CN113696520B - Carbon fiber panel and polyimide film co-curing structure and method of body-mounted solar wing - Google Patents
Carbon fiber panel and polyimide film co-curing structure and method of body-mounted solar wing Download PDFInfo
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- CN113696520B CN113696520B CN202110910171.8A CN202110910171A CN113696520B CN 113696520 B CN113696520 B CN 113696520B CN 202110910171 A CN202110910171 A CN 202110910171A CN 113696520 B CN113696520 B CN 113696520B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
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- B29C70/681—Component parts, details or accessories; Auxiliary operations
- B29C70/683—Pretreatment of the preformed part, e.g. insert
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- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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- 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
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- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
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- 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
- B29C70/681—Component parts, details or accessories; Auxiliary operations
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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
- B29C70/78—Moulding material on one side only of the preformed part
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
- B32B27/281—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42 comprising polyimides
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
- B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
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- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
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- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
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Abstract
The invention provides a carbon fiber panel and polyimide film co-curing structure and a method of a body-mounted solar wing, and the method comprises the following steps of 1, cutting a polyimide film, and testing the insulating property of the polyimide film; step 2, preparing a transition buffer layer; step 3, implementing blanking of each layer of prepreg; step 4, sequentially laying each layer of prepreg on the surface of the polyimide film according to the laying sequence requirement of the carbon fiber panel; step 5, laying an isolation material on the surface of the polyimide film and carbon fiber panel prepreg composite, and prepressing and exhausting in a hot-pressing tank; and 6, co-curing the carbon fiber panel and the polyimide film. The co-curing method for the carbon fiber panel and the polyimide film of the body-mounted solar wing adopts one-step co-curing integral molding of the carbon fiber panel and the polyimide film instead of the traditional method of firstly preparing the aluminum panel honeycomb sandwich structure plate and then secondarily gluing and sticking the polyimide film on the outer surface, so that the production efficiency can be greatly improved and the weight of the product can be reduced.
Description
Technical Field
The invention relates to a co-curing structure and method for a carbon fiber panel and a polyimide film of a solar wing with integrated structure and electric function, and belongs to the technical field of small satellite solar wing structures and deep space exploration.
Background
The rapid development of modern engineering structures, particularly the structures of aerospace vehicles, has an urgent need for integrating structural products and functional products, and the urgent needs require that the structural quality be reduced and the materials be saved as much as possible and the requirements on the functional performance of electric, thermal and signal processing be met. The traditional solar wing substrate and the structural support are two independent functional modules, the solar wing substrate mainly bears the functions of mounting a battery piece and supporting the structure, and the structural support mainly bears the functions of supporting the whole satellite structure and transmitting force. The body-mounted solar wing has the advantages that the disadvantage that the structure and the solar wing structure are independently designed in the traditional spacecraft is eliminated, the support and load transfer functions of the spacecraft structure can be realized through inheritance optimization of two subsystems, and the functions of solar wing cell insulation, circuit transmission, equipment connection and the like can also be provided. The body-mounted solar wing structure is adopted by more and more small satellites, the structural mass of the satellite can be reduced to the maximum extent, and the total assembly workload of the satellite is reduced.
The initial-stage body-mounted solar wing is mainly characterized in that a polyimide film is adhered to the surface of a formed aluminum panel honeycomb sandwich structure plate in a secondary adhesive joint mode to meet the requirement of insulating performance between a solar wing cell array and a substrate, the surface of the polyimide film is required to be airtight and free of leakage points, bubble control between the polyimide film and the substrate in the adhering process becomes a difficult problem to overcome, and meanwhile, the secondary curing forming method is long in manufacturing period, long in process line length and high in manufacturing cost. With the insight of the properties of the composite material. The polyimide film is pasted on the carbon fiber panel honeycomb sandwich structure plate, a new thought is provided for the design of the spacecraft, and the novel body-mounted solar wing with the carbon fiber panel honeycomb sandwich is expected to achieve the quality target of lightening the spacecraft. The co-curing forming method of the carbon fiber panel and the polyimide film reduces the use times of the autoclave and greatly reduces the manufacturing cost and the manufacturing period because of one-time integral forming. The co-curing molding does not use adhesive, the manufactured structural member has light weight and small deformation, and the structural member has incomparable advantages for parts such as satellite structures and the like which require light weight and high external dimension precision.
The carbon fiber panel and the polyimide film integrated structure of the solar wing means that the polyimide film is completely attached to the surface of the carbon fiber panel, a gap between the carbon fiber panel and the polyimide film is completely filled with the prepreg resin of the carbon fiber panel, and the phenomenon that air bubbles between the polyimide film with airtight surface and the carbon fiber panel of the solar wing occur must be avoided, and the battery array is catastrophically damaged due to expansion and bulge of tiny air bubbles on the surface of the polyimide film under the vacuum condition of the space. Therefore, the control of bubbles and the control of molding quality in the process of attaching the carbon fiber panel and the polyimide film are key points and difficulties of the co-curing molding process scheme.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the co-curing method of the carbon fiber panel and the polyimide film of the body-mounted solar wing overcomes the defects of long manufacturing period and high manufacturing cost of the existing technology for sticking the polyimide film to the surface of the honeycomb sandwich structure plate of the aluminum panel twice and the defect of difficult control of bubbles in the co-curing technology of the carbon fiber panel and the polyimide film. The co-curing structure of the carbon fiber panel and the polyimide film prepared by the method is tightly attached, has no bubbles visible to naked eyes, and has good forming quality.
The technical scheme provided by the invention is as follows:
in a first aspect, a co-curing method for a carbon fiber panel and a polyimide film of a body-mounted solar wing comprises the following steps:
step 2, preparing a transition buffer layer according to the external dimension of the carbon fiber panel, and matching buckling and wrinkle defects of the carbon fiber and the polyimide film caused by inconsistent contraction due to difference of thermal expansion coefficients of the carbon fiber and the polyimide film;
step 3, preparing prepregs required by carbon fiber panel blanks according to the overall dimension of the carbon fiber panels, and performing blanking of each layer of prepreg;
step 4, sequentially laying each layer of prepreg on the surface of the polyimide film according to the laying sequence requirement of the carbon fiber panel;
step 5, laying an isolation material on the surface of the polyimide film and carbon fiber panel prepreg composite, packaging by adopting a vacuum bag, placing in an autoclave, and pre-pressing and exhausting;
step 6, packaging the assembled co-curing structure of the carbon fiber panel and the polyimide film by using a vacuum bag, placing the packaged co-curing structure into an autoclave, and pressurizing step by step to perform co-curing;
step 7, after the curing is finished, taking the carbon fiber panel and the polyimide film co-curing structure out of the autoclave, and demolding;
and 8, checking the co-curing structure of the carbon fiber panel and the polyimide film after demoulding to obtain the co-curing structure of the carbon fiber panel and the polyimide film of the body-mounted solar wing which meets the requirements.
In a second aspect, a carbon fiber panel and polyimide film co-curing structure of a body-mounted solar wing is manufactured by the carbon fiber panel and polyimide film co-curing method of the body-mounted solar wing.
According to the co-curing structure and the co-curing method for the carbon fiber panel and the polyimide film of the body-mounted solar wing, the structure and the method have the following beneficial effects:
(1) The co-curing structure of the carbon fiber panel and the polyimide film of the body-mounted solar wing prepared by the invention is a novel structure form of the body-mounted solar wing, fills up the technical blank of co-curing and molding the carbon panel and the polyimide film of the body-mounted solar wing, is suitable for prepreg or fabric of epoxy resin and cyanate resin matrix, can be used for aviation and aerospace, can meet the structural performance index requirements of the body-mounted solar wing, and can realize effective weight reduction;
(2) The co-curing method for the carbon fiber panel and the polyimide film of the body-mounted solar wing adopts one-step co-curing integral molding of the carbon fiber panel and the polyimide film instead of adopting the traditional method of firstly molding the aluminum panel honeycomb sandwich structure plate and then secondarily gluing and sticking the polyimide film on the outer surface, so that the production efficiency can be greatly improved and the manufacturing cost can be reduced;
(3) The co-curing method realizes the breakthrough of zero bubbles on the surface of the polyimide film, reduces the internal stress in the carbon panel structure of the solar wing, and can enhance the stability of the co-curing structure of the carbon fiber panel and the polyimide film of the body-mounted solar wing in the high-low temperature environment of-170-100 ℃.
Drawings
FIG. 1 is a schematic plan view of a carbon fiber panel of the body-mounted solar wing according to the present invention;
FIG. 2 is a schematic plan view of a co-curing structure of a carbon fiber panel and a polyimide film of the body-mounted solar wing according to the present invention;
FIG. 3 is a schematic view of prepressing, exhausting and packaging a prepreg assembly of a polyimide film and a carbon fiber panel according to the present invention;
FIG. 4 is a schematic view of co-curing and molding a carbon fiber panel and a polyimide film of the body-mounted solar wing according to the present invention;
FIG. 5 is a circuit diagram of a direct current wet insulation test method for testing the insulation performance of a polyimide film;
FIG. 6 is a circuit diagram of a direct current wet insulation test method for testing the insulation performance of the polyimide film on the surface of the co-curing structure of the carbon fiber panel and the polyimide film.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
According to a first aspect of the invention, a co-curing method for a carbon fiber panel and a polyimide film of a body-mounted solar wing is provided, which comprises the following steps:
step 2, preparing a transition buffer layer according to the external dimension of the carbon fiber panel, and matching the defects of buckling, wrinkling and the like of the carbon fiber and the polyimide film due to inconsistent shrinkage caused by the difference of the thermal expansion coefficients of the carbon fiber and the polyimide film;
step 3, preparing prepregs required by carbon fiber panel blanks according to the overall dimension of the carbon fiber panels, and performing blanking of each layer of prepreg;
step 4, sequentially laying each layer of prepreg on the surface of the polyimide film according to the laying sequence requirement of the carbon fiber panel;
step 5, laying an isolation material on the surface of the polyimide film and carbon fiber panel prepreg combination, packaging by adopting a vacuum bag, placing in an autoclave, and prepressing and exhausting;
step 6, packaging the assembled co-curing structure of the carbon fiber panel and the polyimide film by using a vacuum bag, placing the packaged co-curing structure into an autoclave, and pressurizing step by step to perform co-curing;
step 7, after the curing is finished, taking the carbon fiber panel and the polyimide film co-curing structure out of the autoclave, and demolding;
and 8, checking the co-curing structure of the carbon fiber panel and the polyimide film after demolding, such as the apparent state, the glue content of the carbon fiber panel, the insulating property of the polyimide film and the like, so as to obtain the co-curing structure of the carbon fiber panel and the polyimide film of the body-mounted solar wing which meets the requirements.
In a preferred embodiment, in step 1, the outer dimension of the carbon fiber panel is not less than 800mm. That is, the curing method of the present invention is applicable to large-sized carbon fiber panels, and of course, small-sized carbon fiber panels are also applicable.
The resistivity of the polyimide film is more than or equal to 10 18 Omega cm, coefficient of thermal expansion less than or equal to 2 x 10 -5 (℃ -1 ) Such as 200HN film from KAPTON corporation.
The carbon fiber panel is a large-size carbon fiber panel, and the polyimide film is a non-air-permeable film, so that the co-curing structure of the carbon fiber panel and the polyimide film has great difficulty in exhausting.
In the step 1, a direct current wet detection insulation method is adopted to test the insulation performance of the polyimide film, and the method specifically comprises the following steps: the method comprises the steps of laying a polyimide film on a test platform, forming a circuit loop according to the attached drawing 5, detecting by using a megohmmeter under the condition that the direct-current voltage is 250V, fully filling a conductive medium on the surface of a detection probe at an output end of the megohmmeter to contact the surface of the polyimide film, contacting the detection probe at an input end of the megohmmeter to the conductive test platform, forming a current loop between the detection probe and the test platform by using a liquid conductive medium if a penetrable leak point exists on the surface of the polyimide film, displaying the insulation resistance value of the polyimide film by using the megohmmeter to be less than 20M omega, and when the surface of the polyimide film has no penetrable leak point, enabling the insulation resistance value to be more than 20M omega and meeting the requirement of insulation performance.
Further, when the overall dimension of the carbon fiber panel is larger than the width of the polyimide film, the polyimide film corresponding to the overall dimension of the carbon fiber panel is obtained by overlapping a plurality of polyimide films; preferably, the overlapping position of the polyimide films is arranged at the middle line position of the carbon fiber panel, and the overlapping range of the polyimide films is required to be 10mm-50mm.
Specifically, the step of obtaining the polyimide film corresponding to the external dimension of the carbon fiber panel by overlapping a plurality of polyimide films is obtained by:
(1) Coating an adhesive on the overlapping surface of the adjacent polyimide films; the adhesive is epoxy or silicon rubber normal temperature curing adhesive liquid which can bear the curing temperature of the carbon fiber panel prepreg at the using temperature.
(2) Covering a flexible cushion layer, such as a rubber cushion layer, on the surface of the lapped polyimide film;
(3) And placing a heavy object on the flexible cushion layer for pressurization until the curing of the adhesive is completed, wherein no bubble is formed at the overlapping position of the cured polyimide film.
In a preferred embodiment, in step 2, the transition buffer layer is made of a woven or prefabricated fabric material with a thermal expansion coefficient lower than that of the polyimide film and a thickness of 0.05-0.3mm, and the fabric is impregnated with the same resin matrix as the carbon fiber panel prepreg.
Further, the gel content of the transition buffer layer is controlled to be between 35wt% and 65wt%, preferably between 40wt% and 50wt%, and can be adjusted according to the external dimension of the carbon fiber panel, that is, the larger the external dimension of the carbon fiber panel is, the larger the gel content of the selected transition buffer layer is.
In a preferred embodiment, in step 3, the prepreg is a unidirectional prepreg or a fabric prepreg prepared by a wet method, a dry method or a two-step method, and an epoxy resin or cyanate resin matrix is adopted.
In a preferred embodiment, step 4 comprises the following sub-steps:
step 4.1, laying a polyimide film on the surface of the carbon backing plate, driving bubbles between the polyimide film and the carbon backing plate, and requiring close adhesion between the polyimide film and the carbon backing plate until no bubbles are visible to naked eyes;
step 4.2, laying a transition buffer layer on the upper surface of the polyimide film;
and 4.3, paving a first layer of paving prepreg on the upper surface of the transition buffer layer, and paving other paving prepregs in sequence.
Further, in step 4.1, the carbon backing plate is cleaned before use, no protrusion or sharp point is required, after the cleaning is finished, the single-sided adhesive isolation cloth, such as teflon isolation cloth, is pasted on the surface of the carbon backing plate, then the polyimide film is laid, the polyimide film and the isolation cloth are integrated, bubbles between the polyimide film and the single-sided adhesive isolation cloth are driven, and the polyimide film and the single-sided adhesive isolation cloth are required to be tightly pasted until no bubbles visible to naked eyes exist.
Further, in step 4.3, the gel content of the first ply prepreg should be higher than that of the other plies, the gel content is controlled to be between 35wt% and 65wt%, preferably between 40wt% and 50wt%, and the gel content can be adjusted according to the external dimension of the carbon fiber panel, that is, the larger the external dimension of the carbon fiber panel is, the larger the gel content of the selected transition buffer layer is.
In a preferred embodiment, in step 5, the pre-pressing air-discharging process parameters include: the temperature is 80-90 ℃, the pressure is 0.2-0.4 MPa, and the time is 30-90 min.
In step 5, the isolation material laid on the surface of the polyimide film + carbon fiber panel prepreg assembly sequentially comprises from bottom to top: the outer surface of the air permeable felt is covered with a vacuum bag, and the vacuum bag and a packaging platform of the autoclave form a sealed space through sealant.
In a preferred embodiment, in step 6, the co-curing process parameters include: the temperature is 130-180 ℃, the pressure is 0.4-0.8 MPa, and the time is 120-240 min.
In step 6, an isolation material is laid on the surface of the assembled co-curing structure of the carbon fiber panel and the polyimide film, and the isolation material sequentially comprises from bottom to top: the outer surface of the breathable felt is covered with a vacuum bag, and the vacuum bag and a packaging platform of the autoclave form a sealed space through sealant.
In a preferred embodiment, in the step 8, the step of testing the insulating property of the polyimide film on the surface of the co-cured structure of the carbon fiber panel and the polyimide film by using a direct current wet test insulation method is realized by the following steps:
form the circuit loop according to fig. 6, use the megohmmeter to detect under the direct current voltage is 250V state, megohmmeter output test probe surface is full of conductive medium contact polyimide film surface, megohmmeter input test probe contact electrically conductive carbon fiber panel, if there is the penetrability leak source on polyimide film surface, liquid conductive medium can form the current loop between test probe and carbon fiber panel, the megohmmeter shows that carbon fiber panel and polyimide film solidify structure surface polyimide film insulation resistance value altogether, be less than 20M omega, when there is no penetrability leak source on polyimide film surface, insulation resistance value is greater than 20M omega, satisfy the insulating properties requirement.
Example 1
A co-curing method for a carbon fiber panel and a polyimide film of a body-mounted solar wing is disclosed, as shown in FIG. 1, the body-mounted solar wing has a profile structure as a whole, and the maximum profile dimension is 1397 × 1400;
2, selecting a proper lapping position of the polyimide film according to the external dimension of the carbon fiber panel, enabling the lapping position to be located at the middle line position of the carbon fiber panel, enabling the lapping width to be 20mm, using a J-133 adhesive to complete the gluing of the polyimide film, covering a flexible cushion layer on the surface of the lapped polyimide film, placing a heavy object to provide adhesive curing pressure, and completing the curing molding;
step 3, selecting glass cloth with the thermal expansion coefficient lower than that of the polyimide film and the thickness of 0.1mm as a buffer transition layer, impregnating the fabric with epoxy 648 resin which is the same as the carbon panel prepreg, and controlling the gel content at 42% to prepare the glass cloth prepreg;
step 4, preparing epoxy 648 resin prepreg required by a carbon fiber panel blank according to the overall dimension of the carbon fiber panel, and blanking each angle layer;
step 5, paving Teflon isolation cloth with glue on one surface on the surface of the carbon backing plate, then paving the spliced polyimide film, extruding the polyimide film from the center to the periphery by using a flexible roller tool, and discharging bubbles between the polyimide film and the carbon backing plate isolation cloth until no bubbles are visible to naked eyes; laying a glass cloth prepreg transition buffer layer on the upper surface of the polyimide film; and laying a first layer of 0-degree angle layer prepreg on the upper surface of the transition buffer layer, and sequentially finishing the laying of +45 degrees, -45 degrees and 90-degree angle layer prepregs. The glue content of the first layer of the laying prepreg is higher than that of other layers, and the glue content is controlled to be 42wt%.
As shown in fig. 2, the cross-sectional cut view of the co-cured structure of the carbon fiber panel and the polyimide film of the integrally-assembled solar wing is shown, the outer surface of the structure is the polyimide film with the thickness of 0.05mm, and the carbon fiber prepreg assembly formed by 4 layers of unidirectional prepreg laying layers (0 °, +45 °, -45 °,90 °) is sequentially arranged from outside to inside, and the whole structure is integrally formed by matrix resin adhesive, so that the co-cured structure of the carbon fiber panel and the polyimide film of the integrally-assembled solar wing is formed.
Step 6, laying isolation materials (breathable fluorine cloth, adhesive paper and breathable felt) on the surface of the polyimide film and carbon fiber panel prepreg combination body, packaging by adopting a vacuum bag, placing in an autoclave, and performing hot pre-pressing exhaust, wherein the technological parameters comprise: the temperature is 80 deg.C, the pressure is 0.3 MPa, and the time is 60min. Checking the surface state of the assembly after hot pre-pressing, and if wrinkles, bulges and other phenomena occur, repeating the steps again until the surface of the assembly after hot pre-pressing is flat and uniform;
FIG. 3 is a schematic diagram of prepressing and exhausting of a polyimide film and carbon panel prepreg assembly, in which a carbon fiber panel prepreg is placed on the surface of a carbon pad according to the angle requirement, various layers of isolation materials are placed according to the mode shown in the figure to complete hot prepressing and packaging, gas between the polyimide film and the carbon panel prepreg is exhausted under the hot pressing condition, gaps between the various layers are filled with resin, and hot prepressing and exhausting of the polyimide film and carbon panel prepreg assembly is completed.
And 7, packaging the assembled co-curing structure of the carbon fiber panel and the polyimide film by using a vacuum bag, putting the isolation materials of breathable fluorine cloth and breathable felt into an autoclave for co-curing, wherein the process parameters comprise: the temperature is 160 ℃, the pressure is 0.4MPa, and the time is 150min.
Fig. 4 is a schematic view of co-curing and molding a carbon fiber panel and a polyimide film of a body-mounted solar wing. The bottom is a carbon cushion plate with the surface flatness of 0.05/100 multiplied by 100 and without concave pits and bulges on the surface, the layers of the carbon fiber panel and the polyimide film laminated plate are laid on the carbon cushion plate, after all the layers are laid in a hot prepressing mode, each layer of isolation material is placed according to the requirements in the drawing, the isolation material is packaged by using a vacuum bag, and the whole body is cured and formed.
Step 8, after the curing is finished, taking the carbon fiber panel and the polyimide film co-curing structure out of the autoclave, and demolding;
and 9, checking the apparent state of the co-curing structure of the carbon fiber panel and the polyimide film after demolding, wherein the requirement that no bulge or sharp point exists and no bubble or pit with the diameter larger than 0.1mm exists is met, weighing, calculating the gel content of the carbon panel, testing the insulating property of the polyimide film by adopting a wet-check insulation method, and meeting the requirement that the number of leaking points is not more than 3, thus finally preparing the co-curing structure of the carbon fiber panel and the polyimide film of the body-mounted solar wing which meets the requirement.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (8)
1. A co-curing method for a carbon fiber panel and a polyimide film of a body-mounted solar wing is characterized by comprising the following steps of:
step 1, cutting a polyimide film with a corresponding external dimension according to the external dimension of a carbon fiber panel, testing the insulating property of the polyimide film, and selecting the polyimide film with the insulating property meeting the requirement;
step 2, preparing a transition buffer layer according to the overall dimension of the carbon fiber panel, and the transition buffer layer is used for buffering and matching buckling and wrinkling defects caused by inconsistent shrinkage due to difference of thermal expansion coefficients of the carbon fiber and the polyimide film; the transition buffer layer is made of woven or prefabricated fabric materials with thermal expansion coefficients lower than that of the polyimide film, the fabric is impregnated with a resin matrix which is the same as that of a prepreg of the carbon fiber panel, the gel content of the transition buffer layer is controlled to be 35-65 wt%, the gel content is adjusted according to the overall dimension of the carbon fiber panel, and the larger the overall dimension of the carbon fiber panel is, the larger the gel content of the selected transition buffer layer is;
step 3, preparing prepregs required by carbon fiber panel blanks according to the overall dimension of the carbon fiber panels, and performing blanking of each layer of prepreg;
step 4, sequentially laying each layer of prepreg on the surface of the polyimide film according to the laying sequence requirement of the carbon fiber panel; specifically, the method comprises the following steps: step 4.1, laying a polyimide film on the surface of the carbon backing plate, driving bubbles between the polyimide film and the carbon backing plate, and requiring close adhesion between the polyimide film and the carbon backing plate until no bubbles are visible to naked eyes;
step 4.2, laying a transition buffer layer on the upper surface of the polyimide film;
4.3, paving a first layer of laying prepreg on the upper surface of the transition buffer layer, and sequentially paving other laying prepregs; the glue content of the first layer of spread prepreg is higher than that of other layers, the glue content is controlled to be 35-65 wt%, the glue content is adjusted according to the external dimension of the carbon fiber panel, and the larger the external dimension of the carbon fiber panel is, the larger the glue content of the selected first layer of spread prepreg is;
step 5, laying an isolation material on the surface of the polyimide film and carbon fiber panel prepreg composite, packaging by adopting a vacuum bag, placing in an autoclave, and pre-pressing and exhausting;
step 6, packaging the assembled co-curing structure of the carbon fiber panel and the polyimide film by using a vacuum bag, placing the packaged co-curing structure into an autoclave, and pressurizing step by step to perform co-curing;
step 7, after the curing is finished, taking the carbon fiber panel and the polyimide film co-curing structure out of the autoclave, and demolding;
and 8, checking the co-curing structure of the carbon fiber panel and the polyimide film after demolding to obtain the co-curing structure of the carbon fiber panel and the polyimide film of the body-mounted solar wing meeting the requirements.
2. The co-curing method of the carbon fiber panel and the polyimide film of the body-mounted solar wing according to claim 1, wherein in the step 1, the outer dimension of the carbon fiber panel is not less than 800mm.
3. The co-curing method of the carbon fiber panel and the polyimide film of the body-mounted solar wing according to claim 1, wherein in step 1, the resistivity of the polyimide film is not less than 10 18 Omega cm, coefficient of thermal expansion less than or equal to 2 x 10 -5 (℃ -1 )。
4. The co-curing method of the carbon fiber panel and the polyimide film of the body-mounted solar wing according to claim 1, wherein in the step 1, a direct current wet test insulation method is adopted to test the insulation performance of the polyimide film, and the method specifically comprises the following steps:
the method comprises the steps of laying a polyimide film on a test platform, using a megohmmeter to detect under the condition that direct-current voltage is 250V, filling a conductive medium on the surface of a detection probe at an output end of the megohmmeter to be in contact with the surface of the polyimide film, contacting the conductive test platform with the detection probe at an input end of the megohmmeter, and forming a current loop between the detection probe and the test platform by using a liquid conductive medium if the surface of the polyimide film has a penetrable leak point, wherein the megohmmeter shows the insulation resistance value of the polyimide film, which is less than 20M omega, and when the surface of the polyimide film has no penetrable leak point, the insulation resistance value is greater than 20M omega, so that the requirement on insulation performance is met.
5. The co-curing method of the carbon fiber panel and the polyimide film of the body-mounted solar wing according to claim 1, wherein in the step 1, when the external dimension of the carbon fiber panel is larger than the width of the polyimide film, the polyimide film corresponding to the external dimension of the carbon fiber panel is obtained by overlapping a plurality of polyimide films; the lapping position of the polyimide films is arranged at the middle line position of the carbon fiber panel, and the lapping range between the polyimide films is required to be 10mm-50mm.
6. The co-curing method of the carbon fiber panel and the polyimide film of the body-mounted solar wing according to claim 1, wherein in the step 2, the thickness of the transition buffer layer is between 0.05mm and 0.3 mm.
7. The method for co-curing the carbon fiber panel and the polyimide film of the body-mounted solar wing according to claim 1, wherein in the step 5, the release materials laid on the surface of the prepreg combination of the polyimide film and the carbon fiber panel sequentially comprise, from bottom to top: the outer surface of the breathable felt is covered with a vacuum bag, and the vacuum bag and a packaging platform of the autoclave form a sealed space through sealant;
in step 6, an isolation material is laid on the surface of the assembled co-curing structure of the carbon fiber panel and the polyimide film, and the isolation material sequentially comprises the following components from bottom to top: the outer surface of the breathable felt is covered with a vacuum bag, and the vacuum bag forms a sealed space with a packaging platform of the autoclave through sealant.
8. A carbon fiber panel and polyimide film co-curing structure of a body-mounted solar wing is characterized by being prepared by the carbon fiber panel and polyimide film co-curing method of the body-mounted solar wing, wherein the carbon fiber panel and polyimide film are as claimed in any one of claims 1 to 7.
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| WO2015087885A1 (en) * | 2013-12-09 | 2015-06-18 | 日立化成株式会社 | Mold-release polyimide film with adhesive layer, laminated board having mold-release polyimide film with adhesive layer, laminated board, single-layer or multilayer wiring board having mold-release polyimide film with adhesive layer, and method for producing multilayer wiring board |
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| CN101320760B (en) * | 2008-07-11 | 2010-12-15 | 北京航空航天大学 | Solar cell module and preparation method thereof |
| CN106584931A (en) * | 2016-11-23 | 2017-04-26 | 北京空间机电研究所 | Method of pasting polyimide film on surface of grid panel honeycomb sandwich structure |
| CN109065670B (en) * | 2018-08-08 | 2019-12-20 | 长春长光宇航复合材料有限公司 | Preparation method of carbon fiber composite material grid skin solar cell array substrate |
| CN110744833B (en) * | 2019-09-20 | 2021-04-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Carbon nano tube film/composite material forming method and lightning protection structure manufactured by same |
| CN111863993B (en) * | 2020-06-28 | 2022-05-27 | 上海宇航系统工程研究所 | Substrate structure suitable for flexible solar wing and forming method thereof |
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| WO2015087885A1 (en) * | 2013-12-09 | 2015-06-18 | 日立化成株式会社 | Mold-release polyimide film with adhesive layer, laminated board having mold-release polyimide film with adhesive layer, laminated board, single-layer or multilayer wiring board having mold-release polyimide film with adhesive layer, and method for producing multilayer wiring board |
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