CN113059828A - High-temperature-resistant carbon fiber composite material cylinder bearing layer and preparation process thereof - Google Patents
High-temperature-resistant carbon fiber composite material cylinder bearing layer and preparation process thereof Download PDFInfo
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- CN113059828A CN113059828A CN202110431453.XA CN202110431453A CN113059828A CN 113059828 A CN113059828 A CN 113059828A CN 202110431453 A CN202110431453 A CN 202110431453A CN 113059828 A CN113059828 A CN 113059828A
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- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 74
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- 239000002131 composite material Substances 0.000 title claims abstract description 70
- 238000002360 preparation method Methods 0.000 title claims abstract description 37
- 229920003192 poly(bis maleimide) Polymers 0.000 claims abstract description 98
- XQUPVDVFXZDTLT-UHFFFAOYSA-N 1-[4-[[4-(2,5-dioxopyrrol-1-yl)phenyl]methyl]phenyl]pyrrole-2,5-dione Chemical compound O=C1C=CC(=O)N1C(C=C1)=CC=C1CC1=CC=C(N2C(C=CC2=O)=O)C=C1 XQUPVDVFXZDTLT-UHFFFAOYSA-N 0.000 claims abstract description 97
- 229920005989 resin Polymers 0.000 claims abstract description 37
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- 230000009477 glass transition Effects 0.000 claims abstract description 6
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 15
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional 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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/685—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by laminating inserts between two plastic films or plates
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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
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/70—Completely encapsulating inserts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2023/00—Tubular articles
- B29L2023/22—Tubes or pipes, i.e. rigid
Abstract
The invention provides a high-temperature-resistant carbon fiber composite material cylinder bearing layer and a preparation process thereof, which relate to the technical field of composite materials, are mainly used in the aerospace field and are used as external bearing layers of missiles and aerospace transmitters; the invention adopts bismaleimide resin with the glass transition temperature of 260 ℃ as a base material and T800 carbon fiber as a reinforcement material to prepare a unidirectional prepreg as a raw material, and adopts an autoclave molding process to prepare a high-temperature-resistant conical carbon fiber composite cylinder bearing layer; the preparation process comprises the steps of firstly preparing a pressure equalizing plate by using a male die as a die, and then preparing a bearing layer in a mode of matching the male die with the pressure equalizing plate; the bearing layer is paved with one-way prepreg between the male die molding surface and the pressure equalizing plate in a tape-like paving mode, and the paving mode is orthogonal symmetrical paving to ensure the directionality of the fiber and the surface quality of the bearing layer of the cylinder body; the bearing layer of the high-temperature-resistant carbon fiber composite cylinder prepared by the invention meets the use requirement and has high product quality.
Description
Technical Field
The invention relates to the technical field of composite materials, in particular to a high-temperature-resistant carbon fiber composite material cylinder bearing layer and a preparation process thereof.
Background
The carbon fiber composite material has excellent mechanical property, large specific strength and specific rigidity and good weight reduction effect, and is increasingly widely applied in the field of aerospace. The carbon fiber composite material is used for replacing products in the aerospace field, such as outer covers of rocket system products, shells of projectile system products and the like, so that the corresponding system products have more excellent functions, and the comprehensive performance is improved. At present, most of cylinder bearing layer structures applied to the elastic body products in the aerospace field are made of metal materials, high temperature resistance is required, and the maximum service temperature is required to reach more than 250 ℃. Although carbon fiber composite material cylinder bearing layer products are developed by some units or scientific research institutions, the carbon fiber composite material cylinder bearing layer products cannot meet the use requirements of temperature and the appearance quality with high requirements, have the problem of deformation, and cannot meet the assembly precision of the products.
Disclosure of Invention
The invention aims to provide a high-temperature-resistant carbon fiber composite material cylinder bearing layer and a preparation process thereof, and solves the technical problems that the composite material cylinder bearing layer in the prior art is low in appearance quality, cannot meet the use requirement of temperature, and is deformed in use.
In order to achieve the above purpose, the invention provides the following technical scheme: a preparation process of a high-temperature-resistant carbon fiber composite cylinder bearing layer comprises the steps of taking bismaleimide resin one-way prepreg as a raw material, and preparing the high-temperature-resistant carbon fiber composite cylinder bearing layer by adopting a autoclave molding process; when the bearing layer is prepared, the inner side adopts a male die, and the outer side adopts a pressure equalizing plate, so that the preparation errors of the inner side and the outer side of the bearing layer are within a preset precision range.
Further, the specific preparation steps of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder body are as follows:
(2.1) preprocessing a male die;
(2.2) paving a third bismaleimide unidirectional prepreg layer on the pretreated male mould surface;
(2.3) placing a pressure equalizing plate outside the third bismaleimide unidirectional prepreg layer;
(2.4) carrying out vacuum packaging according to an autoclave process, and curing in the autoclave according to a bismaleimide unidirectional prepreg curing system;
(2.5) taking out of the tank and demolding to prepare a bearing layer of the high-temperature-resistant carbon fiber composite material cylinder body;
the size of the inner wall of the pressure equalizing plate is matched with the size of the outer wall of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder.
Further, the preparation steps of the pressure equalizing plate are as follows:
(3.1) attaching and fixing an aluminum plate with the thickness equal to that of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder on the molded surface of the male die, and pretreating the side surface of the aluminum plate away from the molded surface of the male die;
(3.2) sequentially paving a first bismaleimide resin unidirectional prepreg layer, an unvulcanized rubber layer and a second bismaleimide resin unidirectional prepreg layer on the surface of the pretreated aluminum plate;
(3.3) carrying out vacuum packaging according to an autoclave process, and curing in the autoclave according to a bismaleimide unidirectional prepreg curing system;
(3.4) taking out of the tank and demolding to prepare a pressure equalizing plate;
the uniform pressure plate is a sandwich structure obtained by curing a first bismaleimide resin unidirectional prepreg layer, an unvulcanized rubber layer and a second bismaleimide resin unidirectional prepreg layer.
Further, the paving process of the third bismaleimide unidirectional prepreg layer is as follows: the method comprises the following steps that a plurality of bismaleimide unidirectional prepreg material slices are paved on a male die molded surface layer by layer, in the paving process, the first bismaleimide unidirectional prepreg material slice is subjected to vacuum pre-compaction, then, vacuum pre-compaction is performed once according to the condition that three bismaleimide unidirectional prepreg material slices are paved, and after the last bismaleimide unidirectional prepreg material slice is paved, vacuum pre-compaction is performed; the material sheets of any bismaleimide unidirectional prepreg are flatly paved; the pieces of the bismaleimide unidirectional prepreg are spliced in a butt joint mode in the paving and sticking processes, the butt joint seam is smaller than 1mm, and the paving and sticking starting points of each layer are staggered by at least 25 mm.
Further, the layers of the plurality of bismaleimide unidirectional prepreg sheets on the male mould surface are orthogonal and symmetrical layers;
defining the axial direction of the male die to be 0-degree direction, wherein the orthogonal symmetrical layers are 0-degree layer, 45-degree layer, -45-degree layer and 90-degree layer, and the layer proportion is 25%; the paving mode is a mode of simulating automatic tape paving.
Further, defining the length of a high-temperature-resistant carbon fiber composite cylinder force-bearing layer in the vertical direction along the axial section of the high-temperature-resistant carbon fiber composite cylinder body as H, wherein the diameter of the upper end is D1, the diameter of the lower end is D2, and D1 is less than D2; then the process of the first step is carried out,
the blanking graph of the 0-degree layering is a right trapezoid, the length of the short side of the right trapezoid is 50-100 mm, the length of the long side of the right trapezoid is (50-100 mm) × D2/D1, and the height of the right trapezoid is (H +40) mm;
the blanking graphs of the 45-degree layer and the-45-degree layer are both first rectangles, the width of each first rectangle is 30-50 mm, the length of each first rectangle is L, and L is the diagonal length of a fan-shaped graph of the side wall of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder body;
the blanking graph of the 90-degree laminated layer is a second rectangle, the width of the second rectangle is 30mm-50mm, and the length of the second rectangle is pi x D2.
Further, according to the number of 45-degree layers, 45-degree layers and 90-degree layers, uniformly marking the serial number of each layer on the circumference of the end face of the male die; when paving layers of 45 degrees, -45 degrees and 90 degrees, paving reference lines at the upper end and the lower end of the male die, and paving the material sheets of the bismaleimide resin unidirectional prepreg according to a preset paving sequence.
Furthermore, the thickness of the first bismaleimide resin unidirectional prepreg layer in the pressure equalizing plate is 0.5-1.0 mm, and the thickness of the second bismaleimide resin unidirectional prepreg layer in the pressure equalizing plate is 0.5-1.0 mm.
Further, the bismaleimide resin unidirectional prepreg is made of bismaleimide resin with the glass transition temperature of 260 ℃ and T800-grade carbon fiber.
The invention also provides a bearing layer of the high-temperature-resistant carbon fiber composite material cylinder body, which is prepared by adopting the preparation process.
According to the technical scheme, the technical scheme of the invention has the following beneficial effects:
the invention discloses a preparation process of a bearing layer of a high-temperature-resistant carbon fiber composite material cylinder, which adopts bismaleimide resin with the glass transition temperature of 260 ℃ and T800-grade carbon fiber to prepare a unidirectional prepreg, the prepreg is used as a raw material for preparing the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder and is molded by an autoclave molding process; the male die adopts a male die, so that the unidirectional prepreg can be conveniently laid and pasted; the pressure equalizing plate with the sandwich structure is used as the pressure equalizing plate, after the prepreg is laid and attached, the pressure equalizing plate is placed on the outer side of the prepreg, and the appearance quality defects such as folds, depressions and the like on the surface of a product are avoided after curing.
In order to prevent the product from deforming after being cured, the axial direction of a male die is taken as the 0-degree direction during the preparation of the product, and the layering design is carried out according to the orthogonal symmetry principle, wherein the layering is respectively 0-degree layering, 45-degree layering and 90-degree layering, and the layering proportion is 25%; meanwhile, the cooling rate in the curing process is controlled, and the residual stress of the product after curing is reduced; in the laying and cutting processes of the prepreg, the angle of the prepreg is controlled, wherein the blanking graph of a 0-degree laying layer is in a right trapezoid shape, the blanking graphs of a 45-degree laying layer and a-45-degree laying layer are in a rectangular shape, and the blanking graph of a 90-degree laying layer is in a rectangular shape.
In addition, the invention adopts the unvulcanized rubber and the prepreg consistent with the body to prepare the pressure equalizing plate, the pressure equalizing plate is of a sandwich structure, and the mode of the unvulcanized rubber in the middle is adopted, so that the pressure equalizing plate has certain flexibility and rigidity, the curing pressure can be transmitted to the prepreg in the curing process, and the product curing is realized.
The high-temperature-resistant carbon fiber composite material cylinder bearing layer disclosed by the invention is light in weight and high in temperature resistance, and fully meets the application requirements of the current aerospace field.
It should be understood that all combinations of the foregoing concepts and additional concepts described in greater detail below can be considered as part of the inventive subject matter of this disclosure unless such concepts are mutually inconsistent.
The foregoing and other aspects, embodiments and features of the present teachings can be more fully understood from the following description taken in conjunction with the accompanying drawings. Additional aspects of the present invention, such as features and/or advantages of exemplary embodiments, will be apparent from the description which follows, or may be learned by practice of specific embodiments in accordance with the teachings of the present invention.
Drawings
The drawings are not intended to be drawn to scale. In the drawings, each identical or nearly identical component that is illustrated in various figures may be represented by a like numeral. For purposes of clarity, not every component may be labeled in every drawing. Embodiments of various aspects of the present invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic axial section view of a bearing layer of a high-temperature-resistant carbon fiber composite cylinder;
FIG. 2 is a schematic diagram of a package for fabricating a pressure equalization plate;
FIG. 3 is a schematic view of the composition of the pressure equalizing plate;
FIG. 4 is a schematic view of a package for preparing a bearing layer of a high temperature resistant carbon fiber composite cylinder;
figure 5 is a bismaleimide unidirectional prepreg curing regime.
In the figure, the specific meaning of each mark is:
1-a male mold; 2-bearing layer of high temperature resistant carbon fiber composite cylinder; 3-an aluminum plate; 4-bismaleimide unidirectional prepreg; 5-rubber; 6-group of auxiliary materials; 7-vacuum bag film; 8-sealing adhesive tape; 9-sealing adhesive tape; 10-a non-porous barrier film; 11-a pressure equalizing plate; 12-high gram weight airfelt; 13-vacuum quick coupling.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the drawings of the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the described embodiments of the invention without any inventive step, are within the scope of protection of the invention. Unless defined otherwise, technical or scientific terms used herein shall have the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs.
The use of "first," "second," and similar terms in the description and claims of the present application do not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. Similarly, the singular forms "a," "an," or "the" do not denote a limitation of quantity, but rather denote the presence of at least one, unless the context clearly dictates otherwise. The terms "comprises," "comprising," or the like, mean that the elements or items listed before "comprises" or "comprising" encompass the features, integers, steps, operations, elements, and/or components listed after "comprising" or "comprising," and do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. "upper", "lower", "left", "right", and the like are used only to indicate relative positional relationships, and when the absolute position of the object to be described is changed, the relative positional relationships may also be changed accordingly.
When the carbon fiber composite material cylinder bearing layer product developed based on the prior art is applied to the aerospace field as a product shell/cover, on one hand, the scene temperature requirement cannot be met, the product deformation can be caused when the use temperature limit of the product is exceeded, and the assembly precision is obviously reduced; on the other hand, the appearance quality of the product is poor; the invention aims to solve the technical problems and provides a process for preparing a bearing layer by using a hot-pressing tank, which ensures the product quality of the bearing layer of a product in a mode of matching a male die 1 and a pressure equalizing plate 11 by improving the bearing layer raw material, designing and processing parameters and processing steps.
The invention provides a preparation process of a high-temperature-resistant carbon fiber composite material cylinder bearing layer, which is characterized in that bismaleimide resin unidirectional prepreg 4 is used as a raw material, and a high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 is prepared by adopting an autoclave molding process; when the bearing layer is prepared, the male die 1 is adopted on the inner side, and the male die 11 is adopted on the outer side, so that the preparation errors of the inner side and the outer side of the bearing layer are within a preset precision range; in the field of aerospace, the preset precision range of the inner assembly surface of the bearing layer of the cylinder body is 0.05mm-0.2 mm; the bismaleimide resin unidirectional prepreg 4 is made of bismaleimide resin having a glass transition temperature of 260 ℃ and T800-grade carbon fiber.
According to the invention, the uniform pressure plate 11 is prepared by adopting the male die 1, and then the high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 is prepared by combining the male die 1 and the uniform pressure plate 11.
The preparation steps of the pressure equalizing plate 11 are as follows:
(3.1) attaching and fixing an aluminum plate 3 with the thickness equal to that of the bearing layer 2 of the high-temperature-resistant carbon fiber composite cylinder body on the molded surface of the male die 1, and pretreating the side surface of the aluminum plate 3 away from the molded surface of the male die 1;
(3.2) sequentially paving a first bismaleimide resin unidirectional prepreg layer, an unvulcanized rubber layer and a second bismaleimide resin unidirectional prepreg layer on the surface of the pretreated aluminum plate 3;
(3.3) carrying out vacuum packaging according to an autoclave process, and curing in the autoclave according to a bismaleimide unidirectional prepreg curing system;
(3.4) taking out of the tank and demolding to prepare a pressure equalizing plate;
the uniform pressure plate 11 is a sandwich structure obtained by curing a first bismaleimide resin unidirectional prepreg layer, an unvulcanized rubber layer and a second bismaleimide resin unidirectional prepreg layer.
The specific preparation steps of the high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 are as follows:
(2.1) preprocessing the male die 1;
(2.2) paving a third bismaleimide unidirectional prepreg layer on the molded surface of the preprocessed male die 1;
(2.3) placing a pressure equalizing plate 11 on the outer side of the third bismaleimide unidirectional prepreg layer; the size of the inner wall of the pressure equalizing plate 11 is matched with the size of the outer wall of the bearing layer 2 of the high-temperature-resistant carbon fiber composite material cylinder;
(2.4) carrying out vacuum packaging according to an autoclave process, and curing in the autoclave according to a bismaleimide unidirectional prepreg curing system;
and (2.5) taking out of the tank and demoulding to obtain the bearing layer 2 of the high-temperature-resistant carbon fiber composite material cylinder body.
In the above steps, both the pretreatment of the side surface of the aluminum plate 3 far away from the molded surface of the male die 1 and the pretreatment of the molded surface of the male die 1 are cleaned, and a plurality of layers of release agents are uniformly coated; secondly, the thickness of the first bismaleimide resin unidirectional prepreg layer and the thickness of the second bismaleimide resin unidirectional prepreg layer in the prepared uniform pressure plate 11 are both 0.5mm-1.0 mm. In addition, the embodiment of the invention adopts a mode of preparing the pressure equalizing plate 11 and then preparing the bearing layer, but in specific implementation, the invention is not limited to the process flow of self-making the pressure equalizing plate 11, and a mode of outsourcing or directly obtaining the pressure equalizing plate 11 with matched size to prepare the bearing layer 2 of the high-temperature-resistant carbon fiber composite cylinder body also falls within the protection scope of the invention.
The paving process of the third bismaleimide unidirectional prepreg layer in the preparation step (2.2) of the high-temperature-resistant carbon fiber composite cylinder bearing layer 2 is as follows: the method comprises the following steps that a plurality of bismaleimide unidirectional prepreg material slices are paved on a molded surface of a male die 1 layer by layer, in the paving process, the first bismaleimide unidirectional prepreg material slice is subjected to vacuum pre-compaction, then, vacuum pre-compaction is performed once according to three layers of bismaleimide unidirectional prepreg material slices paved and paved, and after the last bismaleimide unidirectional prepreg material slice is paved and paved, vacuum pre-compaction is performed; the material sheets of any bismaleimide unidirectional prepreg are flatly paved. The sheets of the bismaleimide unidirectional prepreg are spliced in a butt joint mode in the paving process, the butt joint seam is smaller than 1mm, and the paving starting points of each layer are staggered by at least 25 mm.
The layers of the material sheets of the bismaleimide unidirectional prepreg on the molded surface of the male die 1 are orthogonal and symmetrical layers; defining the axial direction of the male die to be 0-degree direction, wherein the orthogonal symmetrical layers are 0-degree layer, 45-degree layer, -45-degree layer and 90-degree layer, and the layer proportion is 25%; the layering mode is a mode of simulating automatic tape laying so as to ensure the direction of the fibers and reduce the angle deviation of the fibers.
Defining the length of the high-temperature-resistant carbon fiber composite cylinder force-bearing layer 2 in the vertical direction along the axial section of the cylinder force-bearing layer as H, the diameter of the upper end as D1, the diameter of the lower end as D2, D1 being less than D2; then, the blanking graph of the 0-degree layering is a right trapezoid, the length of the short side of the right trapezoid is 50-100 mm, the length of the long side is (50-100 mm) × D2/D1, and the height is (H +40) mm; the blanking graphs of the 45-degree layer and the-45-degree layer are both first rectangles, the width of each first rectangle is 30-50 mm, the length of each first rectangle is L, and the L is the diagonal length of a fan-shaped graph spread on the side wall of the high-temperature-resistant carbon fiber composite material cylinder bearing layer 2; the blanking graph of the 90-degree laminated layer is a second rectangle, the width of the second rectangle is 30mm-50mm, and the length of the second rectangle is pi x D2.
When the specific steps for preparing the bearing layer 2 of the high-temperature-resistant carbon fiber composite material cylinder body are implemented specifically, the method also comprises the step of uniformly marking the serial numbers of all the layers on the circumference of the end face of the male die according to the number of 45-degree layers, -45-degree layers and 90-degree layers; when paving layers of 45 degrees, -45 degrees and 90 degrees, paving reference lines at the upper end and the lower end of the male die, and paving the material sheets of the bismaleimide resin unidirectional prepreg according to a preset paving sequence.
The detailed preparation process of the high temperature resistant carbon fiber composite material cylinder bearing layer 2 disclosed by the invention is described below with reference to specific embodiments. In the embodiment, the preparation of the high-temperature-resistant carbon fiber composite cylinder bearing layer 2 mainly comprises four stages, namely the preparation of the unidirectional prepreg, the preparation of the uniform pressure plate 11, the laying design and the preparation of the material sheet, and the preparation of the high-temperature-resistant carbon fiber composite cylinder bearing layer 2.
Firstly, preparing unidirectional prepreg
Firstly, bismaleimide resin with the glass transition temperature of 260 ℃ and T800-grade carbon fiber are adopted to prepare bismaleimide unidirectional prepreg 4, the bismaleimide unidirectional prepreg is subjected to two procedures of coating and impregnation to prepare a raw material of a high-temperature-resistant carbon fiber composite material cylinder bearing layer 2, and the raw material is inspected to be qualified and is reserved. The usage amount of the bismaleimide resin is determined according to the resin content in the preset prepreg, the usage amount of the T800-grade carbon fiber is determined according to the fiber volume content, and the content of the bismaleimide resin in the prepreg is 33% -40%.
Secondly, preparing a pressure equalizing plate
As shown in attached figure 2, the surface of the male die 1 is cleaned to be clean and free of dirt, a release agent is coated on the surface of the male die 1, an aluminum plate 3 with the thickness equal to the theoretical thickness of the bearing layer 2 of the high-temperature-resistant carbon fiber composite material cylinder body is fixed on the surface of the male die 1, the gap between the aluminum plate 3 and the male die 1 is smaller than 0.05mm, and the release agent is coated on the surface of the aluminum plate 3.
Paving a bismaleimide unidirectional prepreg 4 on the surface of an aluminum plate 3 to obtain a first paved bismaleimide unidirectional prepreg layer, determining the number of paving layers according to the single-layer thickness of a bismaleimide unidirectional prepreg 4 sheet, wherein the layer thickness of the first bismaleimide unidirectional prepreg layer is 0.5-1.0 mm; then paving and pasting 1-3 layers of unvulcanized rubber 5 on the first bismaleimide unidirectional prepreg layer to obtain an unvulcanized rubber layer, and paving and pasting a bismaleimide unidirectional prepreg 4 to obtain a second bismaleimide unidirectional prepreg layer; the number of the paving layers is determined according to the single-layer thickness of the 4 material sheets of the bismaleimide unidirectional prepreg, and the thickness of the second bismaleimide unidirectional prepreg is 0.5mm-1.0 mm.
After paving, sequentially paving and pasting demolding cloth, a non-porous isolating film, an air felt and a first vacuum bag film 7 according to the auxiliary material paving sequence shown in the attached figure 2, performing bag making according to an autoclave molding process, detecting vacuum, and pushing the male die 1 into an autoclave for curing according to a curing system of the bismaleimide resin one-way prepreg 4 after the pressure maintaining is qualified; after the curing is finished, the auxiliary material is removed, and the pressure equalizing plate 11 can be obtained, wherein the pressure equalizing plate 11 is of a sandwich structure as shown in figure 3.
Thirdly, laying layer design and material sheet preparation
In order to prevent the high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 from generating thermal residual stress after being cured, the axial direction of the male die is defined to be 0-degree direction, and the layering design is carried out according to the orthogonal symmetry principle, wherein the layering design comprises a 0-degree layering layer, a 45-degree layering layer and a 90-degree layering layer, and the layering proportion is 25%.
Combining the axial section view of the high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 of the product shown in fig. 1, defining the length of the high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 along the axial section in the vertical direction as H, the diameter of the upper end as D1, the diameter of the lower end as D2, D1 being less than D2;
in the cutting and laying process of the bismaleimide unidirectional prepreg 4 material sheet, the angle of the bismaleimide unidirectional prepreg 4 is controlled, wherein the blanking graph of 0-degree laying is a right trapezoid, the length of a short side is 50-100 mm, the length of a long side is (50-100 mm) × D2/D1, and the height is (H +40) mm. The blanking graphs of the 45-degree layer and the-45-degree layer are rectangular, the width is 30mm-50mm, the length is L, and L is the diagonal length of the fan-shaped development graph of the bearing layer of the conical cylinder body; the blanking pattern of the 90-degree ply is rectangular, the width is 30mm-50mm, and the length is pi X D2.
Fourthly, preparing a bearing layer of the carbon fiber composite material cylinder body
As shown in the attached figure 4, the surface of the male die 1 is cleaned, a high-temperature resistant release agent is coated for 3-5 times, the cut bismaleimide unidirectional prepreg 4 sheets are paved on the male die 1 layer by layer according to the designed paving sequence, in the paving process, the first bismaleimide unidirectional prepreg 4 sheet is subjected to vacuum pre-compaction, then, the vacuum pre-compaction is performed once according to each paving of 3 bismaleimide unidirectional prepreg 4 sheets, and after the last bismaleimide unidirectional prepreg 4 sheet is paved, the vacuum pre-compaction is performed to obtain a third bismaleimide unidirectional prepreg layer.
In the paving and pasting process, 4 pieces of bismaleimide unidirectional prepreg are spliced in a butt joint mode, the butt joint seam is smaller than 1mm, and the paving and pasting starting points of each layer are staggered by at least 25 mm; the bimaleimide unidirectional prepreg 4 web was not allowed to wrinkle.
After all the bismaleimide unidirectional prepreg 4 pieces are paved, cutting and trimming the redundant bismaleimide unidirectional prepreg 4 pieces along a paving line on the male die 1, paving sealing strips 9 at the upper end and the lower end of each bismaleimide unidirectional prepreg 4 piece, paving a layer of nonporous isolation film on the surface of each bismaleimide unidirectional prepreg 4 piece, namely a first nonporous isolation film, wherein the nonporous isolation film 10 completely adheres to the bismaleimide unidirectional prepreg 4 pieces, then sequentially placing a pressure equalizing plate 11, a second nonporous isolation film and a heavy breathable felt 12, wherein the second nonporous isolation film is the same as the first nonporous isolation film, and then fixing the nonporous isolation film by using a high-temperature resistant pressure sensitive adhesive tape. Pasting sealing rubber strips 8 at the positions of pasting the sealing rubber strips 8 at the two ends of the male die 1, and compacting; placing a base of a vacuum quick connector 13, fixing vacuum bag films 7 on sealing rubber strips 8 at the upper end and the lower end of a male die 1 respectively, connecting a vacuumizing pipeline and a vacuum measuring pipeline to the upper surfaces of the two vacuum quick connectors 13 respectively, starting a vacuum pump, vacuumizing, detecting the vacuum degree, pushing the male die 1 into an autoclave for curing after the vacuum degree reaches over 980mbar and the pressure is maintained to be qualified.
The curing system is as shown in figure 5, the temperature in the autoclave is initially increased to 130 ℃ at the speed of 2 ℃/min, the temperature is kept for 60min, the pressure in the autoclave is increased at the time, and the pressure is increased at the speed of 0.02 Mpa; secondly, heating to 185 ℃ at the speed of 2 ℃/min, and preserving the heat for 120 min; then heating to 210 ℃ at the speed of 2 ℃/min, and preserving heat for 120 min; then, the temperature is increased to 230 ℃ at the speed of 2 ℃/min, and the temperature is kept for 240 min; finally, the temperature is reduced to 50 ℃ at the speed of 15 ℃/min, and the pressure in the tank is increased to 0.6 Mpa. And taking out the cylinder after curing is finished, and demolding to obtain the high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 product.
The other embodiment of the invention provides a high-temperature-resistant carbon fiber composite material cylinder bearing layer 2 prepared by the preparation process, wherein the bearing layer is prepared by the four process steps and a curing system shown in the attached figure 5; the bearing layer is subjected to performance test, and the result shows that the bearing layer can bear the high temperature of 250 ℃, the assembly precision of the assembly surface at the inner side meets the progress requirement of 0.05mm-0.2mm, the outer side is free from folds, depressions and fibers and is free from breakage, and when the bearing layer is applied to the aerospace field, the product quality is stable.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to be limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the invention. Therefore, the protection scope of the present invention should be determined by the appended claims.
Claims (10)
1. A preparation process of a high-temperature-resistant carbon fiber composite cylinder bearing layer is characterized in that bismaleimide resin unidirectional prepreg is used as a raw material, and a autoclave molding process is adopted to prepare the high-temperature-resistant carbon fiber composite cylinder bearing layer; when the bearing layer is prepared, the inner side is formed by adopting a male die, and the outer side is formed by adopting a pressure equalizing plate, so that the preparation errors of the inner side and the outer side of the bearing layer are within a preset precision range.
2. The preparation process of the bearing layer of the high-temperature-resistant carbon fiber composite cylinder body according to claim 1, which is characterized by comprising the following specific preparation steps:
(2.1) preprocessing a male die;
(2.2) paving a third bismaleimide unidirectional prepreg layer on the pretreated male mould surface;
(2.3) placing a pressure equalizing plate outside the third bismaleimide unidirectional prepreg layer;
(2.4) carrying out vacuum packaging according to an autoclave process, and curing in the autoclave according to a bismaleimide unidirectional prepreg curing system;
(2.5) taking out of the tank and demolding to prepare a bearing layer of the high-temperature-resistant carbon fiber composite material cylinder body;
the size of the inner wall of the pressure equalizing plate is matched with the size of the outer wall of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder.
3. The preparation process of the bearing layer of the high-temperature-resistant carbon fiber composite cylinder body according to claim 2, wherein the preparation steps of the pressure equalizing plate are as follows:
(3.1) attaching and fixing an aluminum plate with the thickness equal to that of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder on the molded surface of the male die, and pretreating the side surface of the aluminum plate away from the molded surface of the male die;
(3.2) sequentially paving a first bismaleimide resin unidirectional prepreg layer, an unvulcanized rubber layer and a second bismaleimide resin unidirectional prepreg layer on the surface of the pretreated aluminum plate;
(3.3) carrying out vacuum packaging according to an autoclave process, and curing in the autoclave according to a bismaleimide unidirectional prepreg curing system;
(3.4) taking out of the tank and demolding to prepare a pressure equalizing plate;
the uniform pressure plate is a sandwich structure obtained by curing a first bismaleimide resin unidirectional prepreg layer, an unvulcanized rubber layer and a second bismaleimide resin unidirectional prepreg layer.
4. The preparation process of the bearing layer of the cylinder made of the high-temperature-resistant carbon fiber composite material according to claim 2, wherein the laying and adhering process of the third bismaleimide unidirectional prepreg layer in the step (2.2) is as follows:
the method comprises the following steps that a plurality of bismaleimide unidirectional prepreg material slices are paved on a male die molded surface layer by layer, in the paving process, the first bismaleimide unidirectional prepreg material slice is subjected to vacuum pre-compaction, then, vacuum pre-compaction is performed once according to the condition that three bismaleimide unidirectional prepreg material slices are paved, and after the last bismaleimide unidirectional prepreg material slice is paved, vacuum pre-compaction is performed; the material sheets of any bismaleimide unidirectional prepreg are flatly paved;
the pieces of the bismaleimide unidirectional prepreg are spliced in a butt joint mode in the paving and sticking processes, the butt joint seam is smaller than 1mm, and the paving and sticking starting points of each layer are staggered by at least 25 mm.
5. The preparation process of the high-temperature-resistant carbon fiber composite cylinder bearing layer according to claim 4, wherein the layering of the material sheets of the bismaleimide unidirectional prepreg on the male mould surface is orthogonal symmetrical layering;
defining the axial direction of the male die to be 0-degree direction, wherein the orthogonal symmetrical layers are 0-degree layer, 45-degree layer, -45-degree layer and 90-degree layer, and the layer proportion is 25%; the paving mode is a mode of simulating automatic tape paving.
6. The process for preparing the bearing layer of the cylinder made of the high-temperature-resistant carbon fiber composite material as claimed in claim 5, wherein the length of the bearing layer of the cylinder made of the high-temperature-resistant carbon fiber composite material along the axial section in the vertical direction is defined as H, the diameter of the upper end is D1, the diameter of the lower end is D2, and D1 is less than D2; then the process of the first step is carried out,
the blanking graph of the 0-degree layering is a right trapezoid, the length of the short side of the right trapezoid is 50-100 mm, the length of the long side of the right trapezoid is (50-100 mm) × D2/D1, and the height of the right trapezoid is (H +40) mm;
the blanking graphs of the 45-degree layer and the-45-degree layer are both first rectangles, the width of each first rectangle is 30-50 mm, the length of each first rectangle is L, and L is the diagonal length of a fan-shaped graph of the side wall of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder body;
the blanking graph of the 90-degree laminated layer is a second rectangle, the width of the second rectangle is 30mm-50mm, and the length of the second rectangle is pi x D2.
7. The preparation process of the bearing layer of the high-temperature-resistant carbon fiber composite material cylinder body according to claim 5, characterized by further comprising uniformly marking the serial numbers of all the layers on the circumference of the end face of the male die according to the number of 45-degree layers, -45-degree layers and 90-degree layers; when paving layers of 45 degrees, -45 degrees and 90 degrees, paving reference lines at the upper end and the lower end of the male die, and paving the material sheets of the bismaleimide resin unidirectional prepreg according to a preset paving sequence.
8. The process for preparing the bearing layer of the cylinder made of the high-temperature-resistant carbon fiber composite material according to claim 3, wherein the thickness of the first bismaleimide resin unidirectional prepreg layer in the pressure equalizing plate is 0.5mm-1.0mm, and the thickness of the second bismaleimide resin unidirectional prepreg layer in the pressure equalizing plate is 0.5mm-1.0 mm.
9. The preparation process of the bearing layer of the cylinder made of the high-temperature-resistant carbon fiber composite material according to claim 1, wherein the bismaleimide resin unidirectional prepreg is prepared by taking bismaleimide resin with the glass transition temperature of 260 ℃ as a matrix material and taking T800-grade carbon fiber as a reinforcement material.
10. A bearing layer of a high-temperature-resistant carbon fiber composite cylinder, which is characterized in that the bearing layer is prepared by the preparation process of any one of claims 1 to 9.
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