Method and mold for splicing multiple layers of longitudinal and transverse honeycomb cores

Abstract

The invention relates to the technical field of honeycomb core splicing, in particular to a method and mold for splicing multiple layers of longitudinal and transverse honeycomb cores, and the method comprises the following steps: cleaning honeycomb cores to be spliced; ironing a layer of polystyrene foam on the splicing surface of one honeycomb core in the honeycomb cores to be spliced, and laying a layer of transparent nonporous isolating membrane on the splicing surface ironed with the polystyrene foam to wrap the polystyrene foam; the honeycomb cores needing to be spliced are assembled to a splicing mold, a layer of porous isolation cloth is laid on the upper surface of each honeycomb core, and foaming space is limited and pressure is transmitted through the splicing mold; checking in the autoclave; after verification, observing indentation conditions on the polystyrene foam and the non-porous isolating membrane on the splicing surfaces, and determining a gap between the splicing surfaces; whether the polystyrene foam needs to be checked again or directly assembled and cured is determined according to the indentation; the ironing temperature and the checking temperature are both lower than the polystyrene foam curing temperature; by means of the splicing method and the mold, the problem that the splicing quality of the multiple layers of honeycomb cores is poor can be effectively solved.

Description

Technical Field

[0001] The present invention relates to the technical field of honeycomb core splicing, and particularly to a method and a mold for splicing multiple layers of honeycomb cores longitudinally and transversely. Background Art

[0002] The composite honeycomb core sandwich structure is a commonly used composite adhesive structure, and is also a known adhesive structure that saves the most materials and has the largest strength-to-weight ratio. Therefore, the composite honeycomb core sandwich structure is widely used in structures such as fuselages and ailerons. With the increasing demand for the functional diversity of honeycomb core sandwich structures in the aerospace field, the number and types of honeycomb cores in composite honeycomb core sandwich structures are constantly increasing, and various honeycomb cores need to be spliced into a whole. Usually, foaming glue is filled between the honeycomb cores for splicing.

[0003] In the prior art, a Chinese invention patent document with a publication number of CN103589349A and a publication date of February 19, 2014 was proposed. The technical solution disclosed in this patent document is as follows: A honeycomb core splicing method, the steps are as follows: Insert strip-shaped foaming glue that meets the specified strength requirements between the honeycomb core groups of the honeycomb core sandwich panel or between the honeycomb core and the frame skeleton. The foaming glue expands when heated under the high-temperature state of hot pressing the board, and is synchronously hot-pressed and cured with the adhesive or adhesive film during the board-making process, and the butted honeycomb core groups or the honeycomb core and the frame skeleton are bonded into one body.

[0004] In the prior art, a Chinese invention patent document with a publication number of CN110103483A and a publication date of August 9, 2019 was also proposed. The technical solution disclosed in this patent document is as follows: A honeycomb core splicing method, including an overall splicing method and a trapezoidal distribution of the adhesive; the overall splicing method is to place all the composite materials and honeycomb core components that need to be spliced between the upper and lower composite panels, insert the adhesive in the middle, and complete the hot pressing and curing in one go into the tank; the trapezoidal density adhesive refers to setting the adhesive density as a corresponding trapezoidal distribution according to the thermal expansion coefficients of the two side materials and the interface temperature distribution, so as to alleviate the problem of honeycomb core cracking or deformation caused by thermal stress at the splicing interface.

[0005] The honeycomb cores of the above two technical solutions are limited by the width or the butt joint of two different specifications of honeycomb cores in the width direction (the splicing of the core cells longitudinally), and the splicing surfaces are all perpendicular to the honeycomb core cells.

[0006] In the prior art, a Chinese invention patent document with a publication number of CN117565406A and a publication date of February 20, 2024 was also proposed. The technical solution disclosed in this patent document is as follows: A method for bonding an aluminum alloy skin and a honeycomb core. The chemically milled aluminum alloy skin and the milled honeycomb core are pre-assembled to determine the matching degree between the aluminum alloy skin and the honeycomb core; the aluminum alloy skin and the honeycomb core whose matching degree meets the bonding requirements are subjected to a check film test to detect the fit clearance between the aluminum alloy skin and the honeycomb core; a layer of adhesive film is laid on the bonding surface of the aluminum alloy skin, and the adhesive film is compensated in the area where the fit clearance is greater than the thickness of the adhesive film; a layer of foaming adhesive is laid along the chemical milling step of the aluminum alloy skin so that the foaming adhesive covers the entire chemical milling step; the honeycomb core is assembled and fitted onto the aluminum alloy skin and cured in a autoclave.

[0007] The above technical solution only involves the verification of the horizontal honeycomb core and the skin. Due to the continuous improvement of aircraft performance, the structure of composite material parts is becoming more and more complex. To meet the requirements of complex composite material part structures, the vertical splicing of the honeycomb core in the longitudinal direction of the honeycomb sandwich structure can no longer meet the requirements. The honeycomb core not only has horizontal splicing but also has horizontal splicing parallel to the core cell direction, and the longitudinal splicing is not all perpendicular to the direction of the honeycomb, but has a certain angle. Therefore, the complex honeycomb sandwich structure includes the splicing of multiple layers of honeycomb cores in the longitudinal and horizontal directions. In the splicing of multiple layers of honeycomb cores including horizontal and longitudinal directions, because there are multiple splicing surfaces and the splicing surfaces are not perpendicular to the honeycomb core cells but have a certain angle, when foaming multiple layers of honeycombs, the honeycomb cores with horizontal splicing below (including non-perpendicular splicing) cannot transmit pressure during foaming, and the foaming space is large. The foaming adhesive foams in the large space and is not dense, with many foaming adhesive voids or delamination, which affects the quality of the honeycomb splicing parts. Moreover, the expansion of the foaming adhesive also affects the shape of the honeycomb splicing parts, seriously affecting the product quality.

[0008] Furthermore, even though the technical solution of CN117565406A discloses a verification process for checking the clearance between the aluminum alloy skin and the aluminum honeycomb core through an adhesive film, this verification process is mainly applied in structural bonding. In the bonding of composite material structures, for example, the clearance between the skin and the honeycomb core is relatively small, usually less than 0.35mm. Therefore, using verification is a good method for detecting the clearance and is a commonly used process method in the bonding of composite material structure adhesives. However, the clearance between honeycomb cores is at least more than 1mm, and the existing splicing between honeycomb cores is horizontal and perpendicular to the honeycomb core cells. Based on this characteristic, the splicing of honeycomb cores does not require a verification process, and the clearance between honeycomb cores can be directly filled with foaming adhesive. Summary of the Invention

[0009] To solve the above technical problems, the present invention provides a method and a mold for splicing multi-layer honeycomb cores in the longitudinal and transverse directions, which can effectively solve the problem of poor splicing quality of multi-layer honeycomb cores.

[0010] The present invention is realized by adopting the following technical solutions: A method for splicing multi-layer honeycomb cores in the longitudinal and transverse directions, comprising the following steps: Step S 1 . Clean the honeycomb cores to be spliced; Step S 2 . Iron a layer of foaming glue on the splicing surface of one of the honeycomb cores to be spliced, and the ironing temperature is lower than the curing temperature of the foaming glue; Step S 3 . Lay a layer of transparent non-porous isolation film on the splicing surface where the foaming glue is ironed to wrap the foaming glue, and fix the non-porous isolation film on the honeycomb core; Step S 4 . Assemble the honeycomb cores to be spliced onto the splicing mold, and lay a layer of porous isolation cloth on the upper surface of the honeycomb cores, and limit the foaming space and transfer pressure through the splicing mold; Step S 5 . Enclose the assembled honeycomb cores in a vacuum bag, and perform calibration in a autoclave, and the calibration temperature is lower than the curing temperature of the foaming glue; Step S 6 . Take out of the autoclave and remove the assembled honeycomb cores; Step S 7 . Observe the indentation on the foaming glue and the non-porous isolation film on the splicing surface to determine the gap of the splicing surface; Step S 8 . If the indentation is obvious and the indentation of all honeycomb cores is clearly visible on the non-porous isolation film and the foaming glue, iron another layer of foaming glue on the splicing surface where the foaming glue is not laid, repeat Step S 4 , and re-enclose it in the vacuum bag and put it into the autoclave to cure the foaming glue to complete the splicing of the honeycomb cores; if the indentation is not obvious, iron a layer of foaming glue on the splicing surface where the foaming glue is not laid, and then isolate the foaming glue on the two splicing surfaces with a transparent non-porous isolation film, repeat Step S 4 ~Step S 8 , until the splicing of the honeycomb cores is completed.

[0011] The said Step S 2 Specifically refers to: lay a layer of foaming glue on the splicing surface of one of the honeycomb cores to be spliced, then lay a release cloth on the foaming glue, iron the foaming glue into the honeycomb core, and no foaming glue is needed on the splicing surface of the other honeycomb core to be spliced; operate according to this, and iron a layer of foaming glue on the splicing surface of one of all the honeycomb cores to be spliced.

[0012] The ironing temperature is 60°C.

[0013] Use an electric iron to iron the foaming agent into the honeycomb core.

[0014] The thickness of one layer of foaming agent is 1 mm or 1.5 mm.

[0015] The calibration temperature is 60°C.

[0016] A mold including longitudinally and transversely multi-layered honeycomb core splicing, comprising a tooling template, a cover plate, and stoppers detachably arranged around the tooling template. The profile formed by enclosing the stoppers is the theoretical profile of the spliced honeycomb core; a demolding cloth is also laid on the surface of the tooling template.

[0017] A positioning member is further provided between the tooling template and the stoppers.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. By ironing the foaming agent on one side of the splicing surface and performing calibration in a hot press at a low temperature to determine the gap of the splicing surface, and at the same time using a splicing mold to ensure the tight assembly between all spliced honeycomb cores during calibration and curing, restricting the foaming space, the present invention not only ensures the splicing quality of the longitudinally and transversely multi-layered honeycomb cores, avoiding defects such as debonding and voids, but also ensures the splicing shape of the spliced honeycomb cores, improving the product quality.

[0019] Specifically, the present invention takes into account that there are multiple splicing surfaces in the multi-layer honeycomb core. When the honeycomb core spliced horizontally below is foamed, the pressure cannot be transmitted, the foaming space is large, the foaming agent foams in the large space, and the foaming is not dense. There are many voids or debonding of the foaming agent, which affects the quality of the honeycomb core splicing parts. Based on this, the present invention innovatively adopts verification in the splicing between honeycomb cores, so that the present invention includes the detection of gaps in both horizontal and vertical directions, and then splicing and curing. Traditional composite material verification, such as the comparative document with the publication number CN117565406A, is used between the skin and the honeycomb core. And the traditional composite material verification uses a verification film, and the thickness of the commonly used verification film is generally 0.3 mm, and the verification film basically has no fluidity, and it is difficult to reflect the gap between honeycomb cores. On the contrary, the present invention does not use a verification film to check the gap of the splicing surface, but uses the characteristics of the foaming agent itself, and directly uses the foaming agent as a verification film to check the gap between the spliced honeycomb cores. The foaming agent softens at a temperature lower than the curing temperature of the foaming agent, has a certain fluidity, and micro-foams, and can truly reflect the gap situation between honeycomb cores. And a special splicing mold is adopted to ensure the tight combination between all spliced honeycomb cores during verification and curing, limit the foaming space, improve the foaming quality, and solve the problem of unqualified splicing quality between multi-layer and multi-piece honeycomb cores including vertical and horizontal directions.

[0020] 2. The ironing temperature and the verification temperature are 60 °C, and the curing temperature of the foaming agent is 180 °C. At 60 °C, the foaming agent only micro-foams, and the foaming amount is about 1 / 3 of the fully cured foaming. For example, the thickness of a layer of 1 mm thick foaming agent after curing is 3 mm when it is densely foamed, but at 60 °C, the thickness of a layer of 1 mm thick densely foamed is about 1 mm. At the verification temperature, the foaming agent does not fully foam to the theoretical thickness, that is, the thickness of the foaming agent ironed and pasted will increase during subsequent curing, making the splicing quality of multi-layer honeycomb cores including vertical and horizontal directions better.

[0021] 3. In the present invention, the foaming agent filled between the spliced honeycomb cores has two specifications of 1 mm and 1.5 mm in thickness, so that the gap detection effect is better.

[0022] 4. This splicing mold has a simple structure and is convenient to use.

[0023] 5. Through the setting of the positioning member, the stopper can be installed quickly and accurately. Description of the Drawings

[0024] The following will further elaborate on the present invention in conjunction with the specification drawings and specific embodiments, where: Figure 1 is a schematic diagram of the honeycomb core verification and assembly in the present invention; Figure 2Schematic diagram of the structure of the splicing mold in the present invention; Figure 3 Schematic diagram of the splicing and curing assembly of the honeycomb core in the present invention; Figure 4 Schematic diagram of the second verification assembly of the honeycomb core in the present invention; Markings in the figure: 1. Tooling template, 2. Stop block, 3. Locating pin, 4. Mushroom pin, 5. Release cloth, 6. Honeycomb core I, 7. Honeycomb core II, 8. Honeycomb core III, 9. Honeycomb core IV, 10. Foaming adhesive, 11. Non-porous isolation film, 12. Cover plate, 13. Porous isolation cloth. Detailed implementation mode

[0025] Embodiment 1 As a basic implementation mode of the present invention, the present invention includes a method for splicing longitudinal and transverse multi-layer honeycomb cores, comprising the following steps: Step S 1 . Clean the honeycomb core to be spliced.

[0026] Step S 2 . Iron a layer of foaming adhesive 10 on the splicing surface of one of the honeycomb cores to be spliced, and the ironing temperature is lower than the curing temperature of the foaming adhesive 10.

[0027] Step S 3 . Lay a layer of transparent non-porous isolation film 11 on the splicing surface where the foaming adhesive 10 is ironed to wrap the foaming adhesive 10, and fix the non-porous isolation film 11 on the honeycomb core.

[0028] Step S 4 . Assemble the honeycomb cores to be spliced onto the splicing mold, and lay a layer of porous isolation cloth 13 on the upper surface of the honeycomb core to limit the foaming space and transfer pressure through the splicing mold.

[0029] Step S 5 . Seal the assembled honeycomb core in a vacuum bag and perform verification in a autoclave, and the verification temperature is lower than the curing temperature of the foaming adhesive 10.

[0030] Step S 6 . Take out of the autoclave and remove the assembled honeycomb core.

[0031] Step S 7 . Observe the indentation on the foaming adhesive 10 and the non-porous isolation film 11 on the splicing surface to determine the gap of the splicing surface.

[0032] Step S 8 . If the indentation is obvious and the indentations of all honeycomb cores are clearly visible on the non-porous isolation film 11 and the foaming adhesive 10, then iron another layer of foaming adhesive 10 on the splicing surface where the foaming adhesive 10 is not laid, and repeat step S4 , and re-seal it in a vacuum bag, and cure the foam adhesive 10 in a hot press autoclave to complete the splicing of the honeycomb core. If the indentation is not obvious, iron a layer of foam adhesive 10 on the splicing surface where the foam adhesive 10 is not laid, and then isolate the foam adhesive 10 on the two splicing surfaces with a transparent non-porous isolation film 11, and repeat step S 4 ~step S 8 , until the splicing of the honeycomb core is completed.

[0033] Example 2 As a preferred embodiment of the present invention, the present invention includes a method for splicing multi-layer honeycomb cores longitudinally and transversely, including the following steps: Step S 1 . Clean the honeycomb core to be spliced.

[0034] Step S 2 . Iron a layer of foam adhesive 10 on the splicing surface of one of the honeycomb cores to be spliced, and the ironing temperature is lower than the curing temperature of the foam adhesive 10. Specifically, lay a layer of foam adhesive 10 on the splicing surface of one of the honeycomb cores to be spliced, then lay a release cloth 5 on the foam adhesive 10, and iron the foam adhesive 10 into the honeycomb core. The splicing surface of the other honeycomb core to be spliced does not require the foam adhesive 10. Operate in this way to iron a layer of foam adhesive 10 on the splicing surface of each of the honeycomb cores to be spliced. The thickness of a layer of foam adhesive 10 is 1 mm or 1.5 mm.

[0035] Step S 3 . Lay a layer of transparent non-porous isolation film 11 on the splicing surface where the foam adhesive 10 is ironed to wrap the foam adhesive 10, and fix the non-porous isolation film 11 on the honeycomb core.

[0036] Step S 4 . Assemble the honeycomb cores to be spliced onto the splicing mold, and lay a layer of perforated isolation cloth 13 on the upper surface of the honeycomb core to limit the foaming space and transfer pressure through the splicing mold.

[0037] Step S 5 . Seal the assembled honeycomb core in a vacuum bag and perform calibration in a hot press autoclave, and the calibration temperature is lower than the curing temperature of the foam adhesive 10.

[0038] Step S 6 . Take out of the hot press autoclave and take out the assembled honeycomb core.

[0039] Step S 7 . Observe the indentation on the foam adhesive 10 and the non-porous isolation film 11 on the splicing surface to determine the gap of the splicing surface.

[0040] Step S 8. If the indentations are obvious and clearly visible on the non-porous isolation film 11 and the foaming adhesive 10 for all honeycomb cores, then iron another layer of foaming adhesive 10 on the splicing surface where the foaming adhesive 10 has not been laid, repeat step S 4 , and re-seal it in a vacuum bag, put it into a hot press autoclave to cure the foaming adhesive 10, and complete the splicing of the honeycomb core. If the indentations are not obvious, then iron a layer of foaming adhesive 10 on the splicing surface where the foaming adhesive 10 has not been laid, and then isolate the foaming adhesive 10 on the two splicing surfaces with a transparent non-porous isolation film 11, repeat step S 4 ~step S 8 , until the splicing of the honeycomb core is completed.

[0041] Embodiment 3 As another preferred embodiment of the present invention, the present invention includes a mold for splicing longitudinal and transverse multi-layer honeycomb cores, including a tooling template 1, a cover plate 12, and a stop block 2 detachably arranged around the tooling template 1. The profile formed by enclosing the stop block 2 is the theoretical profile of the spliced honeycomb core. A release cloth 5 is also laid on the surface of the tooling template 1. When this splicing mold needs to be used, fix the stop blocks 2 in three directions on the tooling template 1, and leave one stop block 2 unfixed. Assemble each honeycomb core to be spliced onto the tooling template 1. After assembly, assemble the previously unassembled stop block 2 onto the tooling template 1 and fix it. Lay a layer of porous isolation cloth 13 on the upper surface of the honeycomb core, and then assemble the cover plate 12 onto the tooling to limit the foaming space of the foaming adhesive 10 and transmit pressure.

[0042] Embodiment 4 As the best embodiment of the present invention, the present invention includes a mold for splicing longitudinal and transverse multi-layer honeycomb cores, referring to the attached Figure 2 to the specification, including a tooling template 1, a cover plate 12, and a stop block 2 detachably arranged around the tooling template 1 through a mushroom pin 4. The number of stop blocks 2 is four, and the profile formed by enclosing the four stop blocks 2 is the theoretical profile of the spliced honeycomb core. A release cloth 5 is also laid on the surface of the tooling template 1. Among them, a positioning member is also provided between the tooling template 1 and the stop block 2. The positioning member can be a positioning pin 3.

[0043] Based on the above splicing mold, the present invention also includes a method for splicing longitudinal and transverse multi-layer honeycomb cores, including the following steps: Step S 1 . Clean the honeycomb cores to be spliced. In this embodiment, there are a total of four honeycomb cores to be spliced, namely honeycomb core I 6, honeycomb core II 7, honeycomb core III 8, and honeycomb core IV 9. Wash the splicing surfaces of the honeycomb cores to be spliced until they are clean.

[0044] Step S 2. Lay a layer of foaming glue 10 on the splicing surface of one of the honeycomb cores to be spliced, then lay a release cloth 5 on the foaming glue 10, heat an electric iron to about 60 °C, and iron the foaming glue 10 into the honeycomb core with the electric iron. There is no need for foaming glue 10 on the splicing surface of the other honeycomb core to be spliced. Specifically, the ironing temperature is 60 °C, and the curing temperature of the foaming glue 10 is 180 °C. At 60 °C, the foaming glue 10 only undergoes micro-foaming. For example, the thickness of a layer of 1 mm thick foaming glue 10 after curing is 3 mm when densely foamed, but at 60 °C, the thickness of a layer of 1 mm thick when densely foamed is about 1 mm. At this temperature, the foaming glue 10 does not fully foam to the theoretical thickness.

[0045] Refer to the attached instructions Figure 1 , specifically, iron the foaming glue 10 on the honeycomb core II 7 on the splicing surface between the honeycomb core I 6 and the honeycomb core II 7, iron the foaming glue 10 on the honeycomb core IV 9 on the splicing surface between the honeycomb core I 6 and the honeycomb core IV 9, iron the foaming glue 10 on the honeycomb core IV 9 on the splicing surface between the honeycomb core II 7 and the honeycomb core IV 9, iron the foaming glue 10 on the honeycomb core III 8 on the splicing surface between the honeycomb core II 7 and the honeycomb core III 8, and iron the foaming glue 10 on the honeycomb core III 8 on the splicing surface between the honeycomb core III 8 and the honeycomb core IV 9.

[0046] Step S 3 . Lay a layer of transparent non-porous isolation film 11 on the splicing surface where the foaming glue 10 has been ironed to wrap the foaming glue 10, and fix the non-porous isolation film 11 on the corresponding honeycomb core.

[0047] Step S 4 . Clean the splicing mold, set stoppers 2 around the tooling template 1. The stoppers 2 are positioned by positioning pins 3 and mushroom pins 4. The profiled surface positioned by the four stoppers 2 around is the theoretical profiled surface of the spliced honeycomb core. Lay a layer of release cloth 5 on the surface of the tooling template 1, and then fix three of the stoppers 2 around the tooling template 1 with positioning nails and mushroom pins 4 on the tooling template 1, leaving one stopper 2 unfixed.

[0048] Assemble each honeycomb core to be spliced onto the splicing mold. Specifically, after assembling each honeycomb core to be spliced onto the tooling template 1, assemble the previously unassembled stopper 2 onto the tooling template 1 and fix it, and lay a layer of porous isolation cloth 13 on the upper surface of the honeycomb core to limit the foaming space and transfer pressure through the splicing mold.

[0049] Step S 5. Enclose the assembled honeycomb core in a vacuum bag and conduct verification in an autoclave. The verification temperature is lower than the curing temperature of the foaming adhesive 10. Specifically, the verification temperature is 60°C, and the curing temperature of the foaming adhesive 10 is 180°C. At 60°C, the foaming adhesive 10 only undergoes micro-foaming, and at the verification temperature, the foaming adhesive 10 does not fully foam to the theoretical thickness.

[0050] Step S 6 . Take out of the autoclave, remove the auxiliary materials, remove the cover plate 12 and one of the stoppers 2, and take out the assembled honeycomb core.

[0051] Step S 7 . Observe the indentation on the foaming adhesive 10 and the non-porous isolation film 11 on the splicing surface to determine the gap of the splicing surface.

[0052] Step S 8 . If the indentation is obvious and the indentations of all honeycomb cores are clearly visible on the non-porous isolation film 11 and the foaming adhesive 10, refer to the appendix of the specification Figure 3 , then iron another layer of foaming adhesive 10 on the splicing surface where the foaming adhesive 10 is not laid, repeat Step S 4 , and re-enclose it in the vacuum bag and put it into the autoclave to cure the foaming adhesive 10 to complete the splicing of the honeycomb core.

[0053] If the indentation is not obvious, refer to the appendix of the specification Figure 4 , then iron a layer of foaming adhesive 10 on the splicing surface where the foaming adhesive 10 is not laid, and then isolate the foaming adhesive 10 on the two splicing surfaces with a transparent non-porous isolation film 11, repeat Step S 4 ~Step S 8 , and decide whether the foaming adhesive 10 needs to be verified again according to the indentation, or directly assemble and cure until the splicing of the honeycomb core is completed.

[0054] In summary, after those of ordinary skill in the art read the documents of the present invention, all other corresponding transformation schemes that can be made without creative mental labor according to the technical solutions and technical concepts of the present invention fall within the scope protected by the present invention.

Claims

1. A method for longitudinal and transverse multi-layer honeycomb core splicing, characterized in that: The following steps are involved: Step S1. Cleaning the honeycomb core to be spliced; Step S2. ironing a layer of foam glue (10) on the splicing surface of one of the honeycomb cores to be spliced, wherein the ironing temperature is lower than the curing temperature of the foam glue (10); Step S3. Laying a layer of transparent non-porous isolation film (11) on the joint surface of the ironed foam glue (10) to wrap the foam glue (10), and fixing the non-porous isolation film (11) on the honeycomb core; Step S4. Assembling the honeycomb cores to be spliced ​​onto a splicing mold, and laying a layer of porous isolation cloth (13) on the upper surface of the honeycomb core, so as to limit the foaming space and transmit pressure through the splicing mold; Step S5. The assembled honeycomb core is packaged in a vacuum bag and calibrated in an autoclave, where the calibration temperature is lower than the curing temperature of the foam glue (10); Step S6. Exit the autoclave and take out the assembled honeycomb core; Step S7. Observe the indentations on the foam glue (10) and the non-porous isolation film (11) on the splicing surface to determine the gap between the splicing surfaces; Step S8. If the indentation is obvious and the indentations of all honeycomb cores are clearly visible on the non-porous isolation film (11) and the foam glue (10), then iron another layer of foam glue (10) on the splicing surface where the foam glue (10) is not laid, repeat step S4, and re-package it into a vacuum bag, put it into an autoclave to cure the foam glue (10), and complete the splicing of the honeycomb core; if the indentation is not obvious, iron a layer of foam glue (10) on the splicing surface where the foam glue (10) is not laid, and then use a transparent non-porous isolation film (11) to isolate the foam glue (10) on the two splicing surfaces, and repeat steps S4 to S8 until the splicing of the honeycomb core is completed.

2. A method for splicing multi-layer honeycomb cores in longitudinal and transverse directions according to claim 1, characterized in that: The step S2 specifically includes: laying a layer of foam glue (10) on the splicing surface of one of the honeycomb cores to be spliced, then laying a demoulding cloth (5) on the foam glue (10), and ironing the foam glue (10) into the honeycomb core, and no foam glue (10) is required on the splicing surface of another honeycomb core to be spliced; according to this operation, a layer of foam glue (10) is ironed on the splicing surface of one of the honeycomb cores in all the honeycomb cores to be spliced.

3. A method for longitudinal and transverse multi-layer honeycomb core splicing according to claim 1, characterized in that: The ironing temperature is 60°C.

4. A method for longitudinal and transverse multi-layer honeycomb core splicing according to claim 3, characterized in that: The foam glue (10) is ironed into the honeycomb core using an electric iron.

5. A method for longitudinal and transverse multi-layer honeycomb core splicing according to claim 1, characterized in that: The thickness of the layer of foam glue (10) is 1 mm or 1.5 mm.

6. A method for longitudinal and transverse multi-layer honeycomb core splicing according to claim 1, characterized in that: The calibration temperature is 60°C.

7. A mold for the method of splicing multi-layer honeycomb cores in longitudinal and transverse directions as claimed in any one of claims 1 to 6, characterized in that: It comprises a tooling template (1), a cover plate (12), and stoppers (2) detachably arranged around the tooling template (1), wherein the profile formed by the stoppers (2) is a theoretical profile of the honeycomb core after splicing; The surface of the tooling template (1) is also covered with a demoulding cloth (5).

8. A mold for a method for longitudinal and transverse multi-layer honeycomb core splicing according to claim 7, characterized in that: A positioning piece is also provided between the tooling template (1) and the stopper (2).

Images