CN109676958B - Co-curing molded carbon fiber composite material airfoil and preparation method thereof - Google Patents
Co-curing molded carbon fiber composite material airfoil and preparation method thereof Download PDFInfo
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- CN109676958B CN109676958B CN201811432386.8A CN201811432386A CN109676958B CN 109676958 B CN109676958 B CN 109676958B CN 201811432386 A CN201811432386 A CN 201811432386A CN 109676958 B CN109676958 B CN 109676958B
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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
- B29C70/345—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 matched moulds
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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
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the application field of carbon fiber composite materials, and particularly relates to a co-curing molding airfoil made of a carbon fiber composite material and a preparation method of the airfoil. The co-curing molded carbon fiber composite material airfoil is characterized in that: the airfoil comprises a head prefabricated body and an airfoil prefabricated body, wherein the head prefabricated body and the airfoil prefabricated body are integrally glued, and carbon fiber prepreg paving layers are formed on the surfaces of the head prefabricated body and the airfoil prefabricated body in a coating and curing mode. The invention decomposes the structure of the airfoil, adopts the process of split processing, combination and solidification for production, firstly carries out primary molding on the head prefabricated part, and then carries out secondary composite molding on the head prefabricated part and the main structure of the airfoil, the split processing can reduce the processing difficulty of each component, improve the production efficiency, is also beneficial to improving the precision of products, and further, the processing difficulty is reduced, so that the processing of more complex profile structures becomes possible, and the production requirements with higher requirements are met.
Description
Technical Field
The invention belongs to the application field of carbon fiber composite materials, and particularly relates to a co-curing molding airfoil surface made of carbon fiber composite materials and a preparation method of the airfoil surface.
Background
The missile wing is a main bearing structural part of the missile. The carbon fiber composite missile wing can reduce the mass of a missile hanging on a plane and increase the range and the effective load. Through years of research and tests, the technical problems of mold design and manufacture of large-size complex components, integral layering, curing, demolding and the like of the framework with the main joint are solved, the technical keys of gluing, assembling and the like are overcome, and the carbon fiber composite material missile wing meeting the requirements is successfully developed.
The traditional missile wing is mostly made of metal materials (such as steel, aluminum alloy, titanium alloy and the like), and can well meet the requirements of bearing capacity and high temperature resistance, but the metal missile wing has a heavy structure and can influence the technical indexes such as the effective range of the missile. In contrast, the composite material has the advantages of high specific strength, large specific stiffness, strong designability and the like, so that the composite material is widely applied to aerospace structures in recent years, at present, the composite material is applied to missile wings to a certain extent, but for missile wing structures with complex internal reinforced rib, the processing and manufacturing technical difficulty of the composite material structure is very high, the production cost is greatly increased, and even processing cannot be realized, so that the development of a high-temperature-resistant composite material missile wing structure is not slow.
Disclosure of Invention
In order to overcome the defects of the prior art,
the technical scheme of the invention is as follows:
the co-curing molded carbon fiber composite material airfoil is characterized in that: the airfoil comprises a head prefabricated body and an airfoil prefabricated body, wherein the head prefabricated body and the airfoil prefabricated body are integrally glued, and carbon fiber prepreg paving layers are formed on the surfaces of the head prefabricated body and the airfoil prefabricated body in a coating and curing mode.
The head prefabricated body comprises a metal lining, a carbon fiber preformed body is formed around the metal lining in a curing mode, and the carbon fiber preformed body and the metal lining are connected into a whole.
The outer surface of the metal lining is at least provided with a limiting part matched with the carbon fiber preformed body.
The airfoil prefabricated part comprises a middle prefabricated part and edge prefabricated parts positioned on the upper side and the lower side of the middle prefabricated part, and the middle prefabricated part is glued with the head prefabricated part.
The middle prefabricated body comprises a core body, and the surface of the core body is paved with a conformal carbon fiber prepreg.
The preparation method of the co-cured carbon fiber composite material airfoil is characterized by comprising the following steps of: the method comprises the following steps:
step 1: manufacturing a head prefabricated body mould and an integral mould, and finishing the processing of the metal lining; and the light material is made into an airfoil core body and an edge core body;
step 2: positioning a metal lining in a head preform mould, filling carbon fiber prepreg around the metal lining, and curing and molding to obtain a head preform;
and step 3: positioning the head prefabricated body obtained in the step (2) and the airfoil core body in an integral mold, connecting the head prefabricated body and the airfoil core body into a whole in a gluing mode, and integrally coating and laying by using carbon fiber prepreg to prepare an airfoil main body structure;
and 4, step 4: and placing edge core bodies on the upper side and the lower side of the airfoil core body of the airfoil main body structure, performing skin laying by using a warp knitting fabric, closing the mold, injecting glue, curing, and waiting for the complete airfoil.
The integral cladding and paving layer comprises the following paving steps: a. b, paving airfoil layers with the same shapes as the upper surface and the lower surface of the airfoil core on the upper surface and the lower surface of the airfoil core, and c, repeating a-b until the paved carbon fiber prepreg reaches the designed thickness.
The whole coating layer and the airfoil layer are paved into 33 layers in total, and precompaction is carried out once every 11 layers.
The angle difference between the carbon fiber prepreg in the step a and the carbon fiber of the carbon fiber prepreg used in the step b is +/-45 degrees.
And 3, arranging a head core body around the head prefabricated body of the airfoil main body structure.
In conclusion, the invention has the following beneficial effects:
1. the invention decomposes the structure of the airfoil, adopts the process of split processing, combination and solidification for production, firstly carries out primary molding on the head prefabricated part, and then carries out secondary composite molding on the head prefabricated part and the main structure of the airfoil, the split processing can reduce the processing difficulty of each component, improve the production efficiency, is also beneficial to improving the precision of products, and further, the processing difficulty is reduced, so that the processing of more complex profile structures becomes possible, and the production requirements with higher requirements are met.
2. The metal bushing is used as an insert, so that the high specific strength, the large specific modulus and the good fatigue resistance of the airfoil are ensured, the carbon fiber prepreg is coated on the periphery of the metal bushing to ensure the corrosion resistance of the metal bushing and prolong the service life of the metal bushing, and the carbon fiber composite material is used for manufacturing the airfoil, so that the airfoil has the characteristics of low vibration, low noise, light weight, high efficiency and corrosion resistance.
Drawings
FIG. 1 is a schematic structural view of an airfoil according to the present invention;
FIG. 2 is a schematic cross-sectional view of FIG. 1;
FIG. 3 is a schematic structural view of a metal bushing;
FIG. 4 is a schematic view of a core of the structure of an intermediate preform;
FIG. 5 is a schematic view of a carbon fiber lay-up of an intermediate preform.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1 and 2, the co-cured carbon fiber composite airfoil is characterized in that: the airfoil-shaped carbon fiber prepreg comprises a head prefabricated body 6 and an airfoil prefabricated body 7, wherein the head prefabricated body 6 and the airfoil prefabricated body 7 are integrally glued, and carbon fiber prepreg paving layers 8 are formed on the surfaces of the head prefabricated body 6 and the airfoil prefabricated body 7 in a coating and curing mode.
The airfoil comprises a head prefabricated body and an airfoil prefabricated body, and is processed in a separate processing mode, so that the processing difficulty of each component can be reduced, the production efficiency is improved, the precision of a product can be ensured, further, the processing difficulty is reduced, the processing of a more complex profile structure is possible, and the production requirement with higher requirements is met; the metal bushing is used as an insert, so that the high specific strength, the large specific modulus and the good fatigue resistance of the airfoil are ensured, the carbon fiber prepreg is coated on the periphery of the metal bushing to ensure the corrosion resistance of the metal bushing and prolong the service life of the metal bushing, and the carbon fiber composite material is used for manufacturing the airfoil, so that the airfoil has the characteristics of low vibration, low noise, light weight, high efficiency and corrosion resistance.
The head prefabricated part 6 comprises a metal bushing 1, the metal bushing 1 is circular in shape, an inner hole is further formed in the metal bushing, a key groove 11 for transmitting torque is formed in the hole wall of the inner hole, and the metal bushing is made of stainless steel or titanium alloy; the periphery of the metal lining 1 is cured and molded with a carbon fiber preformed body 2, the carbon fiber preformed body can be formed by laying carbon fiber prepreg or stacking and pressing short carbon fiber materials, and the carbon fiber preformed body and the metal lining are connected into a whole.
As shown in fig. 3, the outer surface of the metal bushing 1 is provided with at least one limiting portion 12 matched with the carbon fiber preform, the arranged limiting portion increases circumferential limitation between the metal bushing and the carbon fiber preform, so that relative movement between the metal bushing and the carbon fiber preform is avoided, and reliability of the metal bushing and the carbon fiber preform is ensured.
The airfoil preform 7 comprises a middle preform 3 and edge preforms 4 and 5 positioned on the upper side and the lower side of the middle preform, the middle preform 3 is glued with a head preform 6, the airfoil preform is processed in a separately forming mode, the airfoil preform is processed firstly, then the edge preforms are placed on the upper side and the lower side of the middle preform of the airfoil, and the whole processing difficulty and the processing cost are reduced through separate processing.
As shown in fig. 4 and 5, the intermediate preform 3 includes a core 30, a conformal carbon fiber prepreg 31 is laid on the surface of the core 30, the core and the edge preform are formed by PMI foam processing, the core is a variable cross-section member, the cross section of the joint of the core and the head preform is smaller than that of the end of the core, when laying, the length of the conformal carbon fiber prepreg laid on the surface of the core is shortened along with the increase of the number of layers of the laying, for example, the conformal laying of the first core surface is laid from one end of the core to the other end, the conformal laying of the second core surface is laid from one end of the core to the position 0.5cm away from the other end, the length of the conformal carbon fiber prepreg laid on the surface of the core is continuously shortened along with the increase of the number of layers of the laying, and the structural strength of the joint of the head preform and the airfoil preform is ensured by adopting the above structure, the problem of fracture of the glued joint can not occur. Meanwhile, the using amount of the carbon fiber prepreg can be reduced, so that the production cost of the product is effectively controlled.
The preparation method of the co-cured carbon fiber composite material airfoil is explained below;
the preparation method of the co-cured carbon fiber composite material airfoil is characterized by comprising the following steps of: the method comprises the following steps:
step 1: manufacturing a head prefabricated body mould and an integral mould, and finishing the processing of the metal lining; and the light material is made into the wing surface core body, the front edge part core body and the rear edge part core body; the light material is PMI foam.
Step 2: positioning a metal lining in a head preform mould, filling carbon fiber prepreg around the metal lining, and curing and molding to obtain a head preform;
and step 3: positioning the head prefabricated body obtained in the step (2) and the airfoil core body in an integral mold, connecting the head prefabricated body and the airfoil core body into a whole in a gluing mode, and integrally coating and laying by using carbon fiber prepreg to prepare an airfoil main body structure;
and 4, step 4: laying a head core body and a front edge core body and a rear edge core body on the outer side and the front edge of the head part of the airfoil main structure, covering and laying a skin by using a warp-knitted fabric, closing a die, injecting glue and curing, automatically finishing the glue injection process by using a glue injection machine in the glue injection process, closing a gas outlet when continuous bubble-free glue solution emerges from the gas outlet of a die, continuously operating the glue injection machine until the pressure of 0.2-0.3Mpa is applied to a die cavity, closing a glue injection port, performing curing after the glue injection is finished, heating the die to 130 ℃, then preserving heat for two hours, removing a product after the curing is finished, polishing and finishing to obtain a finished product.
The carbon fiber composite material is firstly used for preparing the airfoil, compared with the traditional metal airfoil, the carbon fiber composite material has the advantages of better rigidity, strong leather resistance, good damping and shock absorption properties, corrosion resistance, long service life and the like, and secondly, the head and the airfoil are processed and preprocessed separately and then integrally and co-cured and molded at one time, so that the assembly flow is reduced, the production efficiency is improved, the production cost of the airfoil is reduced, and the low-cost production is realized.
The integral cladding and paving layer comprises the following paving steps: a. the method comprises the steps of paving integrally-coated carbon fiber prepreg on a head prefabricated body and an airfoil core body to form an integral coating layer 310, b, paving airfoil layer 311 on the upper surface and the lower surface of the airfoil core body, wherein the shape of the airfoil layer is the same as that of the upper surface and the lower surface of the airfoil core body, c, repeating a-b till the paved carbon fiber prepreg reaches the designed thickness, and alternately paving the integral carbon fiber prepreg and the conformal carbon fiber prepreg to avoid a structural strength weak area in a certain direction and ensure the integral structural strength of the airfoil, wherein in the actual operation process, the thickness of the integral coating layer formed in a is 0.125mm, and the thickness of the airfoil layer formed in b is 0.125 mm.
33 layers are paved on the whole coating layer and the airfoil surface paving layer, and each 11 layers are pre-compacted once, the pre-solidification is performed by vacuumizing, so that defects among the carbon fiber prepreg after paving are avoided, and the problem of product quality defects is avoided.
A in the carbon fiber prepreg with b in the used carbon fiber prepreg's of carbon fiber angular difference be ± 45, adopt the carbon fiber prepreg of different angles to spread the layer, avoid adopting the carbon fiber on the same side to appear the mechanics weak on certain direction, be favorable to improving the structural strength of product, for example, actually spread the layer in-process: and (b) laying a layer by adopting 0-degree carbon fiber prepreg, laying a layer by adopting 45-degree carbon fiber prepreg in the step (a), and then laying a layer by adopting 90-degree carbon fiber prepreg in the step (a) and laying a layer by adopting-45-degree carbon fiber prepreg in the step (b) when circulating the step (a-b).
The resin adopted by the carbon fiber prepreg is bismaleimide resin, the viscosity is 200-600mPa.S, and the epoxy value is 0.4-0.6.
In conclusion, the invention has the following beneficial effects:
1. the invention decomposes the structure of the airfoil, adopts the process of split processing, combination and solidification for production, firstly carries out primary molding on the head prefabricated part, and then carries out secondary composite molding on the head prefabricated part and the main structure of the airfoil, the split processing can reduce the processing difficulty of each component, improve the production efficiency, is also beneficial to improving the precision of products, and further, the reduction of the difficulty also enables the processing of more complex profile structures to become possible, and meets the production requirements with higher requirements.
2. The metal bushing is used as an insert, so that the high specific strength, the large specific modulus and the good fatigue resistance of the airfoil are ensured, the carbon fiber prepreg is coated on the periphery of the metal bushing to ensure the corrosion resistance of the metal bushing and prolong the service life of the metal bushing, and the carbon fiber composite material is used for manufacturing the airfoil, so that the airfoil has the characteristics of low vibration, low noise, light weight, high efficiency and corrosion resistance.
Claims (9)
1. The co-curing molded carbon fiber composite material airfoil is characterized in that: the novel airfoil comprises a head prefabricated body and an airfoil prefabricated body, wherein the head prefabricated body and the airfoil prefabricated body are integrally glued, carbon fiber prepreg paving layers are formed on the surfaces of the head prefabricated body and the airfoil prefabricated body in a coating and curing mode, the head prefabricated body comprises a metal lining, a carbon fiber preformed body is formed on the periphery of the metal lining in a curing mode, and the carbon fiber preformed body and the metal lining are connected into a whole.
2. The co-cured carbon fiber composite airfoil of claim 1, wherein: the outer surface of the metal lining is at least provided with a limiting part matched with the carbon fiber preformed body.
3. The co-cured carbon fiber composite airfoil of claim 1, wherein: the airfoil prefabricated part comprises a middle prefabricated part and edge prefabricated parts positioned on the upper side and the lower side of the middle prefabricated part, and the middle prefabricated part is glued with the head prefabricated part.
4. The co-cured carbon fiber composite airfoil of claim 3, wherein: the middle prefabricated body comprises a core body, and the surface of the core body is paved with a conformal carbon fiber prepreg.
5. The preparation method of the co-cured carbon fiber composite material airfoil is characterized by comprising the following steps of: the method comprises the following steps:
step 1: manufacturing a head prefabricated body mould and an integral mould, and finishing the processing of the metal lining; and making the airfoil core, the front and rear edge cores, and the head core with light material;
step 2: positioning the metal lining in a head preform mold, filling carbon fiber prepreg around the metal lining, and curing and molding to obtain a head preform;
and step 3: positioning the head prefabricated body obtained in the step (2) and the airfoil core body in an integral mold, connecting the head prefabricated body and the airfoil core body into a whole in a gluing mode, and integrally coating and laying by using carbon fiber prepreg to prepare an airfoil main body structure;
and 4, step 4: and laying a head core body and a front edge core body and a rear edge core body on the outer side of the head part and the front edge and the rear edge of the main structure of the airfoil surface, using a warp-knitted fabric to carry out skin laying, and carrying out die assembly, glue injection and curing to obtain the complete airfoil surface.
6. The method of making a co-cured carbon fiber composite airfoil of claim 5, wherein: the integral cladding and paving layer comprises the following paving steps: a. b, paving airfoil layers with the same shapes as the upper surface and the lower surface of the airfoil core on the upper surface and the lower surface of the airfoil core, and c, repeating a-b until the paved carbon fiber prepreg reaches the designed thickness.
7. The method of making a co-cured carbon fiber composite airfoil of claim 6, wherein: the whole coating layer and the airfoil layer are paved into 33 layers in total, and precompaction is carried out once every 11 layers.
8. The method of making a co-cured carbon fiber composite airfoil of claim 6, wherein: the angle difference between the carbon fiber prepreg in the step a and the carbon fiber of the carbon fiber prepreg in the step b is +/-45 degrees.
9. The method of making a co-cured carbon fiber composite airfoil of claim 5, wherein: and 3, arranging a head core body around the head prefabricated body of the airfoil main body structure.
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| CN110588897B (en) * | 2019-11-01 | 2021-03-26 | 连云港神鹰复合材料科技有限公司 | Preparation method of integrally-formed carbon fiber bogie swing bolster safety crane |
| CN113830287A (en) * | 2021-10-11 | 2021-12-24 | 贵州贵飞飞机设计研究院有限公司 | Control surface with separated beam body edge strip and web plate surface and manufacturing method thereof |
| CN113910641B (en) * | 2021-10-11 | 2023-06-02 | 成都锐美特新材料科技有限公司 | Carbon fiber composite material product, preparation method thereof and wearable seat |
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