CN114801214A - Secondary glue joint forming process for aviation composite material structure assembly and assembly structure - Google Patents

Abstract

The invention discloses a secondary glue joint forming process for an aviation composite material structure assembly and an assembly structure, wherein the glue joint 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: forming a foam core by using foaming glue and filling the foam core into the inner cavity of the framework; s3: and (3) gluing the framework, the front edge fairing and the skin by adopting a hot press molding forming process to form a combined closed structural member. The invention provides a secondary hinge molding process of an aeronautical composite material structural component and an aeronautical composite material structural component which meets requirements and can be rapidly produced by a component structure.

Description

Secondary glue joint forming process for aviation composite material structure assembly and assembly structure

Technical Field

The present invention relates to the field of aerospace composite structural components.

Background

When producing aviation combined material structure subassembly, need carry out special processing to the part of production, wherein need wash the metalwork according to specific mode to still need after the washing to the metalwork drying process, dry under specific temperature, and subsequent cooling processing of standing still, can have good compactness when guaranteeing the glued membrane to attach to the metalwork, avoid producing the bubble, influence the use of the structure subassembly after the assembly.

Disclosure of Invention

The purpose of the invention is as follows: in order to overcome the defects in the prior art, the invention provides a secondary gluing forming process of an aviation composite material structure component and an aviation composite material structure component which can rapidly produce the aviation composite material structure component meeting the requirements.

The technical scheme is as follows: in order to achieve the purpose, the technical scheme of the invention is as follows:

the secondary glue joint forming process of the aviation composite material structure 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: forming a foam core by using foaming glue and filling the foam core into the inner cavity of the framework;

s3: and (3) gluing the framework, the front edge fairing and the skin by adopting a hot press molding forming process to form a combined closed structural member.

Further, performing framework gluing on the framework in the S1, and performing surface dust removal treatment on the main joint, the wing tip, the front edge cushion block, the main beam, the rear wall and the rear edge cushion block by using compressed air before the framework gluing; and cleaning the area needing to be glued with acetone.

Further, preparing a bonding adhesive for bonding the skeleton, heating the component A to 45-60 ℃ for softening, then mixing the component A and the component B in proportion, and stirring uniformly; the mixture ratio is A: b is 100: 12.5; and smearing the prepared adhesive glue on the gluing area, and then waiting for the adhesive glue to be cured and molded.

Further, in S2, the foam rubber is taken out of the freezer, placed at room temperature and thawed, and then filled into the cavity of the frame, and then the frame is placed into the mold.

Further, the mould with the framework is sent into a press machine to apply pressure to a mould closing state; during curing, the pressure of the press is set to 175 +/-5 ℃, and the constant temperature and the constant pressure are required to be kept for 2 to 2.5 hours.

Further, in the step S3, when skin treatment is performed, the front edge cushion block and the release cloth on the main beam need to be torn off, and then all the assembly parts need to be cleaned by gasoline or acetone; and the upper skin, the lower skin, the leading edge fairing and the framework are pre-assembled and coordinately assembled, at least 2-3mm allowance is reserved at the edge of a leading edge and a trailing edge part of the skin when the upper skin and the lower skin are assembled, and 2-3mm fit clearance is required to be reserved when the skin is assembled with the main joint.

Further, before assembling the framework, drying equipment is needed to be used for drying a plurality of metal pieces; the drying rack in the drying equipment drives the metal piece to perform up-and-down spiral motion, and the drying rack drives the metal piece to continuously swing and rock.

Furthermore, before the framework is glued, a limiting structure is required to be used for positioning and clamping the framework; the abutting group of the limiting structure is arranged around the framework, the abutting end of the abutting group abuts against the bottom of the framework, and meanwhile the pressing structure at the top of the abutting group presses the side wall of the framework, so that the framework is limited.

Has the advantages that: the invention can quickly and effectively dry the metal piece to be assembled, and improve the adhesive film attaching tightness; including but not limited to the following benefits:

1) the sliding disc correspondingly drives the supporting net rack and the metal piece on the supporting net rack to perform vertical spiral motion through the convex block and the elastic bag body, so that the metal piece can be in full-range contact with hot gas in the drying chamber, and further, the metal piece can be rapidly dried;

2) the side wall of the fixed block is correspondingly moved by the joint disc and pressed against the side wall of the bottom of the concave framework, so that the bottom of the framework is limited; and the corresponding swing of pressing the tentacle utilizes laminating dish to press and pastes on the skeleton lateral wall, prescribes a limit to the skeleton top, because the flexible rod is flexible structure, and then presses the attached skeleton lateral wall that tentacle can adapt to, carries out inseparable pressing and prescribes a limit.

Drawings

FIG. 1 is a diagram of the steps of a glue joint forming process;

FIG. 2 is a flow chart of a secondary gluing molding process of the component;

FIG. 3 is a structural diagram of a drying apparatus;

FIG. 4 is a drawing of a structure of a drying rack;

FIG. 5 is a limited block diagram;

fig. 6 is a view showing the structure of the connection bar.

Detailed Description

The present invention will be further described with reference to the accompanying drawings.

As shown in figures 1-6: the secondary glue joint forming process of the aviation composite material structure 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: forming a foam core by using foaming glue and filling the foam core into the inner cavity of the framework;

s3: and (3) gluing the framework, the front edge fairing and the skin by adopting a hot press molding forming process to form a combined closed structural member.

The main joint needs to be positioned before the framework is assembled, the side face is detected by taking the main joint as a positioning reference according to the standard requirement, and if the main joint is not accurately positioned, the relative position size of the main joint and the side face can deviate, so that the design state and the subsequent use requirement can not be met.

Metal piece surface treatment aging and surface quality: after phosphoric acid anodization surface treatment is carried out on a metal piece according to a standard, after the metal piece is placed in a specified environment for 2-3 hours in a cooling mode, a J-47A (0.06mm) adhesive film is required to be pasted in 8 hours in a gluing area for surface protection, the protection time is not more than 5 days, the J-47A (0.06mm) adhesive film is removed before a framework is foamed, the J-47A (0.06mm) adhesive film is replaced by a high-temperature pressure-sensitive adhesive tape, the gluing area in subsequent assembly is covered and protected, the gluing process is to finish subsequent adhesive film laying in the specified time, and the metal piece is not allowed to be used after the specified time is exceeded;

if the metal piece can not be glued within the protection time of the J-47A glue film, the metal piece needs to be sealed and packaged, and phosphoric acid anodizing surface treatment is carried out 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, combining production records (production flow cards) of the parts in an assembly instruction, and recording a flow number and a batch number marked by the flow cards in the instruction.

Pre-assembling a framework:

a) positioning and fixing the main joint and the wing tip according to the digital-analog position by using 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 each part according to an edge line;

c) positioning and fixing are carried out by utilizing a positioning pin, a positioning block and a movable block, whether abnormal phenomena exist or not is checked, and the assembled composite material framework is disassembled after the requirements are met;

d) the surfaces of the parts in a nesting relationship allow for grinding, but the grinding amount cannot exceed the thickness of a single surface by 8 percent. When the composite part is assembled with the metal part, if interference occurs, the metal part is allowed to be knocked and repaired, H01-101H varnish should be smeared on the non-adhesive surface of the repaired and filed metal part, and when the cushion block type part is not parallel to the metal part during assembly, the cushion block composite part is allowed to be polished;

e) surface treatment of the metal piece: performing phosphoric acid anodizing surface treatment on the main joint and the wingtips; note: after surface treatment, the surface is packaged by a vacuum bag or an isolation film for the next working procedure, and the glue joint surface is polluted. The phenomenon of bruising in the process of carrying and storing the metal piece is strictly forbidden.

Drying the metal piece: drying the surfaces of the main joint and the wing tip for 1-1.5 hours in an environment of 55-65 ℃; after the metal piece is dried, the metal piece is required to be placed in a purification room with the temperature of 22-30 ℃ and the relative humidity of 30-65% 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, one layer of isolation paper of the adhesive film is removed, the adhesive film with the other layer of isolation paper is paved from one end of the gluing surface of the metal, the adhesive film is compacted to avoid generating bubbles when being paved, the pressure is applied to remove redundant air to enable the adhesive film to be firmly paved after being paved, and the operation time of drying the metal piece until the adhesive film is paved and paved is required to be not more than 8 hours.

Performing framework gluing on the framework in the S1:

a) the method comprises the following steps of (1) dedusting the surfaces of a main joint, a wing tip, a front edge cushion block, a main beam, a rear wall and a rear edge cushion block by using compressed air, then cleaning an area needing to be glued in a composite forest in a digital model by using acetone, cleaning 3 sides of the glued area by using a brush, wherein the interval is more than 5 minutes each time, and the part can be used after the last time of sending for more than 15 minutes and is recorded in a production record;

b) taking out the J-81 resin from a refrigeration house, and if the component A is in a viscous state, allowing the family members of the component A to be softened to about 45-60 ℃, wherein the optimal temperature is 50 ℃; the resin is prepared for use with the component B, and the validity period of the resin is checked before use, so that the resin cannot be used after the expiration period; preparing adhesive glue J-81: the ratio of A to B is 100 to 12.5; heating the component A to about 50 ℃ for softening, weighing A, B components according to the proportion, mixing and stirring uniformly, filling an adhesive according to the fit clearance between parts when coating, wherein the activity period of the adhesive is 3 hours at 15-30 ℃;

c) and (3) coating J-81 glue on the main joint, the wingtips, the main beam and the rear wall according to the area of the digifax where the parts need to be glued, gluing and assembling on a forming die, and positioning and fixing by using positioning pins and positioning movable blocks all the time in the assembling process. The front edge cushion block and the rear edge cushion block are placed at corresponding positions of a die and are adhered to the contact surface of the metal piece and the composite material piece through a J-47A adhesive film;

d) when the assembly gap delta is greater than 0.3mm (including the gap caused by all structures sinking) can be eliminated by J-81; when the assembly gap delta is less than 0.3mm, forced assembly is allowed, and a gap which can be eliminated by light pressure can be free of cushion; j-81 adhesive curing molding: j-81 is cured for more than 24 hours at the room temperature of 25-30 ℃.

Trimming and checking a framework:

a) after the composite material framework is bonded and cured, cleaning the excess J-81 glue at the edge of the part after curing, wherein no glue tumors are allowed to exist at the edge of each component;

b) and (5) checking the accuracy of the position of each part by using a part appearance checking frame on the glued framework. 4.1-4.9 mm of the pallet reference gap before 40% of the chord and 4.0-5.0 mm of the pallet reference gap after 40% of the chord, if the appearance of the composite material framework does not meet the requirement of the reference data, the framework needs to be bonded again;

c) sticking demolding cloth and pressure sensitive adhesive tape to the non-glued area of the metal piece for surface protection; a layer of demoulding cloth with glue is pasted on the surfaces of the main beam and the rear wall to protect the surfaces.

Forming the foaming glue:

a) the foaming glue in the S2 is J-121 foaming glue; taking the J-121 foaming adhesive out of the refrigeration house, standing and unfreezing for more than 6 hours at room temperature, and opening the sealed package after the temperature returns to the room temperature and no water vapor is condensed on the package. Before use, whether the product is in the valid period and recorded in the production record is checked, and the product cannot be used after being expired. Removing a J-47A adhesive film with the thickness of delta 0.06 mm;

b) filling J-121 foam rubber into the die cavity according to the digital model; reference amount: 158 +/-15.8 Kg of the cushion block at the front edge; 451 +/-45.1 Kg between the main beam and the rear wall; 49 +/-4.9 Kg of rear wall and rear edge cushion blocks; note: the reference dosage is not taken as the inspection basis, and the dosage of the foaming adhesive can be increased or decreased according to the actual situation.

c) Checking whether the equipment meets the use requirements and safe operation rules; sending the die into a press machine, applying pressure until the die is matched, and checking whether the die has obvious dislocation from the side surface; during curing, the pressure of the press is set to 300T, the temperature is set to 175 +/-5 ℃, and the constant temperature and the constant pressure are required to be kept for 2-2.5 hours.

Pre-assembling a skin and a framework:

a) tearing off the front edge cushion block and the demolding cloth on the main beam;

b) cleaning all parts to be assembled by using gasoline or acetone for at least 4 times, wherein the interval is more than 15 minutes every time, and filling the parts in a production record;

c) pre-assembling and coordinately repairing the upper skin, the lower skin, the front edge fairing and the framework, wherein at least 2-3mm of allowance is reserved at the edge of a front edge and rear edge part of the skin when the upper skin and the lower skin are repaired; when the skin is matched with the main joint, a 2-3mm fit clearance needs to be reserved, and the best fit clearance is 2 mm.

Spreading and pasting an adhesive film:

a) the surfaces of the upper die and the lower die are cleaned up, and the smoothness of the demolding cloth is guaranteed. Polishing the glued surface of the metal piece to be rough by using sand paper, cleaning by using acetone and drying; before the adhesive film is pasted, whether the surfaces of the skin and the framework adhesive film are redundant or not is checked;

b) and laying J-47A adhesive films on the adhesive 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 the adhesive films cannot be more than 2. And then assembling the skin with the framework, paying attention to the leveling of the skin and the root of the framework in the process of assembling the skin, and carrying out peripheral fixation by using a pressure sensitive adhesive tape. The assembled composite material is placed on a workbench and cannot be vertically placed, so that the adhesive film paved in the composite material is prevented from falling off, and the adhesive quality is prevented from being influenced; before covering the skin on the framework, visually checking whether excess materials exist in the sealed part and the adhesive film paved on the part.

Curing of assembly

a) Cleaning the working surface of the die, coating a release agent on the working surface, and volatilizing for at least 15 minutes to perform the next procedure;

b) a 1mm gasket is arranged in the middle of the butt joint surface of the skin and the metal main joint;

c) checking whether the mould has excess material, and putting the assembled composite material into a forming mould. And (3) paying attention to the matching of the step difference of the skin and the framework, fixing the skin and the framework by using a pressure sensitive adhesive tape after the assembly is finished, closing an upper die of a forming die, and putting the forming die on a press bed to prepare for heating and forming. Checking whether the molding equipment and the system meet the use requirements, and confirming that the molding equipment and the system can be heated and cured after no error exists;

d) and (3) testing the pressure by contact pressure, when the temperature rises to 75 +/-5 ℃ at the temperature rise rate of 1-3 ℃, pressurizing until the mold is closed, continuously raising the temperature to 130 +/-5 ℃, keeping the temperature and the pressure for 3 hours, reducing the temperature at the rate of less than or equal to 2 ℃/min, keeping the pressure in the furnace, cooling to 60 ℃, releasing the pressure and opening the mold.

Before assembling the framework, drying equipment 5 is needed to be used for drying a plurality of metal pieces; the drying rack 6 in the drying device 5 drives the metal piece to perform vertical spiral motion, and the drying rack 6 drives the metal piece to continuously swing and rock. The drying apparatus 5 comprises a drying chamber 51; a drying rack 6 is arranged in the drying chamber 51; the bottom of the drying chamber 51 is provided with an air inlet 511; the drying chamber 51 is provided with an opening 52 at the top in an open manner; the opening 52 is correspondingly 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 of the drying chamber flows out of the opening after passing through the drying rack from bottom to top, and the metal piece on the drying rack can be dried when the hot air flows out; the metal piece can meet the requirement of subsequent production process, and the adhesive film can be attached more tightly.

One end of the air inlet 511 is communicated with an external elastic cavity tube 54; one end of the elastic cavity tube 54, which is far away from the air inlet 511, is connected with the air outlet end of the blowing heater; the inner wall of the bottom of the drying chamber 51 is provided with an air duct 512 in the annular 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 rack 6; firstly, a metal piece is placed on the drying frame 6 through the opening 52, then air is supplied into the drying chamber 51 through the air inlet 511, when the temperature in the drying chamber 51 reaches a set temperature, the metal piece is closed on the opening 52 through the switch door 53, and then the drying frame 6 drives the metal piece to perform up-and-down spiral motion in the drying chamber 51. Hot air is introduced into the drying chamber, then the hot air is discharged from the opening, the drying chamber can be heated when the hot air passes through the drying chamber, when the temperature in the drying chamber reaches the required temperature, the opening and closing door can be closed, the temperature in the drying chamber is kept in the required temperature range, and then the metal piece can be dried and heated; the drying 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 comprises 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 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 spirally; the placing frame 62 includes a sliding tray 621; the side wall of the sliding disc 621 is attached to the inner wall of the drying chamber 51 and arranged in a sliding manner; a plurality of vent holes 622 are formed in the sliding disc 521 in a penetrating manner; a plurality of convex blocks 623 are fixedly arranged on the sliding disc 621; the tops of the bumps 623 are provided with cross bars 625; the plurality of cross bars 625 are mutually staggered and spliced to form a support net rack 63; the periphery of the support net rack is spaced from the inner wall of the drying chamber; an elastic capsule body 624 is clamped between the cross bar 625 and the bump 623; 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 disc 621 drives the support net rack 63 to move through the protrusion 623 and the elastic bag body 624, and the elastic bag body 624 drives the support net rack 63 to continuously shake; drive arrangement removes that motion bar drives the motion of sliding tray, and the corresponding lug and the upper and lower screw motion of metalwork that passes through on the elastic bag body drive support rack and the support rack of sliding tray, make the metalwork can the full with the indoor hot gas phase contact of stoving, and then can be quick carry out drying process to the metalwork, and when the elastic bag body drives the motion of support rack, because the elastic action of elastic bag body, elastic bag body self will horizontal hunting so, and then arouse and support the corresponding rocking of rack, the corresponding part of inlaying and supporting the rack fretwork of metalwork, and at the in-process that supports the rack and rock, support the production clearance that will correspond between rack and the metalwork, and steam just can circulate between the clearance of production, thereby the metalwork surface can be comprehensive with the hot gas contact, improve the effect of drying.

An adjusting cavity 7 is annularly 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; a plurality of the elastic traction wires 72 are arranged at intervals in the circumferential direction; when the adjustment cavity 7 is expanded, the elastic layer 71 is protruded into the drying chamber 51, and the section of the elastic layer 71 is tapered. When the adjusting cavity is expanded, the elastic layer correspondingly protrudes into the drying chamber to extrude the air in the drying chamber, the hot air is correspondingly extruded and reversely flows into the elastic cavity pipe, the elastic cavity pipe is expanded, and when the adjusting cavity is contracted, the air in the elastic cavity pipe flows into the drying chamber; therefore, gas can flow up and down rapidly and pass through the drying rack, and the metal piece can be blown by the flowing gas, so that the drying efficiency is improved.

Before the framework is glued, the framework needs to be positioned and clamped by using the limiting structure 1; the tight group 2 that supports of injecing structure 1 encircles the skeleton setting to support the end of contradicting of tight group 2 and support tightly in the skeleton bottom, simultaneously support the pressing structure 3 at tight group 2 top and press in the skeleton lateral wall, and then inject the skeleton. The confining structure 1 comprises an abutment group 2; the plurality of the propping groups 2 can be mutually independent or spliced into a whole; the abutment 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 sticking 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 wall of the framework to limit the framework; the annular structure encircles in the skeleton setting, and presses the structure corresponding to press the skeleton to paste and injectedly, and then can utilize annular structure's annular design to fix a position the skeleton to the utilization is pressed the structure and is compressed tightly the skeleton, and then can inject the firmware, improves the accuracy of location.

The middle edges of the two ends of the arc-shaped block 21 are provided with movable grooves 22; a connecting strip 23 is arranged between the adjacent arc-shaped blocks 21, and two ends of the 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 annularly, the splicing end 231 is correspondingly clamped and embedded into the movable groove 22 on the corresponding side; the plurality of arc-shaped blocks 21 are spliced end to end through a plurality of connecting strips 23 to form an annular structure 4; the concatenation end of connecting strip is embedded into the movable groove, and then can be in the same place adjacent arc type piece concatenation, and then a plurality of arc type pieces can be corresponding encircle and form ring structure, play the effect of location, and the cooperation is pressed the structure and is injectd the skeleton.

A limiting rod 232 penetrates through the middle of the splicing end 231, and the limiting rod 232 and the splicing end 231 are in a cross 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 embedding 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 arranged in an mutually attracting mode. The limiting rod on the splicing end is clamped and embedded in the embedding hole in 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 arranged, and the splicing end can be effectively prevented from being separated from the movable groove.

The pressing and pasting structure 3 comprises a fixing block 31; the fixed block 31 is embedded in the middle of the arc block 21; a bonding disc 32 is arranged on one side wall of the fixed block 31; one side of the attaching disc 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; the fit discs 32 move correspondingly to press and fit 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 far away from the fixed block 31 and extends upwards; a plurality of attaching discs 32 are arranged on the side wall of the flexible rod 33 at intervals; the laminating disks 32 are arranged side by side along the extending direction of the flexible rod 33 to form a pressing tentacle 34, one side, far away from the flexible rod 33, of the laminating disk 32 on the pressing tentacle 34 is correspondingly laminated on the side wall of the framework, and the pressing tentacle 34 is suitable for the bending arrangement of the concave-convex side wall of the framework; a plurality of the pressing tentacles 34 are pressed close to each other and limited on the framework. The side wall of the fixed block is correspondingly moved by the joint disc and pressed against the side wall of the bottom of the concave framework, so that the bottom of the framework is limited; and the corresponding swing of pressing the tentacle utilizes laminating dish to press and pastes on the skeleton lateral wall, prescribes a limit to the skeleton top, because the flexible rod is flexible structure, and then presses the attached skeleton lateral wall that tentacle can adapt to, carries out inseparable pressing and prescribes a limit.

The foregoing is a preferred embodiment of the present invention and is not intended to limit the invention, and it will be apparent to those skilled in the art that several modifications and variations can be made in the present invention without departing from the principles of the invention set forth above, and such modifications and variations are also considered to be within the scope of the invention.

Claims (8)

1. The secondary bonding forming process of the aviation composite material structure component is characterized by comprising the following steps of:

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: forming a foam core by using foaming glue and filling the foam core into the inner cavity of the framework;

s3: and (3) gluing the framework, the front edge fairing and the skin by adopting a hot press molding forming process to form a combined closed structural member.

2. The aerospace composite structural assembly secondary glue joint molding process of claim 1, wherein: performing framework gluing on the framework in the S1, and performing surface dust removal treatment on the main joint, the wing tip, the front edge cushion block, the main beam, the rear wall and the rear edge cushion block by using compressed air before the framework gluing; and cleaning the area needing glue joint by acetone.

3. The aerospace composite structural assembly secondary glue joint molding process of claim 2, wherein: preparing a bonding adhesive for bonding a framework, heating the component A to 45-60 ℃ for softening, then mixing the component A and the component B in proportion, and stirring uniformly; the mixture ratio is A: b is 100: 12.5; and smearing the prepared adhesive glue on the gluing area, and then waiting for the adhesive glue to be cured and molded.

4. The aerospace composite structural assembly secondary glue joint molding process of claim 3, wherein: s2, taking the foaming glue out of the refrigeration house, unfreezing the foaming glue at room temperature, filling the foaming glue into the inner cavity of the framework, and then filling the framework into a mold.

5. The aerospace composite structural assembly secondary glue joint molding process of claim 4, wherein: sending the mould with the framework into a press machine to apply pressure to a mould closing state; during curing, the pressure of the press is set to 175 +/-5 ℃, and the constant temperature and the constant pressure are required to be kept for 2 to 2.5 hours.

6. The aerospace composite structural assembly secondary glue joint molding process of claim 5, wherein: in S3, when skin treatment is carried out, the front edge cushion block and the demoulding cloth on the main beam are firstly torn off, and then all assembly parts are cleaned by gasoline or acetone; and the upper skin, the lower skin, the leading edge fairing and the framework are pre-assembled and coordinately assembled, at least 2-3mm allowance is reserved at the edge of a leading edge and a trailing edge part of the skin when the upper skin and the lower skin are assembled, and 2-3mm fit clearance is required to be reserved when the skin is assembled with the main joint.

7. The composite structural component of claim 6, wherein the component structure is formed by a two-step adhesive bonding process of the composite structural component, and the two-step adhesive bonding process comprises the following steps: before assembling the framework, drying equipment (5) is needed to be used for drying a plurality of metal pieces; the drying rack (6) in the drying equipment (5) drives the metal piece to perform vertical spiral motion, and the drying rack (6) drives the metal piece to continuously swing and rock.

8. The composite structural component of claim 6, wherein the component structure is formed by a two-step adhesive bonding process of the composite structural component, and the two-step adhesive bonding process comprises the following steps: before the framework is glued, the framework needs to be positioned and clamped by using a limiting structure (1); the pressing and sticking structure (3) at the top of the abutting group (2) is pressed on the side wall of the framework, and then the framework is limited.

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