CN115596748A - One-time glue joint curing molding method for mosaic structure and shell assembly - Google Patents
One-time glue joint curing molding method for mosaic structure and shell assembly Download PDFInfo
- Publication number
- CN115596748A CN115596748A CN202211313902.1A CN202211313902A CN115596748A CN 115596748 A CN115596748 A CN 115596748A CN 202211313902 A CN202211313902 A CN 202211313902A CN 115596748 A CN115596748 A CN 115596748A
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- prefabricated
- honeycomb
- outer skin
- paving
- insert
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- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000000465 moulding Methods 0.000 title claims abstract description 18
- 239000003292 glue Substances 0.000 title claims description 26
- 238000004519 manufacturing process Methods 0.000 claims abstract description 8
- 241000264877 Hippospongia communis Species 0.000 claims description 78
- 238000001723 curing Methods 0.000 claims description 38
- 239000002313 adhesive film Substances 0.000 claims description 27
- 239000000853 adhesive Substances 0.000 claims description 23
- 230000001070 adhesive effect Effects 0.000 claims description 23
- 229910052751 metal Inorganic materials 0.000 claims description 17
- 239000002184 metal Substances 0.000 claims description 17
- 238000005187 foaming Methods 0.000 claims description 12
- NBIIXXVUZAFLBC-UHFFFAOYSA-N Phosphoric acid Chemical compound OP(O)(O)=O NBIIXXVUZAFLBC-UHFFFAOYSA-N 0.000 claims description 10
- 238000004026 adhesive bonding Methods 0.000 claims description 10
- 238000001514 detection method Methods 0.000 claims description 6
- 229910000147 aluminium phosphate Inorganic materials 0.000 claims description 5
- 238000013000 roll bending Methods 0.000 claims description 5
- 238000007743 anodising Methods 0.000 claims description 4
- 238000005507 spraying Methods 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 3
- 238000009740 moulding (composite fabrication) Methods 0.000 claims description 3
- 238000009489 vacuum treatment Methods 0.000 claims description 3
- 239000002131 composite material Substances 0.000 abstract description 14
- 238000005520 cutting process Methods 0.000 description 3
- 239000010410 layer Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 239000012792 core layer Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 210000002268 wool Anatomy 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
Abstract
The invention provides a one-time glue-joint curing molding method of an mosaic structure and a shell assembly, which realize one-time glue-joint curing molding of a honeycomb mosaic structure composite material on the premise of meeting glue-joint curing quality and part size after bonding, reduce assembly and glue-joint curing times, can complete production of a honeycomb sandwich mosaic structure only by one-time assembly and one-time glue-joint curing, and have simple operation and easy control of operation process. The problems that the composite material with the double-curvature honeycomb mosaic structure in the prior art needs to be assembled, glued, cured and formed for at least two times, and deformation is difficult to control are solved.
Description
Technical Field
The invention relates to the field of composite materials of aero-engines, in particular to a one-time glue joint curing molding method of an embedded structure and a shell assembly.
Background
The thrust reverser is a device for changing the thrust direction of the engine and mainly plays the roles of decelerating and shortening the running distance. The aluminum honeycomb composite material forms the ducted shell of the thrust reverser, so that the weight is reduced by 40 percent, and the requirements on the smoothness of the inner surface of the ducted body, the specific structural rigidity and the specific strength can be well met. At present, the honeycomb structure composite material cementing, curing and molding component is widely applied to various types of aerospace vehicles. The aluminum honeycomb composite material shell component of the reverse thrust device of the aircraft engine is used as a secondary bearing component, and a plurality of installation devices are embedded in the middle according to bearing requirements.
The following problems exist in the prior art: the insert needs to be glued, cured and formed for multiple times, so that the production period is prolonged, the operation risk is increased, and the cost is increased; the sandwich insert is easy to be displaced, so that the inner skin is warped, and the part is scrapped.
Disclosure of Invention
In view of this, the embodiment of the present invention provides a method for one-time adhesive bonding, curing and molding of an inlaid structure, so as to solve the technical problem in the prior art that the composite material of the inlaid structure needs to be assembled, bonded, cured and molded at least twice, and deformation is difficult to control. The method comprises the following steps:
forming the inner skin, the outer skin and other parts of the sheet metal, performing phosphoric acid anodizing treatment on all the formed sheet metal parts, and spraying primer on the bonding and curing surface;
prefabricating a honeycomb and an insert;
installing the outer skin on a tooling mould for fixing, and paving and sticking the outer skin through the prefabricated honeycomb and the adhesive film to form a paving and sticking piece;
digging out the position of the prefabricated insert on the paving and pasting piece according to the prefabricated sample plate;
placing a prefabricated insert into a preset position on the paving and pasting piece, and filling an adhesive into an interface between the prefabricated insert and the paving and pasting piece;
and placing an adhesive film on the honeycomb of the paving part, and installing an inner skin to obtain the assembled shell assembly.
Further, the prefabricated honeycomb includes:
forming a honeycomb profile by CNC (computer numerical control) machining and roll bending to obtain a prefabricated honeycomb;
or
And cutting the honeycomb by using a sample plate and roll bending and forming to obtain the prefabricated honeycomb.
Further, the prefabricated insert comprises:
paving a layer of adhesive film on a lower backing plate of the insert, placing a prefabricated honeycomb, and pouring foaming adhesive into holes of the prefabricated honeycomb;
and paving an adhesive film on the placed prefabricated honeycomb surface, and placing an upper base plate of the insert to obtain the prefabricated insert.
Further, the prefabricated insert is clamped by the clamp, and the upper backing plate and the lower backing plate of the prefabricated insert are blown by the air gun, so that the lower backing plate, the glue film, the prefabricated honeycomb and the upper backing plate of the prefabricated insert have adhesive force.
Further, will the outer skin is packed into on the frock child and is fixed to carry out outer skin through prefabricated honeycomb and glued membrane and spread and paste, form and spread and paste the piece, include:
the outer skin is arranged on a tooling type tire, and the size of the outer skin is limited and fixed through a positioning block;
pressing the outer skin tightly, and paving an adhesive film on the outer skin;
paving and pasting prefabricated honeycombs on the outer skin on which the adhesive film is paved;
and (4) manufacturing a vacuum bag and vacuumizing to ensure that the prefabricated honeycomb, the adhesive film and the outer skin have adhesive force.
Further, after the interface of the prefabricated insert and the paving piece is filled with the adhesive, the foaming adhesive is filled in the area of the paving piece where the foaming adhesive needs to be filled.
Further, an assembled housing assembly is obtained, comprising:
making a vacuum bag on the assembled shell assembly, and vacuumizing;
transferring the shell assembly subjected to vacuum treatment into an autoclave, and carrying out curing treatment according to preset process parameters;
and taking down the shell assembly subjected to curing treatment from the tooling tire.
Further, the housing assembly is a double curvature assembly.
And further, after the shell assembly subjected to curing treatment is taken down from the tooling tire, carrying out ultrasonic C scanning detection and mechanical property detection on the shell assembly.
Compared with the prior art, the embodiment of the specification adopts at least one technical scheme which can achieve the beneficial effects that at least: the invention provides a one-time assembling, gluing and curing process method for a composite material component of a double-curvature large-diameter honeycomb mosaic structure.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic flow chart of a one-time adhesive bonding molding method according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of a housing assembly of an embodiment of the present invention;
FIG. 3 is a schematic view of a prefabricated insert according to an embodiment of the present invention;
fig. 4 is a schematic size diagram of a housing assembly according to an embodiment of the invention.
Reference numbers in the figures: 1. an inner skin; 2. an outer skin; 3. prefabricating a honeycomb; 4. prefabricating an insert; 5. an upper base plate; 6. and a lower cushion plate.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It should be apparent that the described embodiments are only a few embodiments of the present application, and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.
In an embodiment of the present invention, a one-time glue curing method for forming a damascene structure is provided, as shown in fig. 1, the method includes: step S100: forming the inner skin 1, the outer skin 2 and other parts of sheet metal, performing phosphoric acid anodizing treatment on all sheet metal parts after the sheet metal is formed, and spraying primer on a bonding curing surface; step S200: prefabricated honeycomb 3 and prefabricated insert 4; step S300: the outer skin 2 is arranged on a tooling type tire to be fixed, and the outer skin is paved and pasted through the prefabricated honeycomb 3 and the adhesive film to form a paving and pasting piece; step S400: digging out the position of the prefabricated insert 4 on the paving and pasting piece according to the prefabricated sample plate; step S500: placing a prefabricated insert 4 at a preset position on the paving piece, and filling an adhesive into an interface between the prefabricated insert 4 and the paving piece; step S600: and placing an adhesive film on the honeycomb of the paving and pasting piece, and installing an inner skin 1 to obtain the assembled shell assembly.
The invention provides a one-time assembling, gluing and curing process method for a composite material component of a double-curvature large-diameter honeycomb mosaic structure.
As can be seen from the flow shown in fig. 1, the first embodiment of the present invention specifically includes the following steps:
step S100: forming the inner skin 1, the outer skin 2 and other parts of sheet metal, performing phosphoric acid anodizing treatment on all sheet metal parts after the sheet metal is formed, and spraying primer on a bonding curing surface;
in particular, the assembled shell assembly structure is shown in fig. 2, comprising an inner skin 1, an outer skin 2 and the remaining components. In the one-time gluing, curing, forming and assembling method for the double-curvature honeycomb mosaic structure composite material, metal plate forming is firstly carried out on the inner skin, the outer skin and other parts, and the metal plate forming is a part processing method with expected shape and performance by applying external force to metal wool to cause the metal wool to be plastically deformed or sheared off. After the sheet metal processing, all sheet metal parts are subjected to phosphoric acid anodic oxidation treatment to improve the bonding performance, and then primer is sprayed on the bonding curing surface, preferably, the primer used in this embodiment is J-117 primer. The bonding curing surface is the surface of the outer skin 2 on which the prefabricated honeycomb 2 is to be laid, and in addition, all the rubber materials to be used need to be taken out of a freezing warehouse 6 hours in advance, so that the adhesive film failure and debonding caused by the surface condensed water are prevented.
Step S200: prefabricated honeycomb 3 and prefabricated insert 4;
in specific implementation, the prefabricated honeycomb 3 comprises:
step S210a: forming a honeycomb profile by CNC (computer numerical control) machining and roll bending to obtain a prefabricated honeycomb 3;
or
Step S220a: the honeycomb is cut using a jig and roll-formed to obtain a prefabricated honeycomb 3.
In particular, a honeycomb structure is a sandwich structure having a core layer made up of a series of honeycomb-like cells of hexagonal, quadrilateral or other shape, and having thin face sheets/skins bonded (or brazed) to both the upper and lower surfaces of the core layer. Honeycomb structures have higher strength and stiffness than other forms of sandwich structures. In this embodiment, adopt CNC numerical control processing or manual cutting's mode, utilize raw and other materials honeycomb processing prefabricated honeycomb 3 for the cementing shaping of casing subassembly in this application. Wherein, CNC (computer Numerical Control) Numerical Control processing is carried out to process the honeycomb molded surface, and the prefabricated honeycomb 3 is obtained by roll bending forming; the manual cutting is to cut the raw material honeycomb by using a preset sample plate and roll and bend the raw material honeycomb to obtain the prefabricated honeycomb 3. The preset sample plate is a sample plate manufactured according to the honeycomb shape required by the glue joint molding of the inner skin 1 and the outer skin 2.
In a specific implementation, the prefabricated insert 4 comprises:
step S210b: paving a layer of adhesive film on a lower backing plate 6 of the insert, placing the prefabricated honeycomb 3, and pouring foaming adhesive into holes of the prefabricated honeycomb 3;
step S220b: and paving an adhesive film on the surface of the placed prefabricated honeycomb 3, placing an upper padding plate 5 of the insert, and obtaining the prefabricated insert 4.
In specific implementation, the clamp is used for clamping the prefabricated insert 4, and the air gun is used for blowing the upper cushion plate 5 and the lower cushion plate 6 of the prefabricated insert 4, so that the lower cushion plate 6, the glue film, the prefabricated honeycomb 3 and the upper cushion plate 5 of the prefabricated insert 4 have adhesive force.
Specifically, after obtaining the prefabricated honeycomb 3, the prefabricated insert 4 is fabricated. The prefabricated insert 4 is structured as shown in fig. 3, and comprises an upper cushion plate 5, a prefabricated honeycomb 3 and a lower cushion plate 6. Firstly, a layer of glue film is paved on a lower backing plate 6, a prefabricated honeycomb 3 is placed, the holes of the prefabricated honeycomb 3 are filled with foaming glue, the glue film is paved on the surface of the prefabricated honeycomb 3, and then an upper backing plate 5 of a prefabricated insert 4 is placed. And the prefabricated insert 4 is clamped by a clamp, and the backing plate of the prefabricated insert 4 is blown by a hot air gun, so that a certain adhesive force is formed among the lower backing plate 6, the adhesive film, the honeycomb and the upper backing plate 5, and the prefabricated insert 4 is manufactured.
Step S300: the outer skin 2 is arranged on a tooling type tire to be fixed, and the outer skin is paved and pasted through the prefabricated honeycomb 3 and the adhesive film to form a paving and pasting piece;
in specific implementation, step S300 further includes:
step S310: the outer skin 2 is arranged on a tooling type tire, and the size of the outer skin 2 is limited and fixed through a positioning block;
step S320: compressing the outer skin 2, and paving an adhesive film on the outer skin 2;
step S330: paving prefabricated honeycombs 3 on the outer skin 2 after the adhesive film is paved;
step S340: and (3) manufacturing a vacuum bag and vacuumizing to ensure that the prefabricated honeycomb 3, the adhesive film and the outer skin 2 have adhesive force.
Specifically, the outer skin 2 is loaded on the tooling tire, the peripheral dimension of the outer skin 2 is limited by the positioning blocks, the outer skin 2 is fixed and pressed tightly, the outer skin 2 is tightly attached to the tooling tire, and a glue film is applied to the outer skin 2, preferably, in this embodiment, a J-116A glue film is applied to the outer skin 2. And then paving the prefabricated honeycomb 3 on the outer skin 2 paved with the adhesive film, and manufacturing a vacuum bag for vacuumizing treatment, so that a certain bonding force is formed between the prefabricated honeycomb 3 and the outer skin 2, and the bonding quality is improved.
Step S400: digging out the position of the prefabricated insert 4 on the paving and pasting piece according to the prefabricated sample plate;
step S500: placing a prefabricated insert 4 at a preset position on the paving piece, and filling an adhesive into an interface between the prefabricated insert 4 and the paving piece;
preferably, the adhesive is a J-118 adhesive.
In specific implementation, after the interface between the prefabricated insert 4 and the paving part is filled with the adhesive, the foaming adhesive is filled into the area of the paving part where the foaming adhesive needs to be filled.
Preferably, the foaming glue is J-60 foaming glue.
Step S600: and placing an adhesive film on the honeycomb of the paving and pasting piece, and installing an inner skin 1 to obtain the assembled shell assembly.
Specifically, in this embodiment, the housing assembly is a double-curvature large-diameter housing. Typical components of the housing assembly are shown in fig. 4 with a maximum diameter of 2 meters, a height of 1 meter, and an opening arc of about 150 degrees.
When specifically implementing, after obtaining the assembled casing subassembly, still include:
step S610: manufacturing a vacuum bag for the assembled shell assembly, and vacuumizing;
step S620: transferring the shell assembly subjected to vacuum treatment into an autoclave, and carrying out curing treatment according to preset process parameters;
step S630: and taking down the shell assembly subjected to curing treatment from the tooling type tire.
Specifically, the assembled shell assembly is vacuumized, then the vacuumized assembly is transferred into a hot-pressing tank, and curing treatment is completed according to preset process parameters. And then taking down the shell component from the mould to finish the one-time glue joint curing molding of the composite material with the double-curvature large-diameter honeycomb mosaic structure.
During specific implementation, after the shell assembly subjected to curing treatment is taken down from the tooling tire, ultrasonic C scanning detection and mechanical property detection are carried out on the shell assembly.
The embodiment of the invention realizes the following technical effects:
the assembling method of the double-curvature large-diameter honeycomb mosaic structure composite material provided by the invention realizes one-step glue joint curing molding of the double-curvature honeycomb mosaic structure composite material on the premise of meeting glue joint curing quality and part size after bonding, reduces assembling and glue joint curing times, can complete the production of the honeycomb sandwich mosaic structure only by one-step assembling and one-step glue joint curing, and is simple to operate and easy to control in operation process. The problems that the composite material with the double-curvature honeycomb mosaic structure in the prior art needs to be assembled, glued, cured and formed for at least two times, and deformation is difficult to control are solved.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made to the embodiment of the present invention by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A one-time glue joint curing molding method for an mosaic structure is characterized in that the one-time glue joint curing molding method for the mosaic structure comprises the following steps:
forming the inner skin (1), the outer skin (2) and other parts by sheet metal, performing phosphoric acid anodizing treatment on all sheet metal parts formed by the sheet metal, and spraying primer on a bonding and curing surface;
prefabricated honeycombs (3) and prefabricated inserts (4);
the outer skin (2) is arranged on a tooling type tire to be fixed, and the outer skin is paved and pasted through the prefabricated honeycomb (3) and the adhesive film to form a paving and pasting piece;
digging out the position of the prefabricated insert (4) on the paving part according to the prefabricated sample plate;
placing a prefabricated insert (4) at a preset position on the paving piece, and filling an adhesive into an interface between the prefabricated insert (4) and the paving piece;
and placing an adhesive film on the honeycomb of the paving piece, and installing an inner skin (1) to obtain the assembled shell assembly.
2. The single-stage glue-curing molding method for the mosaic structure according to claim 1, wherein the prefabricated honeycomb (3) comprises:
forming a honeycomb profile by CNC (computer numerical control) machining and roll bending to obtain a prefabricated honeycomb (3); or
The honeycomb is cut by using a template and roll-formed to obtain a prefabricated honeycomb (3).
3. A one-time glue-bonding curing molding method for mosaic structure according to claim 1, wherein said prefabricated mosaic member (4) comprises:
paving a layer of adhesive film on a lower backing plate (6) of the insert, placing the prefabricated honeycomb (3), and pouring foaming adhesive into holes of the prefabricated honeycomb (3);
and paving an adhesive film on the surface of the placed prefabricated honeycomb (3), placing an upper base plate (5) of the insert, and obtaining the prefabricated insert (4).
4. The one-time glue curing molding method of an embedded structure as claimed in claim 3,
the prefabricated insert (4) is clamped by a clamp, and an upper cushion plate (5) and a lower cushion plate (6) of the prefabricated insert (4) are blown by an air gun, so that the lower cushion plate (6), the glue film, the prefabricated honeycomb (3) and the upper cushion plate (5) of the prefabricated insert (4) have adhesive force.
5. The one-time gluing, curing and forming method of the mosaic structure as claimed in claim 1, wherein the outer skin (2) is fixed on a tooling type tire, and the outer skin is paved through the prefabricated honeycomb (3) and the adhesive film to form a paved part, comprising the following steps:
the outer skin (2) is arranged on a tooling type tire, and the outer skin (2) is limited in size and fixed through a positioning block;
compacting the outer skin (2), and paving an adhesive film on the outer skin (2);
paving and pasting prefabricated honeycombs (3) on the outer skin (2) which is paved with the adhesive film;
and (3) manufacturing a vacuum bag and vacuumizing to ensure that the prefabricated honeycomb (3), the adhesive film and the outer skin (2) have adhesive force.
6. The one-time glue curing molding method of an embedded structure as claimed in claim 1,
and after filling the adhesive into the interface between the prefabricated insert (4) and the paving piece, filling foaming glue into the area of the paving piece, which is required to be filled with the foaming glue.
7. The method of claim 1, wherein obtaining the assembled housing assembly comprises:
making a vacuum bag on the assembled shell assembly, and vacuumizing;
transferring the shell assembly subjected to vacuum treatment into an autoclave, and carrying out curing treatment according to preset process parameters;
and taking down the shell assembly subjected to curing treatment from the tooling tire.
8. The one-time glue-bonding curing molding method for an embedded structure as claimed in claim 7, wherein the shell component is a double-curvature component.
9. The one-time gluing, curing and forming method of the mosaic structure according to claim 7, wherein after the shell assembly which is cured is removed from the tooling tire, the shell assembly is subjected to ultrasonic C scanning detection and mechanical property detection.
10. A housing assembly manufactured by using the one-time glue-bonding curing method of any one of the mosaic structures of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211313902.1A CN115596748A (en) | 2022-10-25 | 2022-10-25 | One-time glue joint curing molding method for mosaic structure and shell assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211313902.1A CN115596748A (en) | 2022-10-25 | 2022-10-25 | One-time glue joint curing molding method for mosaic structure and shell assembly |
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| Publication Number | Publication Date |
|---|---|
| CN115596748A true CN115596748A (en) | 2023-01-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211313902.1A Pending CN115596748A (en) | 2022-10-25 | 2022-10-25 | One-time glue joint curing molding method for mosaic structure and shell assembly |
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| Country | Link |
|---|---|
| CN (1) | CN115596748A (en) |
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- 2022-10-25 CN CN202211313902.1A patent/CN115596748A/en active Pending
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