CN118144337A - Composite material edge structure repairing method - Google Patents
Composite material edge structure repairing method Download PDFInfo
- Publication number
- CN118144337A CN118144337A CN202410449504.5A CN202410449504A CN118144337A CN 118144337 A CN118144337 A CN 118144337A CN 202410449504 A CN202410449504 A CN 202410449504A CN 118144337 A CN118144337 A CN 118144337A
- Authority
- CN
- China
- Prior art keywords
- composite material
- edge structure
- edge
- expansion
- heating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 118
- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000000463 material Substances 0.000 claims abstract description 35
- 238000010438 heat treatment Methods 0.000 claims abstract description 27
- 238000004519 manufacturing process Methods 0.000 claims abstract description 24
- 239000011347 resin Substances 0.000 claims abstract description 11
- 229920005989 resin Polymers 0.000 claims abstract description 11
- 239000000853 adhesive Substances 0.000 claims abstract description 10
- 230000001070 adhesive effect Effects 0.000 claims abstract description 10
- 238000003892 spreading Methods 0.000 claims abstract description 7
- 239000002184 metal Substances 0.000 claims description 8
- 239000003365 glass fiber Substances 0.000 claims description 7
- 239000003292 glue Substances 0.000 claims description 5
- 239000002390 adhesive tape Substances 0.000 claims description 4
- 238000005520 cutting process Methods 0.000 claims description 4
- 239000002313 adhesive film Substances 0.000 abstract description 6
- 238000001723 curing Methods 0.000 description 24
- 238000001029 thermal curing Methods 0.000 description 5
- 239000012774 insulation material Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 210000003484 anatomy Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/24—Apparatus or accessories not otherwise provided for
- B29C73/30—Apparatus or accessories not otherwise provided for for local pressing or local heating
- B29C73/34—Apparatus or accessories not otherwise provided for for local pressing or local heating for local heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/24—Apparatus or accessories not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
Abstract
The invention discloses a method for repairing a composite material edge structure, which comprises the following steps: manufacturing a supporting backboard with the same shape as the edge structure of the composite material to be repaired; spreading and fixing an expansion material which is the same as the edge structure of the composite material to be repaired on the back of the support backboard to manufacture an expansion structure; fixing the expansion structure at the edge of the edge structure of the composite material, and symmetrically arranging the expansion structure and the edge structure of the composite material; and heating and curing the edge structure of the composite material by adopting a heating and curing system so as to repair the edge structure of the composite material. In the invention, the resin adhesive or the adhesive film can be precisely controlled according to the required curing temperature, so that the resin adhesive or the adhesive film is fully cured, the best performance is achieved, and the structural strength of a repair area is ensured.
Description
Technical Field
The invention relates to the technical field of repair, in particular to a method for repairing a composite material edge structure.
Background
The composite structure is widely applied in the aviation industry due to the characteristics of excellent high rigidity, high strength, light weight, good design performance and the like, and particularly on civil airliners, the proportion of composite structural members is continuously rising. However, in actual repair work, it is often necessary to perform thermal curing repair on the damaged portion. When the damaged area relates to the edge structure, it is difficult to maintain the temperature in the heated area uniform due to the heat conduction property of the edge structure.
Existing manufacturer solutions generally use only vacuum negative pressure devices and a thermal curing system to perform thermal curing to repair the composite material.
However, the prior art is deficient in consideration of thermal loss and structural differences in the edge region when processing composite structures for thermal curing. Due to the difference of the structures, the heat insulation performance and the heat conductivity of the heat insulation material are naturally different, so that the temperature consistency of the whole temperature control area is difficult to achieve, the heat insulation material may not only cause local overtemperature and damage the repaired component, but also cause that the glue or the adhesive film needing to be heated and cured is not completely cured due to the insufficient local temperature, thereby affecting the performance and the structural strength of the heat insulation material and finally causing repair failure.
Disclosure of Invention
The purpose of the invention is that: the method for repairing the edge structure of the composite material is provided, so that the edge area of the composite material structure can be repaired smoothly.
In order to solve the technical problems, the invention provides the following technical scheme:
A method for repairing a composite material edge structure comprises the following steps:
manufacturing a supporting backboard with the same shape as the edge structure of the composite material to be repaired;
Spreading and fixing an expansion material which is the same as the edge structure of the composite material to be repaired on the back of the support backboard to manufacture an expansion structure;
Fixing the expansion structure at the edge of the edge structure of the composite material, and symmetrically arranging the expansion structure and the edge structure of the composite material;
And heating and curing the edge structure of the composite material by adopting a heating and curing system so as to repair the edge structure of the composite material.
Preferably, when manufacturing a support back plate having the same shape as the edge structure of the composite material to be repaired, the method comprises the steps of:
selecting a glass fiber which is well soaked by resin glue and paved in the area with the same shape as the edge structure of the composite material in the undamaged area of the edge structure of the composite material;
And sleeving the vacuum bag on the region where the glass fiber is paved on the edge structure of the composite material, and vacuumizing and solidifying to finish the manufacturing of the support backboard.
Preferably, when a support back plate having the same shape as the edge structure of the composite material to be repaired is manufactured, the metal plate is manufactured into the support back plate by a sheet metal forming process.
Preferably, when the expansion material of the same material as the edge structure of the composite material to be repaired is paved and fixed on the back of the support back plate to manufacture the expansion structure, the method comprises the following steps:
spreading an expansion material which is the same as the edge structure of the composite material to be repaired on the back of the support backboard by adopting curing adhesive;
Sleeving the expansion material and the support backboard by adopting a vacuum bag, and vacuumizing to shape the expansion material;
and heating and curing the expansion material by adopting a heating and curing system to manufacture the expansion structure.
Preferably, the heating curing system is used for heating and curing the expansion material to manufacture the expansion structure, and then a cutting tool is used for cutting the corners of the expansion structure so that the expansion structure can be tightly attached to the edge structure of the composite material.
Preferably, the expansion material is heated and cured by a heating and curing system to form an expansion structure, and then the surface of the expansion structure is polished by a sander.
Preferably, when the expansion structure is fixed at the edge of the edge structure of the composite material and the expansion structure is symmetrically arranged with the edge structure of the composite material, the method comprises the following steps:
Splicing the expansion structure at the edge of the edge structure of the composite material, so that the expansion structure and the edge structure of the composite material are symmetrical;
Preliminarily sticking and fixing the expansion structure and the edge structure of the composite material together by using an adhesive tape;
And sleeving the expansion structure and the edge structure of the composite material by adopting a vacuum bag, and vacuumizing to fix the expansion structure and the edge structure of the composite material together.
Compared with the prior art, the method for repairing the edge structure of the composite material has the beneficial effects that:
In the invention, a support backboard is firstly manufactured through an edge structure of a composite material, then the support backboard is used as a mould, an expansion material which is the same as the edge structure of the composite material to be repaired is paved on the support backboard, so that the expansion structure is manufactured, then the expansion structure is spliced at the edge of the edge structure of the composite material, so that the expansion structure is symmetrical with the edge structure of the composite material, therefore, when the heating curing system is adopted to carry out heating curing on the edge structure of the composite material, the original edge of the composite material is moved outwards due to the arrangement of the expansion structure to carry out repairing work, the original edge of the composite material is positioned in a heated middle area, the heat conductivity of the original edge area is controlled, the temperature of the heating area is controlled to be consistent, the curing and repairing temperature is controlled, the resin adhesive or the adhesive film is accurately controlled according to the required curing temperature, the resin adhesive is fully cured, the best performance is achieved, and the structural strength of the repairing area is ensured.
Drawings
FIG. 1 is a flow chart of a method of repairing an edge structure of a composite material in accordance with an embodiment of the present invention;
FIG. 2 is a top view of an edge structure and an extension structure of an embodiment of the present invention;
fig. 3 is a side view of an edge structure and an extension structure of an embodiment of the present invention.
In the figure, 1, edge structure; 2. and (5) expanding the structure.
Detailed Description
The following describes in further detail the embodiments of the present invention with reference to the drawings and examples. The following examples are illustrative of the invention and are not intended to limit the scope of the invention.
In the description of the present invention, it should be understood that the term "comprises/comprising" when used in this specification is taken to specify the presence of stated features, integers, steps, operations, elements/components, and/or groups thereof, but does not preclude the presence or addition of one or more other features, integers, steps, operations, elements/components, and/or groups thereof. It will be understood that when an element/component is referred to as being "connected" to another element/component, it can be directly connected to the other element/component or intervening elements/components may also be present. The term "and/or" as used herein includes all or any element and all combination of one or more of the associated listed items.
As shown in fig. 1 and 3, the invention relates to a method for repairing an edge structure of a composite material, which comprises the following steps:
Manufacturing a supporting backboard with the same shape as the edge structure 1 of the composite material to be repaired;
spreading and fixing an expansion material which is the same as the edge structure 1 of the composite material to be repaired on the back of the support backboard to manufacture an expansion structure 2;
fixing the expansion structure 2 at the edge of the edge structure 1 of the composite material, and arranging the expansion structure 2 and the edge structure 1 of the composite material symmetrically;
And heating and curing the edge structure 1 of the composite material by adopting a heating and curing system so as to repair the edge structure 1 of the composite material.
In the invention, a support backboard is firstly manufactured through an edge structure 1 of a composite material, then the support backboard is used as a mould, an expansion material which is the same as the edge structure 1 of the composite material to be repaired is paved on the support backboard, so that an expansion structure 2 is manufactured, then the expansion structure 2 is spliced at the edge of the edge structure 1 of the composite material, so that the expansion structure 2 and the edge structure 1 of the composite material are symmetrical, therefore, when a heating curing system is adopted to carry out heating curing on the edge structure 1 of the composite material, in order to carry out repairing work, the edge of the original composite material is moved outwards due to the arrangement of the expansion structure 2, the edge of the original composite material is positioned in a heated middle area, the heat conductivity of the original edge area is controlled, the temperature of the heated area is consistent, the curing temperature is controlled, the resin adhesive or the adhesive film is accurately controlled according to the required curing temperature, the resin adhesive is fully cured, the best performance is achieved, and the structural strength of the repairing area is ensured.
It should be noted that, before the repair of the thermal curing, the structure of the edge region of the composite material to be repaired is analyzed, and the structure and the required material of the edge region are analyzed, and this work can be performed by querying manuals provided by manufacturers, the structural anatomy of the waste parts, and empirical summaries of previous repair of this region. Thus, it is clear what kind of fiber material is used, what layer the thickness of the face sheet is, and other key information is obtained, whether the edge structure 1 of the composite material is a laminate structure or a honeycomb sandwich structure.
In this embodiment, when manufacturing a support back plate having the same shape as the edge structure 1 of the composite material to be repaired, the method comprises the steps of:
Selecting a glass fiber which is well soaked by resin glue and paved in the same shape as the edge structure 1 of the composite material in the undamaged area of the edge structure 1 of the composite material;
and sleeving the vacuum bag on the region where the glass fiber is paved on the edge structure 1 of the composite material, and vacuumizing and solidifying to finish the manufacturing of the support backboard.
That is, a glass fiber impregnated with resin glue is paved in an undamaged area of the edge structure 1 of the composite material, a vacuum bag is sleeved in the area, and vacuum curing is performed to obtain a support back plate with the same shape as the edge structure 1 of the composite material, so that the shape of the expansion structure 2 can be ensured to be the same as that of the edge structure 1 of the composite material when the expansion structure 2 is paved on the support back plate.
In other embodiments, the metal sheet is made into a support back plate using a sheet metal forming process when making a support back plate of the same shape as the edge structure 1 of the composite material to be repaired.
That is, the metal plate can be made into a supporting back plate with the same shape as the edge structure 1 of the composite material by a sheet metal forming process, so that the supporting back plate has stronger structural strength.
In this embodiment, when an extension material made of the same material as the edge structure 1 of the composite material to be repaired is laid on the back of the support back plate to manufacture the extension structure 2, the method includes the following steps:
Spreading an expansion material which is the same as the edge structure 1 of the composite material to be repaired on the back of the support backboard by adopting curing adhesive;
Sleeving the expansion material and the support backboard by adopting a vacuum bag, and vacuumizing to shape the expansion material;
the expansion material is heated and cured by a heating and curing system to manufacture the expansion structure 2.
That is, the expansion material is firstly laid on the back of the support back plate along the shape of the support back plate so that the expansion material is the same as the shape of the edge structure 1 of the composite material, then the expansion material and the support back plate are sleeved together by the vacuum bag, and vacuumized to shape the expansion material, and finally the expansion material is heated and cured by the heating and curing system to form the stable expansion structure 2.
Preferably, after the expansion material is heated and cured by adopting a heating and curing system to manufacture the expansion structure 2, the corners of the expansion structure 2 are cut by adopting a cutting tool, so that the expansion structure 2 can be tightly attached to the edge structure 1 of the composite material, and the smoothness of subsequent repair work is ensured.
Further, after the expansion material is heated and solidified by adopting a heating and solidifying system to manufacture the expansion structure 2, a sander is adopted to polish the surface of the expansion structure 2, so that flaws and burrs of the expansion structure 2 are removed, and the vacuum bag is prevented from being punctured in the vacuumizing process.
In this embodiment, when the extension structure 2 is fixed at the edge of the edge structure 1 of the composite material and the extension structure 2 is symmetrically arranged with the edge structure 1 of the composite material, the method includes the following steps:
Splicing the expansion structure 2 at the edge of the edge structure 1 of the composite material, so that the expansion structure 2 and the edge structure 1 of the composite material are symmetrical;
the expansion structure 2 and the edge structure 1 of the composite material are preliminarily stuck and fixed together by using adhesive tape;
the expanded structure 2 and the edge structure 1 of the composite material are sleeved together by a vacuum bag, and vacuuming treatment is carried out to fix the expanded structure 2 and the edge structure 1 of the composite material together.
That is, when the extension structure 2 and the edge structure 1 of the composite material are spliced together, the extension structure 2 and the edge structure 1 of the composite material are firstly stuck together through an adhesive tape so as to be preliminarily fixed together, then the extension structure 2 and the edge structure 1 of the composite material are sleeved together by a vacuum bag, and vacuumizing treatment is carried out, so that the extension structure 2 and the edge structure 1 of the composite material can be firmly connected together, and further the smoothness of subsequent repair work is ensured.
In summary, compared with the prior art, the method for repairing the edge structure of the composite material, provided by the embodiment of the invention, considers the characteristic of quick thermal conductivity of the edge of the component structure, and makes the edge of the edge structure 1 of the composite material move outwards through manufacturing the expansion area, so that the edge of the edge structure 1 of the composite material is positioned in a heated middle position, the thermal conductivity of the original edge area is controlled, and therefore, the resin adhesive or the adhesive film can be accurately controlled according to the required curing temperature, and can be fully cured, the best performance is achieved, and the structural strength of the repair area of the edge structure 1 of the composite material is ensured.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and substitutions can be made by those skilled in the art without departing from the technical principles of the present invention, and these modifications and substitutions should also be considered as being within the scope of the present invention.
Claims (7)
1. The method for repairing the edge structure of the composite material is characterized by comprising the following steps of:
manufacturing a supporting backboard with the same shape as the edge structure of the composite material to be repaired;
Spreading and fixing an expansion material which is the same as the edge structure of the composite material to be repaired on the back of the support backboard to manufacture an expansion structure;
Fixing the expansion structure at the edge of the edge structure of the composite material, and symmetrically arranging the expansion structure and the edge structure of the composite material;
And heating and curing the edge structure of the composite material by adopting a heating and curing system so as to repair the edge structure of the composite material.
2. The method for repairing an edge structure of a composite material according to claim 1, wherein when a support back plate having the same shape as the edge structure of the composite material to be repaired is manufactured, comprising the steps of:
selecting a glass fiber which is well soaked by resin glue and paved in the area with the same shape as the edge structure of the composite material in the undamaged area of the edge structure of the composite material;
And sleeving the vacuum bag on the region where the glass fiber is paved on the edge structure of the composite material, and vacuumizing and solidifying to finish the manufacturing of the support backboard.
3. The method for repairing an edge structure of a composite material according to claim 1, wherein the metal plate is manufactured into the support back plate by a sheet metal forming process when manufacturing a support back plate having the same shape as the edge structure of the composite material to be repaired.
4. The method for repairing an edge structure of a composite material according to claim 1, wherein when an extension material of the same material as the edge structure of the composite material to be repaired is laid on the back of the support back plate to manufacture the extension structure, the method comprises the steps of:
spreading an expansion material which is the same as the edge structure of the composite material to be repaired on the back of the support backboard by adopting curing adhesive;
Sleeving the expansion material and the support backboard by adopting a vacuum bag, and vacuumizing to shape the expansion material;
and heating and curing the expansion material by adopting a heating and curing system to manufacture the expansion structure.
5. The method of claim 4, wherein the edge structure of the composite material is cured by heating using a heating curing system, and after the expanded structure is formed, the corners of the expanded structure are cut using a cutting tool, so that the expanded structure can be closely attached to the edge structure of the composite material.
6. The method of claim 4, wherein the surface of the expanded structure is polished by a polisher after the expanded material is heated and cured by a heating and curing system to form the expanded structure.
7. The method of repairing an edge structure of a composite material according to claim 1, wherein the step of fixing the extension structure to the edge of the edge structure of the composite material and arranging the extension structure symmetrically to the edge structure of the composite material comprises the steps of:
Splicing the expansion structure at the edge of the edge structure of the composite material, so that the expansion structure and the edge structure of the composite material are symmetrical;
Preliminarily sticking and fixing the expansion structure and the edge structure of the composite material together by using an adhesive tape;
And sleeving the expansion structure and the edge structure of the composite material by adopting a vacuum bag, and vacuumizing to fix the expansion structure and the edge structure of the composite material together.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410449504.5A CN118144337A (en) | 2024-04-15 | 2024-04-15 | Composite material edge structure repairing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410449504.5A CN118144337A (en) | 2024-04-15 | 2024-04-15 | Composite material edge structure repairing method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118144337A true CN118144337A (en) | 2024-06-07 |
Family
ID=91290153
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410449504.5A Pending CN118144337A (en) | 2024-04-15 | 2024-04-15 | Composite material edge structure repairing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118144337A (en) |
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2024
- 2024-04-15 CN CN202410449504.5A patent/CN118144337A/en active Pending
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