CN110744872B - Composite material honeycomb sandwich structure and foaming glue filling method used in same - Google Patents
Composite material honeycomb sandwich structure and foaming glue filling method used in same Download PDFInfo
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- CN110744872B CN110744872B CN201911065654.1A CN201911065654A CN110744872B CN 110744872 B CN110744872 B CN 110744872B CN 201911065654 A CN201911065654 A CN 201911065654A CN 110744872 B CN110744872 B CN 110744872B
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- composite material
- foaming
- sandwich structure
- foaming adhesive
- filling
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- 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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
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- 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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
- B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
Abstract
The invention relates to the technical field of composite material manufacturing, in particular to a composite material honeycomb sandwich structure and a foaming adhesive filling method used in the structure, wherein the sandwich structure comprises a composite material inner skin, a composite material outer skin, a honeycomb core material, foaming adhesive and a shrinkage inhibiting part, a filling cavity is formed between the composite material inner skin and the composite material outer skin, the filling cavity comprises a honeycomb core material filling cavity and a foaming adhesive filling cavity, the honeycomb core material is filled into the honeycomb core material filling cavity, the foaming adhesive is filled into the foaming adhesive filling cavity, the shrinkage inhibiting part cluster is placed into the foaming adhesive and is cured together with the foaming adhesive through a prepreg unidirectional tape, and the problem of deformation caused by internal stress caused by thermal expansion of the foaming adhesive is solved.
Description
Technical Field
The invention relates to the technical field of composite material manufacturing, in particular to a composite material honeycomb sandwich structure and a foaming glue filling method used in the structure.
Background
The composite material sandwich structure is a structural material which saves most materials and has great strength-weight ratio at present, compared with a solid material, the effective material used by the composite material sandwich structure is only 1% -5% of the replaced material, although the composite material sandwich structure is a light material with the advantages of material saving, small energy consumption and great potential, the composite material sandwich structure has the advantages of light weight, high bending rigidity and strength, strong instability resistance, fatigue resistance, sound absorption, heat insulation and the like, and therefore, the composite material sandwich structure is widely applied to main and secondary bearing structures of airplanes in developed countries of the aviation industry.
The position of the core material in the composite material frame layer structure, which is difficult to completely fill, is often filled with the foaming adhesive, so that the processing difficulty of the molded surface of the core material is reduced, and the filling and weight reduction effects are ensured.
Therefore, in view of the above-mentioned problems, it is desirable to provide a composite honeycomb sandwich structure and a foam filling method for use in the structure.
Disclosure of Invention
The invention aims to provide a novel composite material honeycomb sandwich structure and a foaming glue filling method used in the structure, so as to solve the problem of deformation caused by thermal expansion stress in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
the composite material honeycomb sandwich structure comprises a composite material inner skin, a composite material outer skin, a honeycomb core material, foaming glue and a shrinkage inhibitor, wherein a filling cavity is formed between the composite material inner skin and the composite material outer skin and comprises a honeycomb core material filling cavity and a foaming glue filling cavity, the honeycomb core material is filled into the honeycomb core material filling cavity, the foaming glue is filled into the foaming glue filling cavity, and the shrinkage inhibitor is put into the foaming glue in a bundling manner.
Preferably, the shrinkage inhibitor is a prepreg unidirectional tape, and the prepreg unidirectional tape and the composite material outer skin are made of the same material.
Preferably, the curing temperature and time of the foaming adhesive are consistent with those of the prepreg unidirectional tape.
Preferably, the foaming adhesive is filled into a cavity with a large length-width ratio of the composite material interlayer, and the prepreg unidirectional tape is located at the center of the section of the foaming adhesive.
Preferably, the sectional area of the prepreg unidirectional tape is 5% -15% of the filling sectional area of the foaming glue, and the length of the prepreg unidirectional tape is consistent with the filling length of the foaming glue.
Preferably, according to the expansion ratio of the foaming adhesive, the cross-sectional shape of the foaming adhesive before curing is similar to the cross-sectional shape of the foaming adhesive filling cavity.
Preferably, the shape of the foaming adhesive is a belt shape, the curing temperature of the foaming adhesive is 120-180 ℃, and the expansion ratio of the foaming adhesive is 1 (2.5 +/-1).
Preferably, the cross-sectional shape of the prepreg unidirectional tape is circular or oval.
In another aspect, the foam rubber filling method for a composite sandwich structure provided by the embodiment of the invention comprises the following steps:
s1: and filling a honeycomb core material into a cavity with a large length-width ratio of the composite material sandwich structure, and forming a foaming glue filling cavity in the composite material sandwich structure.
And S2, adding a prepreg unidirectional tape with the curing temperature and time consistent with those of the foaming adhesive into the uncured foaming adhesive in the process of filling the foaming adhesive in the foaming adhesive filling cavity.
In step S2, the prepreg unidirectional tape is wrapped around the center of the cross section of the foam rubber. The invention comprises at least the following effective benefit effects: in the composite material sandwich structure, the foaming glue is filled into the foaming glue filling cavity, so that the filling effect can be ensured, and the weight can be reduced relatively; the prepreg unidirectional tape which is made of the same material as the composite material sandwich structure panel is added into the uncured foaming adhesive, and the prepreg unidirectional tape and the foaming adhesive are cured together, so that the internal stress caused by thermal expansion of the foaming adhesive is reduced, and the problem of composite material adhesive joint deformation caused by the foaming adhesive in the process of filling the large length-width ratio cavity of the composite material sandwich structure is solved; the prepreg unidirectional tape is positioned in the center of the section of the foaming adhesive, and when the prepreg unidirectional tape is heated and expanded, the stress borne by the prepreg unidirectional tape is uniformly distributed, and the deformation degree is correspondingly uniform.
Drawings
FIG. 1 is a schematic cross-sectional view of a composite honeycomb sandwich structure and a cavity for a foam rubber-filled cavity of the structure according to the present invention;
fig. 2 is a schematic cross-sectional view of a composite honeycomb sandwich structure of the present invention.
In the figure: 1. foaming glue; 2. a prepreg unidirectional tape; 3. filling the cavity with the foaming glue; 4. a honeycomb core material; 5. a composite outer skin; 6. and (4) a composite material inner skin.
Detailed Description
The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
In the description of the present invention, it is to be understood that the terms "center", "inside", "outside", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1-2, the composite material honeycomb sandwich structure provided by the invention comprises a composite material inner skin 6, a composite material outer skin 5, a honeycomb core material 4, a foaming adhesive 1 and a shrinkage inhibitor, wherein a filling cavity is formed between the composite material inner skin 6 and the composite material outer skin 5, the filling cavity comprises a honeycomb core material filling cavity and a foaming adhesive filling cavity, the honeycomb core material 4 is filled in the honeycomb core material filling cavity, the foaming adhesive 1 is filled in the foaming adhesive filling cavity 3, and the shrinkage inhibitor is put into the foaming adhesive 1 in a bundling manner.
In the above embodiment, the core material in the composite material interlayer is not easily and completely filled, and the foam rubber 1 is often used for filling to reduce the difficulty in processing the core material surface; because the thermal expansion coefficient of the foaming adhesive 1 is greater than that of the composite material, the prepreg unidirectional tape 2 is added into the uncured foaming adhesive 1, and the curing temperature and time of the prepreg unidirectional tape 2 and the curing time of the foaming adhesive 1 are kept consistent so as to reduce the shrinkage deformation of the composite material sandwich structure along the length direction caused by the shrinkage stress existing after the foaming adhesive 1 is cured.
Specifically, the shrinkage inhibitor is a prepreg unidirectional tape 2, and the prepreg unidirectional tape 2 is made of the same material as the composite material outer skin 5.
Specifically, the curing temperature and time of the foaming adhesive 1 are consistent with those of the prepreg unidirectional tape 2.
Specifically, the foaming glue 1 is filled into the foaming glue filling cavity 3, and the prepreg unidirectional tape 2 is located at the center of the section of the foaming glue 1.
Specifically, the sectional area of the prepreg unidirectional tape 2 is 5% -15% of the filling sectional area of the foaming glue 1, and the length of the prepreg unidirectional tape 2 is consistent with the filling length of the foaming glue 1.
Specifically, according to the expansion ratio of the foaming adhesive 1, the cross-sectional shape of the foaming adhesive 1 before curing is similar to the cross-sectional shape of the foaming adhesive filling cavity 3.
Specifically, the shape of the foaming adhesive 1 is a strip shape, the curing temperature of the foaming adhesive 1 is 120-180 ℃, and the expansion ratio of the foaming adhesive 1 is 1 (2.5 +/-1).
Specifically, the cross-sectional shape of the prepreg unidirectional tape 2 is circular or elliptical.
In another aspect, the foam rubber filling method for a composite sandwich structure provided by the embodiment of the invention comprises the following steps:
s1: and filling a honeycomb core material into a cavity with a large length-width ratio of the composite material sandwich structure, and forming a foaming glue filling cavity in the composite material sandwich structure.
And S2, adding a prepreg unidirectional tape with the curing temperature and time consistent with those of the foaming adhesive into the uncured foaming adhesive in the process of filling the foaming adhesive in the foaming adhesive filling cavity.
In step S2, the prepreg unidirectional tape is wrapped around the center of the cross section of the foam rubber.
In summary, the present application provides a composite honeycomb sandwich structure and a method for filling foam rubber in the structure, which have the following advantages through specific examples:
1. the deformation and shrinkage of the composite material frame layer structure along the length direction caused by shrinkage stress existing after the foaming adhesive is cured can be weakened.
2. The foaming adhesive has the characteristics of energy conservation, environmental protection, durability and environmental protection, has fire resistance, and is suitable for aviation.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (8)
1. The composite material honeycomb sandwich structure is characterized by comprising a composite material inner skin, a composite material outer skin, a honeycomb core material, foaming glue and a shrinkage inhibitor, wherein a filling cavity is formed between the composite material inner skin and the composite material outer skin and comprises a honeycomb core material filling cavity and a foaming glue filling cavity, the honeycomb core material is filled into the honeycomb core material filling cavity, the foaming glue is filled into the foaming glue filling cavity, and the shrinkage inhibitor cluster is put into the foaming glue;
the shrinkage inhibitor is a prepreg unidirectional tape, and the prepreg unidirectional tape and the composite material outer skin are made of the same material;
the sectional area of the prepreg unidirectional tape is 5% -15% of the filling sectional area of the foaming glue, and the length of the prepreg unidirectional tape is consistent with the filling length of the foaming glue.
2. A composite honeycomb sandwich structure according to claim 1 wherein: the curing temperature and time of the foaming adhesive are consistent with those of the prepreg unidirectional tape.
3. A composite honeycomb sandwich structure according to claim 1 wherein: the prepreg unidirectional tape is positioned at the center of the section of the foaming adhesive.
4. A composite honeycomb sandwich structure according to claim 1 wherein: according to the expansion ratio of the foaming adhesive, the section shape of the foaming adhesive before curing is similar to the section shape of the foaming adhesive filling cavity.
5. A composite honeycomb sandwich structure according to claim 1 wherein: the shape of the foaming adhesive is strip-shaped, the curing temperature of the foaming adhesive is 120-180 ℃, and the expansion ratio of the foaming adhesive is 1 (2.5 +/-1).
6. A composite honeycomb sandwich structure according to claim 1 wherein: the cross section of the prepreg unidirectional tape is circular or oval.
7. A foam rubber filling method for a composite material sandwich structure is characterized by comprising the following steps:
s1: filling a honeycomb core material into a cavity with a large length-width ratio of the composite material sandwich structure, and forming a foaming glue filling cavity in the composite material sandwich structure;
s2: and in the process of filling the foaming adhesive in the foaming adhesive filling cavity, adding a prepreg unidirectional tape with the curing temperature and time consistent with the curing temperature and time of the foaming adhesive into the uncured foaming adhesive.
8. The foam rubber filling method for the sandwich structure of the composite material according to claim 7, wherein: in step S2, the prepreg unidirectional tape is wrapped around the center of the cross section of the foam rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911065654.1A CN110744872B (en) | 2019-11-04 | 2019-11-04 | Composite material honeycomb sandwich structure and foaming glue filling method used in same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911065654.1A CN110744872B (en) | 2019-11-04 | 2019-11-04 | Composite material honeycomb sandwich structure and foaming glue filling method used in same |
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| Publication Number | Publication Date |
|---|---|
| CN110744872A CN110744872A (en) | 2020-02-04 |
| CN110744872B true CN110744872B (en) | 2021-10-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911065654.1A Active CN110744872B (en) | 2019-11-04 | 2019-11-04 | Composite material honeycomb sandwich structure and foaming glue filling method used in same |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112829161B (en) * | 2021-01-07 | 2022-10-21 | 中国航空制造技术研究院 | Foaming glue filling method for composite material honeycomb sandwich structure |
| CN114106728B (en) * | 2021-12-14 | 2023-07-25 | 芜湖徽氏新材料科技有限公司 | Foaming adhesive tape and use method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103589349A (en) * | 2013-10-26 | 2014-02-19 | 衡阳泰豪通信车辆有限公司 | Honeycomb core splicing method |
| CN108081681A (en) * | 2017-12-15 | 2018-05-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of mixing sandwich structure and its processing method with sloped transition area |
-
2019
- 2019-11-04 CN CN201911065654.1A patent/CN110744872B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103589349A (en) * | 2013-10-26 | 2014-02-19 | 衡阳泰豪通信车辆有限公司 | Honeycomb core splicing method |
| CN108081681A (en) * | 2017-12-15 | 2018-05-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of mixing sandwich structure and its processing method with sloped transition area |
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| Publication number | Publication date |
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| CN110744872A (en) | 2020-02-04 |
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