CN115416392A - Glue joint deformation control method for composite material sandwich structure - Google Patents
Glue joint deformation control method for composite material sandwich structure Download PDFInfo
- Publication number
- CN115416392A CN115416392A CN202211158480.5A CN202211158480A CN115416392A CN 115416392 A CN115416392 A CN 115416392A CN 202211158480 A CN202211158480 A CN 202211158480A CN 115416392 A CN115416392 A CN 115416392A
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- Prior art keywords
- composite material
- sandwich structure
- material sandwich
- bonding
- deformation
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Links
- 239000002131 composite material Substances 0.000 title claims abstract description 63
- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000003292 glue Substances 0.000 title claims abstract description 15
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 20
- 230000008569 process Effects 0.000 claims abstract description 13
- 239000002390 adhesive tape Substances 0.000 claims abstract description 4
- 239000011162 core material Substances 0.000 claims description 23
- 239000003365 glass fiber Substances 0.000 claims description 3
- 230000007547 defect Effects 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 4
- 230000005764 inhibitory process Effects 0.000 abstract description 3
- 239000000463 material Substances 0.000 description 7
- 239000006260 foam Substances 0.000 description 4
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000006872 improvement Effects 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000002313 adhesive film Substances 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000007688 edging Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 238000005187 foaming Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000011343 solid material Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/18—Handling of layers or the laminate
- B32B38/1825—Handling of layers or the laminate characterised by the control or constructional features of devices for tensioning, stretching or registration
- B32B38/1833—Positioning, e.g. registration or centering
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B41/00—Arrangements for controlling or monitoring lamination processes; Safety arrangements
Landscapes
- Laminated Bodies (AREA)
Abstract
The invention relates to a method for controlling the gluing deformation of a composite material sandwich structure, which comprises the following steps: placing a support core mold and a positioning stop block at one side of a composite material sandwich structure beam, one side of an end rib and one side of a side rib, placing a slidable limiting block at one side of a rear edge strip of the composite material sandwich structure, bonding the slidable limiting block on a bonding tool through a double-sided adhesive tape, bonding the slidable limiting block to the bonding tool, and performing limiting control on deformation of one side of the rear edge strip of the composite material sandwich structure in the bonding process. The glue joint deformation control method for the composite material sandwich structure can effectively inhibit the glue joint deformation of the composite material sandwich structure, is simple to operate and obvious in effect, does not cause internal glue joint defects caused by excessive inhibition of the appearance, and finally realizes good internal quality and high dimensional accuracy of a part formed by glue joint.
Description
Technical Field
The invention belongs to the technical field of composite material manufacturing, and relates to a method for controlling the gluing deformation of a composite material sandwich structure, which is mainly used for controlling the deformation of a composite material honeycomb or foam sandwich structure in a secondary gluing process.
Background
The composite material has become one of the most important aviation structural materials in the present day due to the advantages of high specific strength, high specific stiffness, strong designability, good fatigue fracture resistance, corrosion resistance, good dimensional stability, convenience for large-area integral forming and the like. The composite material sandwich structure is a structural material with a very large strength-weight ratio, compared with a solid material, the effective material used by the composite material sandwich structure is only 1% -5% of the replaced material, and the composite material sandwich structure is obviously a light material with great potential, low material consumption and low energy consumption. Composite sandwich structures for aviation are generally foam sandwich structures or honeycomb sandwich structures, are commonly used for secondary load-bearing parts such as aircraft elevators, flaperons and the like, and are mainly formed by secondary adhesive bonding in a successful process. In the secondary bonding process, due to the fact that the thermal expansion coefficients of the composite material, the core material, the adhesive film, the foaming adhesive and the like are inconsistent, bonding deformation exists in the finally-formed composite material sandwich structure. At present, the secondary gluing process generally adopts a support core mould and a positioning stop block to inhibit the gluing deformation of a sandwich structure. If the deformation of the supporting core mold and the positioning stop block on the sandwich structure is not sufficiently inhibited, the glue joint deformation greatly affects the assembly and the pneumatic appearance of the final product; if the deformation of the supporting core mold and the positioning stop block on the sandwich structure is inhibited too much, the part is easy to warp in the gluing process, and internal gluing defects such as debonding and the like are easily caused.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides a method for controlling the bonding deformation of a composite material sandwich structure.
The glue joint deformation control method for the composite material sandwich structure can effectively inhibit the glue joint deformation of the composite material sandwich structure, is simple to operate and obvious in effect, does not cause internal glue joint defects caused by excessive inhibition of deformation, and finally realizes good internal quality and high dimensional precision of a part formed by glue joint.
(2) Technical scheme
The embodiment of the invention provides a glue joint deformation control method for a composite material sandwich structure.
Furthermore, the slidable limiting block is made of glass fiber composite materials, the number of the slidable limiting block is n, n = (L-2)/0.8, n is an integer, wherein L is the length of the composite material foam sandwich structure, and the unit is meter.
Furthermore, 5mm-10mm allowance is reserved on the bonding sides of the upper skin and the lower skin of the composite material sandwich structure and the rear edge strip, the same allowance is reserved on the rear edge strip and the skin, and after the composite material foam sandwich structure is bonded and molded, the allowance is removed.
Furthermore, the double-sided adhesive tape is a temperature-resistant adhesive tape, the upper limit of the bonding temperature is not invalid, and the bonding shear strength is between 0.1MPa and 2 MPa.
Further, slidable stopper glue the in-process, can carry out limit control to the deformation of combined material sandwich structure back strake one side, when the deformation stress surpassed the limit and probably resulted in covering and core debonding, the displacement can take place for the slidable stopper, allows the back strake to warp in order to reduce the deformation stress.
(3) Advantageous effects
The method for controlling the gluing deformation of the composite material sandwich structure can effectively inhibit the gluing deformation of the composite material sandwich structure, is simple to operate and obvious in effect, does not cause internal gluing defects caused by excessive inhibition of the appearance, and finally realizes good internal quality and high dimensional precision of a part formed by gluing.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic diagram of the bonding and positioning of the composite sandwich structure of the present invention.
FIG. 2 is a schematic view of the composite sandwich structure skeleton of the present invention.
Figure 3 is an axial cross-section of a composite sandwich structure of the present invention taken along a vertical beam.
In the figure:
1-gluing a tool main body with a composite material sandwich structure; 2-end rib support core mould; 3-the rib supports the mandrel; 4-beam support mandrel; 5-end rib positioning stop blocks; 6-rib positioning stop blocks; 7-beam positioning stops; 8-a slidable stopper; 9-composite sandwich construction; 10-end ribs; 11-a rib; 12-a beam; 13-back edging; 14-a core material; 15-upper covering; 16-lower skin.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention, but are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, alterations and improvements in the parts, components and connection means, without departing from the spirit of the invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1, the composite sandwich structure 9 is composed of an upper skin 15, a lower skin 16, end ribs 10, side ribs 11, a beam 12, a rear edge bar 13, and a core material 14. In the gluing process, the end rib supporting core mold 2, the edge rib supporting core mold 3 and the beam supporting core mold 4 are respectively arranged on the inner molded surfaces of the end rib 10, the edge rib 11 and the beam 12 of the composite material sandwich structure and are used for supporting the inner molded surfaces of parts. The end rib positioning stop 5, the side rib positioning stop 6 and the beam positioning stop 7 are respectively tightly attached to the end rib supporting core mold 2, the side rib supporting core mold 3 and the beam supporting core mold 4 and used for positioning the end rib 10, the side rib 11 and the beam 12 in the gluing process. The slidable limiting block 8 is mounted on the outer side of the rear edge strip 13 of the composite material sandwich structure through double-sided tape adhesion and used for positioning the rear edge strip of the composite material sandwich structure 9.
The innovation point of the scheme of the invention is that in the process of gluing, the slidable limiting block 8 can limit and control the deformation of one side of the rear edge strip 13 of the composite material sandwich structure 9 and can slide to a certain extent along the original limiting direction so as to ensure the internal quality of gluing. In the process of gluing the composite material sandwich structure 9, when the deformation stress of the part caused by different thermal expansion coefficients exceeds a limit, if the slidable limiting block 8 is immovable like the end rib positioning block 5, the edge rib positioning block 6 and the beam positioning block 7, deformation and warpage of the upper skin 15, the lower skin 16 or the beam 12 may occur, so that the upper skin 15, the lower skin 16 or the beam 12 and the core material 14 have debonding defects. Therefore, when the part exceeds a limit because of the different deformation stress that causes of thermal expansion coefficient, the slidable stopper 8 can follow the slip of former spacing direction and carry out certain degree, after slidable stopper 8 takes place to slide, when the part because of the different deformation stress that causes of thermal expansion coefficient reduces because of the part warp, when the bonding strength of slidable stopper 8 and part deformation stress reach balanced, slidable stopper 8 no longer slides. When the slidable limiting block 8 does not slide any more, the composite material sandwich structure 9 is prevented from being bonded and deformed.
Optionally, in this embodiment, the double-sided tape is a temperature-resistant tape, failure does not occur at the upper limit of the bonding temperature, and the bonding shear strength is between 0.1MPa and 2 MPa.
Optionally, in this embodiment, the slidable stopper 8 is made of a glass fiber composite material, and the number of the slidable stopper is n, where n = (L-2)/0.8, n is an integer, where L is the length of the composite sandwich structure and is measured in meters.
Specifically, the number of the required slidable limiting blocks 8 can be calculated according to the formula so as to adapt to composite sandwich structures with different lengths.
Optionally, in this embodiment, a margin of 5mm to 10mm is reserved on the side where the upper skin 15 and the lower skin 16 of the composite sandwich structure are bonded to the back edge strip 13, the same margin is reserved on the back edge strip 13, and the margin is removed after the composite sandwich structure is bonded and molded.
Specifically, after the composite material sandwich structure 9 is glued and molded, the slidable limiting block 8 may slip due to excessive deformation stress, so that the rear edge strip 13 of the composite material sandwich structure may deform to some extent. Because the slidable limiting block 8 is arranged at every 0.8m, the rear edge strip 13 of the longer composite material sandwich structure 9 with the length exceeding 4m after being glued can be in an S shape, and the allowance of 5mm-10mm in the width direction of the rear edge strip is removed at the moment, so that the appearance precision of the formed composite material sandwich structure 9 is ensured.
It should be clear that the embodiments in this specification are described in a progressive manner, and the same or similar parts between the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the drawings. Also, a detailed description of known process techniques is omitted herein for the sake of brevity.
The above description is only an example of the present application and is not limited to the present application. Numerous modifications and variations could be made to the present disclosure by those skilled in the art without departing from the scope of the present disclosure. Any modification, equivalent replacement, improvement or the like made within the spirit and principle of the present application shall be included in the scope of the claims of the present application.
Claims (5)
1. A glue joint deformation control method for a composite material sandwich structure is characterized in that in the glue joint process, an end rib supporting core mold (2), an edge rib supporting core mold (3) and a beam supporting core mold (4) are respectively arranged on inner molded surfaces of the composite material sandwich structure end rib (10), the edge rib (11) and the beam (12) and are used for supporting inner molded surfaces of parts, wherein the composite material sandwich structure (9) comprises an upper skin (15), a lower skin (16), an end rib (10), an edge rib (11), the beam (12), a rear edge strip (13) and a core material (14); the end rib positioning stop block (5), the side rib positioning stop block (6) and the beam positioning stop block (7) are respectively tightly attached to the end rib supporting core mold (2), the side rib supporting core mold (3) and the beam supporting core mold (4) and are used for positioning the end rib (10), the side rib (11) and the beam (12) in the gluing process; the slidable limiting block (8) is mounted on the outer side of the rear edge strip (13) of the composite material sandwich structure through double-sided adhesive tape adhesion and used for positioning the rear edge strip of the composite material sandwich structure (9).
2. The method for controlling the adhesive bonding deformation of the composite material sandwich structure according to claim 1, wherein the slidable stopper (8) is made of glass fiber composite material, the number of the slidable stopper is n, n = (L-2)/0.8, n is an integer, wherein L is the length of the composite material sandwich structure, and the unit is meter.
3. The bonding deformation control method for the composite material sandwich structure according to claim 1, wherein a margin of 5mm to 10mm is reserved on the bonding side of the upper skin (15) and the lower skin (16) of the composite material sandwich structure and the back edge strip (13), a same margin is reserved on the back edge strip (13), and after the composite material sandwich structure is bonded and molded, the margin is removed.
4. The bonding deformation control method for the sandwich structure of the composite material according to claim 1, wherein the double-sided tape is a temperature-resistant tape, the upper limit of the bonding temperature does not fail, and the bonding shear strength is between 0.1MPa and 2 MPa.
5. The bonding deformation control method for the composite material sandwich structure according to claim 1, wherein the slidable stopper (8) can perform limit control on deformation of one side of the rear edge strip (13) of the composite material sandwich structure during bonding, and when the deformation stress exceeds a limit, which may cause the upper skin (15) or the lower skin (16) to be debonded from the core material (14), the slidable stopper (8) can be displaced, so as to allow the rear edge strip (13) to be deformed to reduce the deformation stress.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211158480.5A CN115416392A (en) | 2022-09-22 | 2022-09-22 | Glue joint deformation control method for composite material sandwich structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211158480.5A CN115416392A (en) | 2022-09-22 | 2022-09-22 | Glue joint deformation control method for composite material sandwich structure |
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| Publication Number | Publication Date |
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| CN115416392A true CN115416392A (en) | 2022-12-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211158480.5A Pending CN115416392A (en) | 2022-09-22 | 2022-09-22 | Glue joint deformation control method for composite material sandwich structure |
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