S3, when the skin treatment is carried out, the demolding cloth on the front edge cushion block and the main beam is required to be torn off, and then all assembly parts are cleaned by using gasoline or acetone; and the upper skin, the lower skin and the front edge fairing are subjected to preassembly coordination repair with the framework, when the upper skin and the lower skin are subjected to repair, at least 2-3mm allowance is reserved at the edge of the front edge and the rear edge part of the skin, and when the skin is matched with the main joint, 2-3mm fit clearance is required to be reserved.
Furthermore, before assembling the framework, drying equipment is required to be used for drying a plurality of metal pieces; the drying rack in the drying equipment drives the metal piece to move up and down in a spiral mode, and the drying rack drives the metal piece to swing continuously.
Furthermore, before the framework is glued, the framework is required to be positioned and clamped by using a limiting structure; the tight group of support of limit structure encircles the skeleton setting, and the tight end of support of group supports tightly in the skeleton bottom, simultaneously the pressure subsides structure at tight group top presses in the skeleton lateral wall, and then prescribes a limit to the skeleton.
The beneficial effects are that: the invention can rapidly and effectively dry the metal parts to be assembled, and improves the adhesion compactness of the adhesive film; including but not limited to the following benefits:
1) The sliding disc drives the supporting net rack and the metal piece on the supporting net rack to move up and down in a spiral mode through the convex blocks and the elastic bag bodies correspondingly, so that the metal piece can be in full-scale contact with the hot gas phase in the drying chamber, and further the metal piece can be dried rapidly;
2) The corresponding movement of the attaching disc on the side wall of the fixed block is pressed against the side wall of the bottom of the concave framework to limit the bottom of the framework; and press and paste corresponding swing of tentacle, utilize the laminating dish to press and paste to the skeleton lateral wall on, inject the skeleton top, because flexible pole is flexible structure, and then press and paste the subsides that the tentacle can adapt to and paste to the skeleton lateral wall on, carry out inseparable pressure and paste and inject.
Drawings
FIG. 1 is a diagram of the steps of a cementing process;
FIG. 2 is a flow chart of a secondary glue joint forming process of the assembly;
FIG. 3 is a block diagram of a drying apparatus;
FIG. 4 is a diagram of a structure of a drying rack;
FIG. 5 is a diagram of a limiting structure;
fig. 6 is a diagram of the structure of the connecting bar.
Detailed Description
The invention will be further described with reference to the accompanying drawings.
As shown in fig. 1-6: the secondary gluing and forming process of the aviation composite structural component comprises the following steps:
s1: assembling the front edge cushion block, the main beam, the rear wall and the rear edge cushion block with the main joint and the wing tip to form a framework;
s2: filling foam cores formed by foaming glue into the inner cavity of the framework;
s3: and (3) cementing the framework, the front edge fairing and the skin by adopting a compression molding process of a hot press to form the combined closed structural member.
Before assembling the framework, the main joint needs to be positioned, the main joint is used as a positioning reference for detecting the side face according to the standard requirement, and if the main joint is positioned inaccurately, the relative position and the size of the main joint and the side face are necessarily deviated, so that the design state and the subsequent use requirement cannot be met.
Aging and surface quality of metal piece surface treatment: after the metal piece is subjected to phosphoric acid anodized surface treatment according to the standard, cooling is carried out in a specified environment for 2-3 hours, a J-47A (0.06 mm) adhesive film is attached to the glued joint area for surface protection within 8 hours, the protection time is not more than 5 days, the J-47A (0.06 mm) adhesive film is removed before the framework is foamed, a high-temperature pressure-sensitive adhesive tape is adopted to replace the J-47A (0.06 mm) adhesive film, the glued joint area in the subsequent assembly is covered and protected, the subsequent adhesive film laying is completed in the specified time in the glue joint process, and the metal piece is not allowed to be used;
if the metal part bonding cannot be completed within the protection time of the J-47A adhesive film, the metal part needs to be hermetically packaged and the phosphoric acid anodized surface treatment is performed again.
Preparation for production
Preparing qualified composite material parts such as a front edge cushion block, a main beam, a rear wall, an upper skin, a lower skin, a rear edge cushion block, a front edge fairing and the like, merging production records (production flow cards) of the parts into an assembly instruction, and recording a serial number and a batch number marked by the flow cards into the instruction.
Pre-assembling a framework:
a) Positioning and fixing the main joint and the wing tip according to the digital-analog position by utilizing the vacancy of the metal piece;
b) Pre-assembling a front edge cushion block, a main beam, a rear wall and a rear edge cushion block according to a digital model, and positioning all parts according to edge lines;
c) Positioning and fixing by using a positioning pin, a positioning block and a movable block, checking whether abnormal phenomenon exists or not, and dismantling the assembled composite skeleton after meeting the requirements;
d) Surfaces of the parts in nesting relationship allow for sanding but cannot be sanded by more than 8% of the thickness of a single face. When the composite part and the metal part are assembled, if interference occurs, the metal part is allowed to be knocked and repaired, the non-adhesive surface of the metal part after being trimmed should be coated with H01-101H varnish, and when the cushion block part and the metal part are not level during assembly, the cushion block composite part is allowed to be polished;
e) Surface treatment of metal parts: phosphoric acid anodizing the main joint and the wing tip; and (3) injection: after surface treatment, the product is packed by a vacuum bag or a separation film for the next process, and the cementing surface is placed to be polluted. The phenomenon of bruising during the process of carrying and storing the metal parts is forbidden.
Drying the metal piece: drying the main joint and the wing tip for 1 to 1.5 hours in an environment of 55 to 65 degrees after the surface treatment; after the metal piece is dried, the metal piece is required to be placed in a purifying room with the temperature of 22-30 degrees and the relative humidity of 30-65 percent for 1-1.5 hours, and then a J-47A adhesive film with the thickness of 0.06mm is paved on the metal piece for protection. When the adhesive film is paved, a layer of isolating paper of the adhesive film is torn off, the adhesive film with another layer of isolating paper is paved from one end of the adhesive bonding surface of the metal, the adhesive film needs to be pressed during paving, air bubbles are avoided, the adhesive film is compacted by removing redundant air after the adhesive film is paved, and the operation time from the drying of the metal piece to the adhesive film paving is required to be no more than 8 hours.
And (3) performing skeleton bonding on the skeleton in the step S1:
a) The method comprises the steps of dedusting the surfaces of parts by using compressed air through a main joint, a wingtip, a front edge cushion block, a main beam, a rear wall and a rear edge cushion block, then cleaning a region needing to be glued in a composite wood forest in a digital model by using acetone, cleaning 3 sides of the glued region by using a hairbrush, enabling the parts to be used after more than 15 minutes are generated for the last time at intervals of more than 5 minutes each time, and recording the parts in a production record;
b) Taking out the J-81 resin from the refrigeration house, and if the A component is in a viscous state, allowing the family of the A component to soften to about 45-60 ℃, wherein the optimal temperature is 50 ℃; the preparation and the component B are prepared for use, and the resin validity period is checked before the use, and the resin cannot be used for an excessive period; preparing adhesive J-81: the proportion is A, B=100:12.5; heating the component A to about 50 ℃ for softening, weighing A, B components according to the proportion, mixing, stirring uniformly, and if the adhesive is filled according to the fit clearance between parts during application, the adhesive activity period is 3 hours at 15-30 ℃;
c) And (3) smearing J-81 glue on the parts to be glued in the main joint, the wing tip, the main girder and the rear wall reference digital-analog, and carrying out glue-joint assembly on a forming die, wherein a locating pin and a locating movable block are always used for locating and fixing in the assembly process. The front edge cushion block and the rear edge cushion block are arranged at the corresponding positions of the die, and the J-47A adhesive film is adhered to the contact surface of the metal piece and the composite piece;
d) The assembly gap delta > 0.3mm (including the gap generated by all structural sagging) can be eliminated by J-81; when the assembly clearance delta is less than 0.3mm, the forced assembly is allowed, and the clearance which can be eliminated by the light pressure can be eliminated without being padded; and (3) curing and forming the J-81 adhesive: j-81 is solidified for more than 24 hours at the room temperature of 25-30 ℃.
And (3) framework finishing and checking:
a) After the composite material framework is glued and cured, cleaning up the excessive J-81 glue after curing at the edge of the part, wherein the edge of each component is not allowed to have glue tumor;
b) And (3) checking the accuracy of the positions of the parts by using the appearance checking frame of the parts on the framework after the gluing is finished. 4.1-4.9 mm for the clamping plate reference clearance before the chord of 40% and 4.0-5.0 mm for the clamping plate reference clearance after the chord of 40%, if the profile of the composite skeleton does not meet the requirement of reference data, the skeleton needs to be glued again;
c) Sticking release cloth and pressure-sensitive adhesive tape on the non-glued area of the metal piece for surface protection; and a layer of glued demolding cloth is adhered to the surface of the main beam and the back wall to protect the surface.
And (3) forming a foaming adhesive:
a) S2, the foaming glue is J-121 foaming glue; and taking the J-121 foaming adhesive out of the refrigeration house, standing at room temperature, thawing for more than 6 hours, and opening the sealed package after the foaming adhesive returns to the room temperature and no water vapor condenses on the package. Before use, checking whether the usage is in the validity period and recorded in the production record, and the usage is out of date. Removing the J-47A adhesive film with the thickness delta of 0.06 mm;
b) Filling J-121 foaming glue into the mold cavity by referring to the digital mold; reference amount: 158+/-15.8 Kg of front edge cushion block; 451+/-45.1 Kg of the space between the main beam and the rear wall; 49+/-4.9 Kg of rear wall and rear edge cushion block; and (3) injection: the reference amount is not used as a test basis, and the amount of the foaming adhesive can be increased or decreased according to actual conditions.
c) Checking whether the equipment meets the use requirement and the safety operation rules; feeding the die into a press machine to apply pressure until the die is clamped, and checking whether the die has obvious dislocation phenomenon from the side surface; when curing is carried out, the pressure of the press is set to be 300T, the temperature is 175+/-5 ℃, the constant temperature and the constant pressure are required to be kept, and the time is 2-2.5 hours.
Preassembling the skin and the framework:
a) Tearing off the demolding cloth on the front edge cushion block and the main beam;
b) Cleaning all parts to be assembled by using gasoline or acetone for at least 4 times, wherein each time is separated by more than 15 minutes, and filling in a production record;
c) Pre-assembling and coordinating the upper skin, the lower skin, the front edge fairing and the framework, and at least leaving 2-3mm allowance at the edges of the front edge and the rear edge parts of the skins when the upper skin and the lower skin are assembled; when the skin is matched with the main joint, a fit clearance of 2-3mm, preferably 2mm, is reserved.
Paving a rubberizing film:
a) And cleaning the surfaces of the upper die and the lower die, and ensuring the smoothness of the stripping cloth. Polishing the adhesive joint surface of the metal part by using sand paper to roughen, cleaning by using acetone and airing; before the adhesive film is pasted, checking whether the surface of the skin and the skeleton adhesive film has redundant substances or not;
b) And (3) paving J-47A adhesive films on the adhesive joint surfaces of the upper skin and the lower skin, wherein the thickness of the adhesive films can be properly increased according to the matching condition, and the number of layers cannot be more than 2. And then assembling the skin with the framework, paying attention to the flush of the skin and the root of the framework in the process of assembling the skin, and performing peripheral fixation by using a pressure-sensitive adhesive tape. The assembled composite material is placed on a workbench and can not be placed vertically, so that the falling of an adhesive film paved in the composite material is prevented, and the adhesive quality is prevented from being influenced; before covering the skin on the framework, visually checking whether the inside of the closed part and the paved adhesive film have redundant objects or not.
Assembling and solidifying
a) Cleaning a working molded surface of a die, brushing a release agent on the working molded surface, and volatilizing for at least 15 minutes to perform the next procedure;
b) Placing a gasket of 1mm in the middle of the butt joint surface of the skin and the metal main joint;
c) Checking whether the mold has excessive residues or not, and placing the assembled composite material into a forming mold. Note the step-by-step fit between the skin and the skeleton, after assembly, the skin and the skeleton are fixed with pressure-sensitive adhesive tape, then the upper mold of the forming mold is closed, and the forming mold is placed on a press bed to be ready for heating forming. Checking whether the molding equipment and the molding system meet the use requirement or not, and heating and curing after confirming that the molding equipment and the molding system are error-free;
d) And (3) carrying out pressure test by using contact pressure, when the temperature rising rate is 1-3 ℃, and the temperature rises to 75+/-5 ℃, pressurizing to be standard, continuously rising the temperature to 130+/-5 ℃, preserving heat and pressure for 3 hours, cooling at the rate of less than or equal to 2 ℃/min, carrying out pressure maintaining cooling to 60 ℃ along with the furnace, and releasing pressure and opening the die.
Before assembling the framework, drying equipment 5 is needed to carry out drying treatment on a plurality of metal pieces; the drying rack 6 in the drying equipment 5 drives the metal piece to move up and down in a spiral mode, and the drying rack 6 drives the metal piece to swing continuously. The drying apparatus 5 includes a drying chamber 51; a drying rack 6 is arranged in the drying chamber 51; an air inlet 511 is formed in the bottom of the drying chamber 51; an opening 52 is arranged at the top of the drying chamber 51 in an open manner; the opening 52 is provided with a switch door 53 which can close the drying chamber 51; one side of the switch door 53 is hinged with the drying chamber 51; the hot air in the drying chamber flows out from the opening after passing through the drying frame from bottom to top, and the metal parts on the drying frame can be dried when the hot air flows out; the metal piece can meet the requirement of the subsequent production process, and the adhesive film is more tightly attached.
An elastic cavity tube 54 with one end communicated with the outside is arranged at one end of the air inlet 511; one end of the elastic cavity tube 54, which is far away from the air inlet 511, is connected to the air outlet end of the blowing heater; an air duct 512 is circumferentially arranged on the inner wall of the bottom of the drying chamber 51; the other end of the air inlet 511 is communicated with an air duct 512; the air duct 512 is communicated with the bottom of the drying chamber 51 through a plurality of exhaust pipes 513; a plurality of exhaust pipes 513 are arranged below the drying rack 6; firstly, a metal piece is placed on a drying frame 6 through an opening 52, then air is introduced into a drying chamber 51 through an air inlet 511, when the temperature in the drying chamber 51 reaches a set temperature, the opening and closing door 53 is closed at the opening 52, and then the drying frame 6 drives the metal piece to move up and down in a spiral manner in the drying chamber 51. Firstly, hot air is introduced into the drying chamber, then the hot air is discharged from the opening, when the hot air passes through the drying chamber, the drying chamber can be heated, when the temperature in the drying chamber reaches the required temperature, the switch door can be closed, and then the temperature in the drying chamber is kept within the required temperature range, and further, the metal piece can be dried and heated; the device has the function of keeping constant temperature and constant pressure, and is beneficial to effectively drying and drying the metal piece.
The drying rack 6 includes a moving rod 61; the bottom driving device of the drying chamber 51 is in driving connection with the bottom end of the moving rod 61; a placing frame 62 is fixedly arranged at the top end of the moving rod 61; the moving rod 61 drives the placing frame 62 to move up and down in a spiral manner; the placement frame 62 includes a sliding plate 621; the side wall of the sliding disk 621 is attached to the inner wall of the drying chamber 51 in a sliding manner; a plurality of vent holes 622 are formed in the sliding plate 521 in a penetrating manner; a plurality of protruding blocks 623 are fixedly arranged on the sliding disk 621; a cross bar 625 is arranged at the top of the convex blocks 623; the cross bars 625 are mutually staggered and spliced to form a supporting net rack 63; the periphery of the support net frame is spaced from the inner wall of the drying chamber; an elastic bag body 624 is clamped between the transverse bar 625 and the convex block 623; the elastic bag body 624 is semicircular, and the bottom of the transverse bar 625 is fixedly connected with the top of the elastic bag body 624; the sliding plate 621 drives the support net rack 63 to move through the protruding block 623 and the elastic bag body 624, and the elastic bag body 624 drives the support net rack 63 to continuously shake; the driving device drives the sliding plate to move, the sliding plate correspondingly drives the supporting grid frame and the metal piece on the supporting grid frame to move up and down in a spiral mode through the protruding blocks and the elastic bag body, the metal piece can be enabled to be in full-scale contact with hot air in the drying chamber, further the metal piece can be rapidly dried, when the elastic bag body drives the supporting grid frame to move, the elastic bag body can swing left and right due to the elastic effect of the elastic bag body, the supporting grid frame is further caused to swing correspondingly, the metal piece is correspondingly embedded into the hollowed-out part of the supporting grid frame, gaps are correspondingly formed between the supporting grid frame and the metal piece in the swinging process of the supporting grid frame, hot air can circulate between the generated gaps, and accordingly the surface of the metal piece can be comprehensively contacted with the hot air, and the drying effect is improved.
An adjusting cavity 7 is circumferentially arranged on the side wall of the top of the drying chamber 51; the part of the inner wall of the drying chamber 51 corresponding to the adjusting cavity 7 is an elastic layer 71; the adjusting cavity 7 is communicated with the air outlet end of the blowing heater through an air pipe; the top and bottom side walls of the elastic layer 71 are fixedly connected with the inner wall of the adjusting cavity 7 through elastic traction wires 72; the elastic traction wires 72 are arranged at intervals in the circumferential direction; when the regulating cavity 7 is expanded, the elastic layer 71 protrudes into the drying chamber 51, and the section of the elastic layer 71 is tapered. When the adjusting cavity expands, the elastic layer correspondingly protrudes into the drying chamber, gas in the drying chamber is extruded, hot gas correspondingly is extruded to reversely flow into the elastic cavity tube, the elastic cavity tube expands, and when the adjusting cavity contracts, the gas in the elastic cavity tube flows into the drying chamber again; therefore, the gas can flow up and down through the drying rack rapidly, and then the metal piece can be blown by the flowing of the gas, so that the drying efficiency is improved.
Before the framework is glued, the framework is required to be positioned and clamped by using the limiting structure 1; the propping group 2 of the limiting structure 1 is arranged around the framework, the propping end of the propping group 2 is propped against the bottom of the framework, and meanwhile, the pressing structure 3 at the top of the propping group 2 is pressed on the side wall of the framework, so that the framework is limited. The limiting structure 1 comprises a tightening group 2; the abutting groups 2 can be mutually independent or spliced into a whole; the abutting group 2 comprises an arc-shaped block 21; the middle part of the top of the arc-shaped block 21 is provided with a pressing and pasting structure 3; the arc-shaped blocks 21 can be spliced end to form an annular structure 4; the annular structures 4 are correspondingly arranged around the framework, and the pressing ends of the pressing structures 3 are correspondingly pressed on the side walls of the framework to limit the framework; the annular structure surrounds in the skeleton setting, and presses the corresponding skeleton of pasting the structure to press and paste and prescribe a limit, and then can utilize annular structure's annular design to fix a position the skeleton to press the structure to compress tightly the skeleton, and then can prescribe a limit to the firmware, improve the accuracy of location.
The edges of the middle parts of the two ends of the arc-shaped block 21 are provided with movable grooves 22; connecting strips 23 are arranged between the adjacent arc-shaped blocks 21, and two ends of each connecting strip 23 are respectively embedded into the adjacent movable grooves 22; one end of the connecting strip 23 is hinged with the movable groove 22 on the corresponding side, and the other end of the connecting strip 23 is a splicing end 231; when the arc-shaped blocks 21 are distributed in a circumferential direction, corresponding cards of the splicing ends 231 are embedded into the movable grooves 22 on the corresponding sides; the arc-shaped blocks 21 are spliced end to end through a plurality of connecting strips 23 to form an annular structure 4; the splicing ends of the connecting strips are embedded into the movable grooves, so that adjacent arc-shaped blocks can be spliced together, a plurality of arc-shaped blocks can correspondingly encircle to form an annular structure, the positioning effect is achieved, and the framework is limited by matching with the pressing structure.
A limiting rod 232 is arranged in the middle of the splicing end 231 in a penetrating manner, and the limiting rod 232 and the splicing end 231 are in a crisscross shape; an embedding opening 221 is formed at the edge of the movable groove 22 corresponding to the splicing end 231; the limiting rod 232 is correspondingly embedded into the embedded opening 221 under the action of external force; the limiting rod 232 is of a magnetic structure, and the limiting rod 232 and the magnetic block in the embedding opening 221 are mutually attracted. The limiting rod on the splicing end is clamped and embedded into the embedded opening on the side wall of the movable groove, so that the limiting effect on the connecting strip is achieved, the limiting rod and the magnetic block are attracted, and the splicing end can be effectively prevented from being separated from the movable groove.
The pressing structure 3 comprises a fixed block 31; the fixed block 31 is embedded in the middle of the arc-shaped block 21; a bonding disc 32 is arranged on one side wall of the fixed block 31; one side of the attaching plate 32 is arranged towards the center of the annular structure 4; the driving end of the telescopic device on the side wall of the fixed block 31 is in driving connection with the other side of the attaching disc 32; a plurality of attaching plates 32 are correspondingly moved to be attached to the top of the framework; a flexible rod 33 is arranged at the top of the fixed block 31; the top driving device of the fixed block 31 is in driving connection with the bottom end of the flexible rod 33; the other end of the flexible rod 33 is arranged away from the fixed block 31 in an upward extending way; a plurality of attaching plates 32 are arranged on the side wall of the flexible rod 33 at intervals; the laminating discs 32 are arranged side by side along the extending direction of the flexible rod 33 to form laminating tentacles 34, one side, away from the flexible rod 33, of the laminating disc 32 on the laminating tentacles 34 is correspondingly laminated on the side wall of the framework, and the laminating tentacles 34 are correspondingly bent and arranged on the concave-convex side wall of the framework; the pressing feelers 34 are pressed close to each other to be limited to the skeleton. The corresponding movement of the attaching disc on the side wall of the fixed block is pressed against the side wall of the bottom of the concave framework to limit the bottom of the framework; and press and paste corresponding swing of tentacle, utilize the laminating dish to press and paste to the skeleton lateral wall on, inject the skeleton top, because flexible pole is flexible structure, and then press and paste the subsides that the tentacle can adapt to and paste to the skeleton lateral wall on, carry out inseparable pressure and paste and inject.
The above description is not intended to limit the invention to the preferred embodiments of the present invention, and it will be apparent to those skilled in the art that modifications and variations can be made to the present invention without departing from the above-described principles of the invention, and these modifications and variations are also considered to be within the scope of the invention.
Claims (3)
1. The secondary gluing and forming process of the aviation composite structural component is characterized by comprising the following steps of:
s1: assembling a front edge cushion block, a main beam, a rear wall and a rear edge cushion block with a main joint and wing tips to form a framework, and performing framework gluing on the framework in the step S1; preparing adhesive glue for framework bonding, heating the component A to 45-60 ℃ for softening, then mixing the component A and the component B according to the proportion, and uniformly stirring; coating the prepared adhesive on the adhesive joint area, and waiting for curing and forming the adhesive;
s2: filling foam cores formed by foaming glue into the inner cavity of the framework; taking out the foaming glue from the refrigeration house, placing the foaming glue in room temperature for thawing, filling the foaming glue into an inner cavity of a framework, and filling the framework into a die; feeding a die with a framework into a press machine to apply pressure to a die closing state; setting the pressure of a press machine to 175+/-5 ℃ when curing, and keeping a constant temperature and constant pressure state for 2-2.5 hours;
s3: bonding the framework, the front edge fairing and the skin by adopting a compression molding process of a hot press to form a combined closed structural member;
drying equipment (5) is needed to carry out drying treatment on a plurality of metal pieces before assembling the framework; the drying rack (6) in the drying equipment (5) drives the metal piece to move up and down in a spiral mode, and the drying rack (6) drives the metal piece to swing continuously;
the drying device (5) comprises a drying chamber (51); a drying rack (6) is arranged in the drying chamber (51); an air inlet (511) is formed in the bottom of the drying chamber (51); an opening (52) is formed in the top of the drying chamber (51) in an open mode; a switch door (53) capable of closing the drying chamber (51) is correspondingly arranged on the opening (52); one side of the switch door (53) is hinged with the drying chamber (51);
one end of the air inlet (511) is communicated with an elastic cavity tube (54) outside; one end of the elastic cavity tube (54) far away from the air inlet (511) is connected with the air outlet end of the blowing heater; an air duct (512) is arranged on the inner wall of the bottom of the drying chamber (51) in a circumferential direction; the other end of the air inlet (511) is communicated with an air duct (512); the air duct (512) is communicated with the bottom of the drying chamber (51) through a plurality of exhaust pipes (513); the exhaust pipes (513) are arranged below the drying frames (6);
the drying rack (6) comprises a moving rod (61); the bottom driving device of the drying chamber (51) is in driving connection with the bottom end of the motion rod (61); a placing frame body (62) is fixedly arranged at the top end of the moving rod (61); the moving rod (61) drives the placing frame body (62) to move up and down in a spiral manner; the placement frame body (62) comprises a sliding disc (621); the side wall of the sliding disc (621) is attached to the inner wall of the drying chamber (51) in a sliding manner; a plurality of vent holes are formed in the sliding plate (621) in a penetrating manner; a plurality of protruding blocks are fixedly arranged on the sliding plate (621); the tops of the convex blocks are provided with transverse bars (625); the transverse strips (625) are mutually staggered and spliced to form a supporting net rack (63); the periphery of the support net frame is spaced from the inner wall of the drying chamber; an elastic bag body (624) is clamped between the transverse bar (625) and the convex blocks; the elastic bag body (624) is semicircular, and the bottom of the cross bar (625) is fixedly connected with the top of the elastic bag body (624); the sliding plate (621) drives the supporting net rack (63) to move through the convex blocks and the elastic bag body (624), and the elastic bag body (624) drives the supporting net rack (63) to continuously shake;
an adjusting cavity (7) is formed in the top side wall of the drying chamber (51) in a circumferential direction; the part of the inner wall of the drying chamber (51) corresponding to the adjusting cavity (7) is an elastic layer (71); the adjusting cavity (7) is communicated with the air outlet end of the blowing heater through an air pipe; the top and bottom side walls of the elastic layer (71) are fixedly connected with the inner wall of the adjusting cavity (7) through elastic traction wires (72); the elastic traction wires (72) are arranged at intervals in the circumferential direction;
before the framework is glued, the framework is required to be positioned and clamped by using a limiting structure (1); the abutting group (2) of the limiting structure (1) is arranged around the framework, the abutting end of the abutting group (2) abuts against the bottom of the framework, and meanwhile, the pressing structure (3) at the top of the abutting group (2) presses the side wall of the framework, so that the framework is limited;
the limiting structure (1) comprises a tightening group (2); the abutting groups (2) are spliced into a whole; the abutting group (2) comprises an arc-shaped block (21); the middle part of the top of the arc-shaped block (21) is provided with a pressing and pasting structure (3); the arc-shaped blocks (21) are spliced end to form an annular structure (4); the annular structures (4) are correspondingly arranged around the framework, and the pressing ends of the pressing structures (3) are correspondingly pressed on the side walls of the framework to limit the framework;
the edges of the middle parts of the two ends of the arc-shaped block (21) are provided with movable grooves (22); connecting strips (23) are arranged between the adjacent arc-shaped blocks (21), and two ends of each connecting strip (23) are respectively embedded into the adjacent movable grooves (22); one end of the connecting strip (23) is hinged with the movable groove (22) on the corresponding side, and the other end of the connecting strip (23) is a splicing end (231); when the arc-shaped blocks (21) are distributed in a circumferential direction, corresponding cards of the splicing ends (231) are embedded into the movable grooves (22) on the corresponding side; the arc-shaped blocks (21) are spliced end to end through a plurality of connecting strips (23) to form an annular structure (4);
a limiting rod (232) is arranged in the middle of the splicing end (231) in a penetrating manner, and the limiting rod (232) and the splicing end (231) are in a crisscross shape; an embedding opening (221) is formed at the edge of the movable groove (22) corresponding to the splicing end (231);
the limiting rod (232) is of a magnetic structure, and the limiting rod (232) and the magnetic block in the embedded port (221) are mutually attracted;
the pressing structure (3) comprises a fixed block (31); the fixed block (31) is embedded in the middle of the arc-shaped block (21); a first attaching disc is arranged on one side wall of the fixed block (31); one side of the first attaching disc faces to the center of the annular structure (4); the driving end of the telescopic device on the side wall of the fixed block (31) is in driving connection with the other side of the first attaching disc; the first attaching plates are correspondingly moved and pressed on the top of the framework; a flexible rod (33) is arranged at the top of the fixed block (31); the top driving device of the fixed block (31) is in driving connection with the bottom end of the flexible rod (33); the other end of the flexible rod (33) is upwards extended away from the fixed block (31); a plurality of second attaching plates are arranged on the side wall of the flexible rod (33) at intervals; the second attaching plates are arranged side by side along the extending direction of the flexible rod (33) to form pressing contact arms (34), one side, far away from the flexible rod 33, of each second attaching plate on each pressing contact arm (34) is correspondingly attached to the side wall of the framework, and the pressing contact arms (34) are bent and arranged correspondingly to the concave-convex side wall of the framework; the pressing contact arms (34) are mutually close to each other and are limited to the framework in a pressing mode.
2. The secondary bonding molding process of an aerospace composite structural component according to claim 1, wherein: in the step S1, the main joint, the wingtips, the front edge cushion blocks, the main girder, the rear wall and the rear edge cushion blocks are subjected to surface dust removal treatment by using compressed air before framework cementing; and cleaning the area needing to be glued by acetone.
3. The secondary bonding molding process of an aerospace composite structural component according to claim 2, wherein: in S3, when skin treatment is carried out, the demolding cloth on the front edge cushion block and the main beam is required to be torn off, and then all assembly parts are cleaned by using gasoline or acetone; and the upper skin, the lower skin and the front edge fairing are preassembled and coordinated with the framework, and when the skins are matched with the main joint, a 2-3mm fit gap is required to be reserved.
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| CN114801214A (en) | 2022-07-29 |
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