CN108973089B - Preparation method of composite material special-shaped skin structure - Google Patents
Preparation method of composite material special-shaped skin structure Download PDFInfo
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- CN108973089B CN108973089B CN201810816211.0A CN201810816211A CN108973089B CN 108973089 B CN108973089 B CN 108973089B CN 201810816211 A CN201810816211 A CN 201810816211A CN 108973089 B CN108973089 B CN 108973089B
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- composite
- skin structure
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- 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
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
- B29C51/002—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor characterised by the choice of material
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- 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
- B29C51/00—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor
- B29C51/12—Shaping by thermoforming, i.e. shaping sheets or sheet like preforms after heating, e.g. shaping sheets in matched moulds or by deep-drawing; Apparatus therefor of articles having inserts or reinforcements
Abstract
The invention relates to a preparation method of a composite material special-shaped skin structure. The method comprises the following steps: preparing a combined process cover plate matched with a forming surface of the composite material special-shaped skin structure digital model according to the composite material special-shaped skin structure digital model; compounding and curing a flexible process carrier with a fiber net structure and resin to form a composite process thin layer with a composite area and a non-composite area, wherein the composite area corresponds to the joint of the combined process cover plate and is provided with a structural boundary compounded in a resin content gradient in the in-plane direction; sequentially laminating the composite material anisotropic skin structure blank, the composite process thin layer and the combined process cover plate on a mould tool from bottom to top to form a process combination, wherein the composite process thin layer corresponds to the joint of the combined process cover plate through a composite area; and (5) hot-pressing and curing to obtain the required composite material special-shaped skin structure.
Description
Technical Field
The invention relates to the technical field of composite material structure forming, in particular to a preparation method of a composite material special-shaped skin structure.
Background
In the application field of composite material structures in the aviation industry, composite material special-shaped skins including beams, leading edges, polyhedrons and the like of R areas or folded angle structures are common. At present, based on the requirement of internal quality manufacturing, the composite material special-shaped skin preparation method mostly adopts combined process cover plates, the combined process cover plates are usually formed by jointing a plurality of independent split process cover plates through joints, and the split process cover plates have high mutual activity coordination due to the fact that the joints penetrate through the whole thickness direction, and can meet the requirement of the internal quality manufacturing of the composite material special-shaped skin. However, the split process cover plates are easily dislocated, so that obvious surface process indentations are formed on the surface of a workpiece, and the surface quality problem is caused. Therefore, the development of a novel process method becomes an important technical problem concerned in the field of forming the composite material special-shaped skin structure.
Therefore, the inventor provides a preparation method of the composite material special-shaped skin structure.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a preparation method of a composite material special-shaped skin structure, which is characterized in that a composite process thin layer with a composite area and a non-composite area is introduced between a composite structure process cover plate and a composite material special-shaped skin structure blank formed by the composite structure process cover plate, and the composite material special-shaped skin structure is prepared and obtained in a mode that the joint of the composite area with a structure boundary of resin content gradient composite in the in-plane direction and the composite structure process cover plate corresponds to each other.
The embodiment of the invention provides a preparation method of a composite material special-shaped skin structure, which comprises the following steps:
preparing a combined process cover plate matched with a forming surface of the composite material special-shaped skin structure according to a digital model of the composite material special-shaped skin structure, and forming a composite process thin layer with a composite area and a non-composite area by utilizing a flexible process carrier with a fiber net structure and resin through composite curing, wherein the joint of the composite area and the combined process cover plate corresponds to each other, and the composite area has a structural boundary with resin content gradient composite in the in-plane direction;
laminating the composite material special-shaped skin structure blank, the composite process thin layer and the combined process cover plate on the mold tool from bottom to top in sequence to form a process combination, wherein the composite process thin layer is introduced into the process combination in a mode that a composite area corresponds to the joint of the combined process cover plate;
and carrying out hot pressing on the process combination to carry out hot pressing and curing on the composite material special-shaped skin structure blank to obtain the final composite material special-shaped skin structure.
Further, the composite profiled skin structure refers to a fiber reinforced resin matrix composite skin structure at least comprising an R-angle structure or a bevel structure.
Furthermore, the combined process cover plate is formed by jointing at least two independent split process cover plates in a butt joint or lap joint mode.
Further, the combined process cover plate is made of one or more of fiber reinforced resin matrix composite materials, rubber materials or fiber reinforced rubber materials.
Further, the material of the resin is one or more of epoxy resin, bismaleimide resin, polyimide resin, polybenzoxazine resin, cyanate resin and phenolic resin.
Further, the flexible technical carrier is a single-layer or multi-layer laminated body formed by non-woven fabrics.
Furthermore, the width a of the composite area, the thickness b of the composite area and the width c of the structural boundary of the resin content gradient composite satisfy that a is more than or equal to 30mm and less than or equal to 50mm, b is more than or equal to 0.1mm and less than or equal to 1mm, and c is more than or equal to 3 b.
Furthermore, the Tmax between the highest curing preparation temperature Tmax of the composite material special-shaped skin structure blank and the glass transition temperature Tg (F) of the composite area is less than or equal to Tg (F) -30 ℃.
In conclusion, the invention has the advantages and beneficial effects that: the invention is different from the traditional method that the composite material special-shaped skin structure is prepared by directly adopting the combined process cover plate, and a composite process thin layer is introduced between the joint of the combined structure process cover plate and the formed composite material special-shaped skin structure blank. The surface defect of the composite material special-shaped skin structure is caused by pressure mutation generated by dislocation of a split process cover plate, the final source of the pressure mutation is generated by structural rigidity mutation at a joint, a composite process thin layer is provided with a composite region and a non-composite region, the composite region is a rigid structure formed by a resin matrix, the pressure mutation at the joint of the process cover plate can be transferred to the boundary of the composite region, the boundary of the composite region is a resin content gradient composite structure in the in-plane direction and is in a structural form with gradually-changed rigidity, the structural rigidity mutation effect can be greatly reduced or even completely weakened, and the surface with excellent structure is further realized on the basis of ensuring the internal quality. Finally, the invention also limits other characteristics of the process cover plate and the composite area of the combined structure, and further ensures the implementation effect of the whole invention.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed 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 to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic view of a combined process cover and process carrier of the present invention.
FIG. 2 is a schematic diagram of a thin layer of the composite process of the present invention.
Fig. 3 is a schematic view of a preparation scenario of a composite material profiled skin structure according to an embodiment of the present invention.
FIG. 4 is a schematic structural view of the composite profiled skin prepared by the present invention.
In the figure:
1-combining a process cover plate; 11-joint of combined process cover plate;
2-a process carrier;
3-compounding process thin layers; 31-a recombination zone; 32-a non-recombination zone; a-the width of the recombination zone; b-the thickness of the recombination zone; c-width of structural boundary of resin content gradient composite;
4-composite material special-shaped skin structure blank;
5, die tooling;
6-composite material special-shaped skin structure.
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 and are not intended to limit the scope of the invention, i.e., the invention is not limited to the described embodiments.
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.
With reference to fig. 1, 2, 3 and 4, the preparation method of the composite material profiled skin structure includes the following steps S110 to S130:
step S110 is to prepare a composite process thin layer, prepare a composite process cover plate 1 matched with a forming surface thereof according to a composite material irregular skin structure model, and form a composite process thin layer 3 having a composite region 31 and a non-composite region 32 by using a flexible process carrier 2 having a fiber mesh structure and compounding and curing with resin, wherein the composite region 31 corresponds to a joint 11 of the composite process cover plate 1, and the composite region 31 has a structural boundary of resin content gradient composite in an in-plane direction.
Wherein the width a of the composite area of the composite process thin layer 3, the thickness b of the composite area and the width c of the structural boundary of the resin content gradient composite satisfy that a is more than or equal to 30mm and less than or equal to 50mm, b is more than or equal to 0.1mm and less than or equal to 1mm, and c is more than or equal to 3 b.
In the step, the combined process cover plate 1 is formed by jointing at least two independent split process cover plates in a butt joint or lap joint mode, and the material of the combined process cover plate is one of a fiber reinforced resin matrix composite material, a rubber material or a fiber reinforced rubber material.
The material of the resin is one or more of epoxy resin, bismaleimide resin, polyimide resin, polybenzoxazine resin, cyanate resin and phenolic resin.
Preferably, the process support 2 is a single-layer or multi-layer laminate of non-woven fabrics.
Step S120 is laminating to form a process combination, and the composite material special-shaped skin structure blank 4, the composite process thin layer 3 and the combined process cover plate 1 are sequentially laminated on the die tool 5 from bottom to top to form a structure of the process combination, wherein the composite process thin layer 3 is introduced into the process combination in a mode that the composite area 31 corresponds to the joint 11 of the combined process cover plate 1.
Step S130 is a hot-press curing molding, and the process combination of the above steps is hot-pressed, so that the composite material irregular skin structure blank 4 can be hot-press cured, and finally the composite material irregular skin structure 6 is obtained.
In the step, Tmax is not more than Tg (F) -30 ℃ between the highest curing preparation temperature Tmax of the composite material special-shaped skin structure blank 4 and the glass transition temperature Tg (F) of the composite area 31.
The preparation method of the composite material special-shaped skin structure has the following specific application:
example 1, taking the preparation of an epoxy resin-based carbon fiber composite material C beam as an example:
step (1), an epoxy resin-based carbon fiber composite material C beam is provided with two R angle structures, a combined process cover plate formed by butt joint of two independent split process cover plates is designed and prepared, a joint is positioned in a web area between the two R angle structures, the material of the combined process cover plate is a fiber reinforced rubber material, by means of a mould tool, a carrier-free bismaleimide resin film with equal thickness is selected to be directly subjected to hot melting composite curing with a process carrier fully covered by a molded surface in a corresponding area of the joint of the combined process cover plate, the process carrier is a two-layer non-woven fabric laminated body, a structured composite process thin layer with 1 composite area and 2 non-composite areas is prepared and obtained, the length a of the composite area is about 35mm, the thickness b of the composite area is about 0.2mm, the composite area is provided with a resin content gradient composite structure boundary, and the width C of the structure boundary is about 1.2mm, the glass transition temperature Tg (F) of the composite zone was 265 ℃.
And (2) introducing the structured composite process thin layer into a process combination of a blank of the epoxy resin-based carbon fiber composite C beam in a manner that a composite area corresponds to a joint of a combined process cover plate of the epoxy resin-based carbon fiber composite C beam, wherein the process combination comprises the composite material special-shaped skin structure blank, the composite process thin layer and the combined process cover plate which are sequentially laminated on a die tool from bottom to top.
And (3) carrying out hot-pressing curing operation on the composite material special-shaped skin structure blank to prepare an epoxy resin-based carbon fiber composite material C beam structure, wherein the highest curing process temperature Tmax =180 ℃ during curing preparation. Through detection, the internal quality and the surface quality of the C beam structure of the epoxy resin-based carbon fiber composite material are good.
Example 2: taking the preparation of the bismaleimide resin-based glass fiber composite material profiled skin as an example:
step (1), the special-shaped skin made of bismaleimide resin-based glass fiber composite material comprises 1 bevel structure and an R angle structure, a combined process cover plate formed by splicing 3 independent split process cover plates in a wedge-shaped overlapping mode is designed and prepared, two joints J1 and J2 are respectively located on two sides of the R angle structure, polyimide resin solution is selected to be directly compounded and solidified with process carriers in corresponding areas of J1 and J2 of the joints of the combined process cover plate by means of a mold tool, the process carriers are made of a layer of non-woven fabric, a composite process thin layer combining a1 area and A2 with a non-composite area is prepared, wherein the composite area A1 corresponds to the joint J1, the width a1 is about 38mm, the thickness b1 is about 0.15mm, the boundary structure of the composite structure with gradient resin content in the in-plane direction, the width c1 of the boundary structure is about 2.52mm, and the composite area A2 corresponds to the joint J2, the width a2 is about 47mm, the thickness b2 is about 0.2mm, the boundary structure is a resin content gradient composite structure in the in-plane direction, the width c2 of the boundary structure is about 3mm, and the glass transition temperature Tg (F) of two composite regions is 335 ℃.
And (2) introducing the structural composite process thin layers into the process combination of the blanks of the bismaleimide resin-based glass fiber composite profiled skin in a mode that the composite areas A1 and A2 of the structural composite process thin layers correspond to the two joints J1 and J2 of the combined process cover plate of the bismaleimide resin-based glass fiber composite profiled skin.
And (3) curing the blank of the composite material special-shaped skin to prepare the bismaleimide resin based glass fiber composite material special-shaped skin, wherein the maximum curing process temperature Tmax =200 ℃ during curing preparation. Through detection, the surface and the internal quality of the bismaleimide resin-based glass fiber composite material special-shaped skin are good.
The above description is only an example of the present application and is not limited to the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (8)
1. A method for preparing a composite material special-shaped skin structure is characterized by comprising the following steps:
preparing a combined process cover plate matched with a forming surface of the composite material special-shaped skin structure according to a composite material special-shaped skin structure digital model, and forming a composite process thin layer with a composite area and a non-composite area by utilizing a flexible process carrier with a fiber net structure and resin in a composite curing mode, wherein the joint of the composite area and the combined process cover plate corresponds to each other, and the composite area is provided with a structural boundary of resin content gradient composite in the in-plane direction;
sequentially laminating the composite material special-shaped skin structure blank, the composite process thin layer and the combined process cover plate on a mould tool from bottom to top to form a process combination, wherein the composite process thin layer is introduced into the process combination in a mode that a composite area corresponds to the joint of the combined process cover plate;
and carrying out hot pressing on the process combination to ensure that the composite material special-shaped skin structure blank is cured by hot pressing to obtain the composite material special-shaped skin structure.
2. The method for manufacturing the composite profiled skin structure according to claim 1, wherein the composite profiled skin structure is a fiber reinforced resin based composite skin structure including at least one R-angle structure or bevel structure.
3. The method for preparing the composite material profiled skin structure according to claim 1, characterized in that the combined process cover plate is formed by jointing not less than two independent split process cover plates in a butt joint or lap joint mode.
4. The method for manufacturing the composite profiled skin structure according to claim 3, wherein the material of the combined process cover plate is one or more of a fiber reinforced resin matrix composite material, a rubber material or a fiber reinforced rubber material.
5. The method for preparing the composite material profiled skin structure according to claim 1, characterized in that the material of the resin is one or more of epoxy resin, bismaleimide resin, polyimide resin, polybenzoxazine resin, cyanate resin and phenolic resin.
6. The method for manufacturing the composite profiled skin structure according to claim 1, wherein the flexible process carrier is a single-layer or multi-layer laminate formed by non-woven fabrics.
7. The method for manufacturing the composite material special-shaped skin structure according to claim 1, wherein the width a of the composite area, the thickness b of the composite area and the width c of the structural boundary of the resin content gradient composite satisfy that a is more than or equal to 30mm and less than or equal to 50mm, b is more than or equal to 0.1mm and less than or equal to 1mm, and c is more than or equal to 3 b.
8. The method for preparing the composite profiled skin structure according to claim 1, wherein Tmax is not more than Tg (F) -30 ℃ is satisfied between the maximum curing preparation temperature Tmax of the composite profiled skin structure blank and the glass transition temperature Tg (F) of the composite zone.
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