CN118438580A - Forming die of composite material tail wing and integrated manufacturing method - Google Patents
Forming die of composite material tail wing and integrated manufacturing method Download PDFInfo
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- CN118438580A CN118438580A CN202410594006.XA CN202410594006A CN118438580A CN 118438580 A CN118438580 A CN 118438580A CN 202410594006 A CN202410594006 A CN 202410594006A CN 118438580 A CN118438580 A CN 118438580A
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- 239000002131 composite material Substances 0.000 title claims abstract description 45
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 25
- 239000011162 core material Substances 0.000 claims description 51
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 26
- 239000004917 carbon fiber Substances 0.000 claims description 26
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 26
- 238000000034 method Methods 0.000 claims description 20
- 238000000465 moulding Methods 0.000 claims description 18
- 239000003292 glue Substances 0.000 claims description 13
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 10
- 229910052799 carbon Inorganic materials 0.000 claims description 10
- 239000006261 foam material Substances 0.000 claims description 10
- 239000011347 resin Substances 0.000 claims description 9
- 229920005989 resin Polymers 0.000 claims description 9
- 239000002313 adhesive film Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 239000004744 fabric Substances 0.000 claims description 5
- 239000003365 glass fiber Substances 0.000 claims description 5
- 230000003247 decreasing effect Effects 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- 210000001503 joint Anatomy 0.000 claims 2
- 238000007493 shaping process Methods 0.000 claims 1
- 238000005260 corrosion Methods 0.000 abstract description 4
- 230000007797 corrosion Effects 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 17
- 238000000748 compression moulding Methods 0.000 description 5
- 239000006260 foam Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 238000004381 surface treatment Methods 0.000 description 3
- NBIIXXVUZAFLBC-UHFFFAOYSA-N Phosphoric acid Chemical compound OP(O)(O)=O NBIIXXVUZAFLBC-UHFFFAOYSA-N 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 229910000147 aluminium phosphate Inorganic materials 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
-
- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- 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
- B29L2031/3097—Cosmonautical vehicles; Rockets
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The invention discloses a forming die of a composite material tail wing and an integrated manufacturing method, wherein the forming die of the composite material tail wing comprises a first forming die and a second forming die, the first forming die comprises a first upper die and a first lower die, a plurality of ejection movable blocks are arranged on the first lower die, the upper end of the first lower die is fixedly connected with a plurality of first positioning pins matched with the first upper die, the second forming die comprises a second upper die and a second lower die, a plurality of first grooves are arranged on the second upper die, a second wedge-shaped pressurizing movable block matched with the first grooves is fixedly connected on the second lower die, two second positioning pins matched with the second upper die are fixedly connected on the second lower die, and a product cavity movable block matched with the second wedge-shaped pressurizing movable block is arranged on the second lower die. Compared with the prior art, the forming die and the integrated manufacturing method of the composite material empennage have the advantages of light weight, corrosion resistance and the like, and have long service life.
Description
Technical Field
The invention belongs to the technical field of composite material tail fin forming, and particularly relates to a forming die of a composite material tail fin and an integrated manufacturing method.
Background
The empennage bears aerodynamic load and provides lift force in the missile flight process, at present, most of the empennages are structures of metal frameworks and composite material skins, and most of the empennages are formed in a compression molding mode. In order to densify the tail structure, the gas in the prepreg must be exhausted as much as possible, and parameters such as curing temperature, pressure and time must be controlled so as to obtain the best mechanical properties.
Chinese patent publication No. CN107628232a discloses a "composite material unmanned aerial vehicle tail wing and its manufacturing method", which proposes that the honeycomb sandwich carbon fiber left and right skin, carbon fiber laminated front and rear beams, foam sandwich carbon fiber ribs are manufactured separately, and then the skin, ribs and beams are combined into the unmanned aerial vehicle tail wing structure by using the front and rear reinforcing plates of aluminum alloy and fixing blocks in the glue joint assembly mode of structural glue, screws and rivets. According to the method, a part forming tool is required to be designed and manufactured to produce the skin, the ribs and Liang Lingjian, and then the parts are assembled and combined into a whole through an assembling tool, so that the forming process is complicated, the external dimension of a product is difficult to control, the surface is smooth and not high, the later surface treatment is inconvenient, and the mass production is not facilitated.
The information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person of ordinary skill in the art.
Disclosure of Invention
The invention aims to provide a forming die of a composite material tail wing and an integrated manufacturing method, which can solve the problems in the background art.
In order to achieve the above object, a specific embodiment of the present invention provides the following technical solution:
The utility model provides a forming die of combined material fin, includes first forming die and second forming die, first forming die includes first last mould and first lower mould, offer a plurality of ejecting loose pieces on the first lower mould, the upper end fixedly connected with of first lower mould a plurality of first locating pins with first last mould assorted, the one end fixedly connected with first wedge pressurization loose piece of first lower mould, first last mould and first lower mould are the lid and close, the second forming die includes second last mould and second lower mould, set up a plurality of first recesses on the second last mould, fixedly connected with and first recess assorted second wedge pressurization loose piece on the second lower mould, fixedly connected with two second locating pins with second last mould assorted on the second lower mould, set up the product loose piece with second wedge pressurization loose piece assorted on the second lower mould, set up the gluey groove on the lateral wall of second lower mould, it is with second wedge pressurization loose piece and second lid to go up on the second lower mould.
In order to achieve the above object, a specific embodiment of the present invention provides the following technical solution:
an integrated manufacturing method of a composite tail wing comprises the following steps: s1, bonding a framework and a foam material into a core material by using an adhesive film; s2, placing a non-porous isolating film on the surface of a first forming die, placing a core material into the first forming die, paving carbon twisted strips at the front edge and the rear edge of the framework in a gradient decreasing manner, and pre-compacting by the first forming die to obtain a core die preformed body; s3, paving an adhesive film and a glass fiber fabric prepreg on the surface of the core mold preformed body, putting the core mold preformed body into a first forming mold, heating the first forming mold to 50-70 ℃, pressurizing the first forming mold, keeping the first forming mold at the temperature for 20-40 minutes under the environment, and taking out to obtain a first core mold preformed body; s4, wrapping 20-25 layers of carbon fiber unidirectional prepreg on the first core mold preform, and pre-compacting every 3-5 layers to obtain a second core mold preform; s5, completing die assembly of the second core die preform through the second forming die to obtain a second forming die to be processed; s6, solidifying and molding the second molding die to be processed.
In one or more embodiments of the present invention, the skeleton is formed with a carbon fiber skin layer having a thickness of 2 to 2.5mm and a thickness of 16 to 18mm.
In one or more embodiments of the invention, in said step S2, the width of the lay-on carbon strips is between 15 and 25mm in gradient.
In one or more embodiments of the present invention, in the step S4, the first layer and the last layer of the unidirectional carbon fiber prepreg are subjected to lap joint treatment, and the unidirectional carbon fiber prepregs located between the first layer and the second layer are respectively butt-jointed and laid, and butt-joint positions between the two adjacent layers are staggered.
In one or more embodiments of the present invention, in the step S6, the specific steps of curing and molding are: s6.1, placing the second forming die to be treated into a hot press; s6.2, raising the temperature in the cavity of the second forming die to be treated to 70-90 ℃, starting to pressurize, and exhausting for multiple times in the pressurizing process; s6.2, keeping the temperature of the second forming die to be treated in the environment of 115-135 ℃ for 110-130 minutes.
In one or more embodiments of the present invention, in the step S6.2, the pressurizing pressure is 8 to 10MPa.
In one or more embodiments of the present invention, in the step S6.2, the pressurizing process is performed for not less than 3 times.
In one or more embodiments of the present invention, in the step S5, the specific step of clamping is: s5.1, placing the second core mould preformed body in a second lower mould, and fixing the second core mould preformed body through a second locating pin; s5.2, after the second wedge-shaped pressurizing movable block and the product cavity movable block are installed on the second lower die, the second upper die is combined on the second lower die, and die combination is completed, so that the second forming die to be processed is obtained.
In one or more embodiments of the present invention, in the step S6, the curing process of curing the second molding die to be processed is: the cavity surfaces of the second upper die and the second lower die are pressurized to the upper surface and the lower surface of the second core die preformed body, the second wedge-shaped pressurizing movable block extrudes the die cavity and pressurizes the side edges of the upper side and the lower side of the second core die preformed body, and redundant material edges and gas in the second core die preformed body can flow into glue overflow grooves on the two sides of the second lower die along with resin.
Compared with the prior art, the forming die and the integrated manufacturing method of the composite material empennage have the following advantages:
1) The armature, foam material and carbon lay are first integrated into a mandrel preform. And paving the core mould preformed body, and integrally curing and forming the composite material tail wing by adopting a compression molding process. The carbon fiber prepreg can accurately control the resin content of the product and reduce the porosity of the product. The framework is a main stress area, and the framework and the carbon fiber entity structure are used for wrapping the foam material sandwich, so that the overall weight of the tail wing is reduced, and the overall strength can be increased;
2) The die assembly mode of the forming die is simple, the positioning of the composite material tail fin is convenient, the positioning is accurate, when the forming die is closed, the contact surface of the forming die and the composite material tail fin is pressurized, the second wedge-shaped pressurizing movable block can better pressurize the side edges of the upper side and the lower side of the composite material tail fin through the extrusion product cavity movable block, and during pressurization, redundant material edges and gas in the composite material tail fin can flow into glue overflow grooves on the left side and the right side of the second lower die along with resin;
3) The composite material tail wing prepared by the composite material tail wing integrated manufacturing method has the advantages of light weight, corrosion resistance and the like, and has long service life. The molding process is simple and easy to operate, the overall dimension of the product is accurate and controllable, the surface is smooth and flat, the post surface treatment is easy, and the method is suitable for mass production.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings may be obtained according to the drawings without inventive effort to those skilled in the art.
FIG. 1 is a schematic diagram of a first upper die according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a first lower die according to an embodiment of the invention;
FIG. 3 is a schematic structural view of a tail structure of a composite material according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a second upper die according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a second lower die according to an embodiment of the invention.
The main reference numerals illustrate:
1. A first upper die; 11. a hollow groove; 2. a first lower die; 21. ejecting the loose piece; 22. a first positioning pin; 23. a first wedge-shaped pressurizing movable block; 3. a second upper die; 31. a first groove; 4. a second lower die; 41. a second wedge-shaped pressurizing movable block; 42. product cavity movable blocks; 43. a second positioning pin; 44. a glue overflow groove; 5. a composite tail structure; 51. a skeleton; 52. a foam material; 53. carbon twisting; 54. and positioning holes.
Detailed Description
In order to make the technical solution of the present invention better understood by those skilled in the art, the technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present invention without making any inventive effort, shall fall within the scope of the present invention.
In an embodiment of the invention, a forming mold of a composite tail fin and an integrated manufacturing method thereof are provided, wherein the forming mold of the composite tail fin comprises a first forming mold and a second forming mold, and the first forming mold and the second forming mold are both used for molding a composite tail fin structure 5 by compression molding.
As shown in fig. 1 to 2, the first molding die includes a first upper die 1 and a first lower die 2, and the first upper die 1 and the first lower die 2 are fixed by being covered. A first positioning pin 22 for fixing the core material is arranged on the opposite surface of the first lower die 2 and the first upper die 1, an ejection movable block 21 is arranged on the opposite surface of the first lower die 2 and the first upper die 1, and the ejection movable block 21 is positioned in the middle of the first lower die 2 and is used for ejecting the core material. A first wedge-shaped pressurizing movable block 23 is detachably installed at one side of the first lower die 2, and the core material can be pressurized by the first wedge-shaped pressurizing movable block 23. The first upper die 1 is provided with a hollowed-out groove 11, and the hollowed-out groove 11 is matched with the first wedge-shaped pressurizing movable block 23 in position.
As shown in fig. 4 to 5, the second molding die includes a second upper die 3 and a second lower die 4, and the second upper die 3 and the second lower die 4 are fixed by being covered. The second lower die 4 and the second upper die 3 are provided with second positioning pins 43 for fixing the core material on opposite sides thereof, two second wedge-shaped pressurizing movable blocks 41 and two product cavity movable blocks 42 are arranged on two sides of the second lower die 4, the second wedge-shaped pressurizing movable blocks 41 and the product cavity movable blocks 42 are used for pressurizing the core material, and the second upper die 3 is provided with a first groove 31 matched with the second wedge-shaped pressurizing movable blocks 41. Glue overflow grooves 44 are formed in the other two sides of the second lower die 4, the glue overflow grooves 44 are located between the two product cavity movable blocks 42, and extension lines of the glue overflow grooves 44 are intersected with extension lines of the product cavity movable blocks 42.
Referring to fig. 3, the method for integrally manufacturing the tail structure 5 of the composite material uses carbon fiber unidirectional prepreg, glass fiber fabric prepreg, skeleton 51 and foam 52 as raw materials, and adopts prepreg lapping technology to attach to a core mold formed by the skeleton 51 and the foam 52, and then integrally cures and forms the tail structure by a compression molding process.
As shown in fig. 3, the composite tail structure 5 comprises a carcass 51, four foam materials 52, leading and trailing edge carbon twists 53 and a skin. The skeleton 51 is provided with a plurality of positioning holes 54, and the positioning holes 54 are used for positioning with the forming die.
The carbon fiber unidirectional prepreg has the advantages that the single-layer curing thickness is 0.1mm, the resin content is 33%, the carbon fiber unidirectional prepreg is used as a raw material, the strength and the rigidity in the main bearing direction are provided, the carbon fiber treatment has good corrosion resistance, the aluminum alloy skeleton is wrapped in the carbon fiber skin, the strength of a product is improved, and the service life of the tail wing can be prolonged. The glass fiber fabric prepreg has a single-layer curing thickness of 0.1mm and a resin content of 33%. The armature 51 is specifically machined from 7075-T7351 aluminum alloy with phosphoric acid anodized, which can increase bond strength. The foam material 52 adopts PMI fine-pore foam with the density of 52Kg/m 3, and the foam material 52 has good heat resistance, lower glue absorption amount and easy processing, so that the overall weight of the composite tail structure 5 can be effectively reduced, and the flying speed can be improved.
The integrated manufacturing method of the composite material tail wing comprises the following specific steps:
S1, bonding the framework 51 and the foam material 52 into a core material by using an adhesive film. The skeleton 51 is formed with a carbon fiber skin layer, the thickness of the carbon fiber skin layer is 2-2.5 mm, and the thickness of the skeleton 51 is 16-18 mm.
S2, placing a non-porous isolating film on the surface of the first forming die, placing the core material into the first forming die, paving carbon twisted strips 53 at the front edge and the rear edge of the framework 51 in a gradient decreasing manner, and pre-compacting by the first forming die to obtain a core mold preformed body. Wherein, the width of the carbon twisted strips 53 is 15-25 mm, preferably 20mm, which are paved and pasted gradually according to the gradient.
S3, paving an adhesive film and a glass fiber fabric prepreg on the surface of the core mold preformed body, putting the core mold preformed body into a first forming mold, heating the first forming mold to 50-70 ℃, pressurizing the first forming mold, keeping the first forming mold at the temperature for 20-40 minutes under the environment, and taking out to obtain the first core mold preformed body. The temperature is preferably 55-65 ℃, and the heat preservation time is preferably 25-35 ℃.
And S4, wrapping 20-25 layers of carbon fiber unidirectional prepreg on the first core mold preform, and pre-compacting every 3-5 layers to obtain a second core mold preform. The first layer and the last layer of the carbon fiber unidirectional prepreg are subjected to lap joint treatment, and the carbon fiber unidirectional prepregs positioned between the first layer and the second layer are butted and paved, and the butted positions of the two adjacent layers are staggered.
And S5, completing die assembly of the second core die preform through the second forming die, and obtaining a second forming die to be processed. The specific step of die assembly is that the second core mold preform is placed in the second lower die 4, the second core mold preform is fixed by the second positioning pin 43, the second wedge-shaped pressurizing movable block 41 and the product cavity movable block 42 are mounted on the second lower die 4, and then the second upper die 3 is combined on the second lower die 4, so that die assembly is completed, and the second forming die to be processed is obtained.
S6, solidifying and molding the second molding die to be processed. The concrete steps of curing and forming are as follows: and (3) placing the second forming die to be treated into a hot press, raising the temperature in the cavity of the second forming die to be treated to 70-90 ℃, starting pressurizing, and exhausting for multiple times in the pressurizing process, so that the second forming die to be treated is kept at the temperature of 115-135 ℃ for 110-130 minutes. Wherein the pressurizing pressure is 8-10 MPa, and the air is exhausted for at least 3 times in the pressurizing process. The temperature in the cavity of the second forming die is preferably 85-85 ℃, and the temperature of the second forming die is preferably 120-130 ℃.
In step S6, the curing process of the second molding die to be processed is: the cavity surfaces of the second upper die 3 and the second lower die 4 are pressurized to the upper surface and the lower surface of the second core die preformed body, the second wedge-shaped pressurizing movable block 41 extrudes the die cavity and pressurizes the side edges of the upper side and the lower side of the second core die preformed body, redundant material edges and gas in the second core die preformed body can flow into glue overflow grooves 44 on the two sides of the second lower die 4 along with resin, and after solidification, demolding and deburring are carried out to obtain the composite material tail wing.
The present invention first integrates the armature 51, foam 52 and carbon ribbon 53 into a core preform. And paving the core mould preformed body, and integrally curing and forming the composite material tail wing by adopting a compression molding process. The carbon fiber prepreg can accurately control the resin content of the product and reduce the porosity of the product. The skeleton 51 is the main stress area, and the skeleton 51 and the carbon fiber entity structure sandwich and wrap the foam material 52 therein, so that the overall weight of the tail wing is reduced, and the overall strength can be increased.
In the invention, the die assembly mode of the forming die is simple, the positioning of the composite material tail fin is convenient, the positioning is accurate, when the forming die is closed, the contact surface of the forming die and the composite material tail fin is pressurized, the second wedge-shaped pressurizing movable block 41 can better pressurize the side edges of the upper side and the lower side of the composite material tail fin through the extrusion product cavity movable block 42, and during the pressurizing, redundant material edges and gas in the composite material tail fin can flow into the glue overflow grooves 44 on the left side and the right side of the second lower die 4 along with resin.
The composite material tail wing prepared by the preparation method has the advantages of light weight, corrosion resistance and the like, and has long service life. The molding process is simple and easy to operate, the overall dimension of the product is accurate and controllable, the surface is smooth and flat, the post surface treatment is easy, and the method is suitable for mass production.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (10)
1. A composite tail forming die, comprising:
A first forming die, the first forming die comprising:
A first upper die;
the upper end of the first lower die is fixedly connected with a plurality of first positioning pins matched with the first upper die, and one end of the first lower die is fixedly connected with a first wedge-shaped pressurizing movable block;
The first upper die and the first lower die are covered;
A second molding die, the second molding die comprising:
the second upper die is provided with a plurality of first grooves;
The second lower die is fixedly connected with a second wedge-shaped pressurizing movable block matched with the first groove, two second positioning pins matched with the second upper die are fixedly connected with the second lower die, a product cavity movable block matched with the second wedge-shaped pressurizing movable block is arranged on the second lower die, a glue overflow groove is arranged on the side wall of the second lower die, and a first groove matched with the second wedge-shaped pressurizing movable block is arranged on the second upper die;
the second upper die and the second lower die are covered.
2. An integrated manufacturing method of a composite tail wing is characterized by comprising the following steps:
S1, bonding a framework and a foam material into a core material by using an adhesive film;
S2, placing a non-porous isolating film on the surface of a first forming die, placing a core material into the first forming die, paving carbon twisted strips at the front edge and the rear edge of the framework in a gradient decreasing manner, and pre-compacting by the first forming die to obtain a core die preformed body;
S3, paving an adhesive film and a glass fiber fabric prepreg on the surface of the core mold preformed body, putting the core mold preformed body into a first forming mold, heating the first forming mold to 50-70 ℃, pressurizing the first forming mold, keeping the first forming mold at the temperature for 20-40 minutes under the environment, and taking out to obtain a first core mold preformed body;
S4, wrapping 20-25 layers of carbon fiber unidirectional prepreg on the first core mold preform, and pre-compacting every 3-5 layers to obtain a second core mold preform;
S5, completing die assembly of the second core die preform through the second forming die to obtain a second forming die to be processed;
S6, solidifying and molding the second molding die to be processed.
3. The integrated manufacturing method of the composite tail wing according to claim 2, wherein the framework is formed with a carbon fiber skin layer, the thickness of the carbon fiber skin layer is 2-2.5 mm, and the thickness of the framework is 16-18 mm.
4. An integrated manufacturing method of a composite tail according to claim 2, wherein in step S2, the width of the carbon twist strips is 15-25 mm in gradient decreasing steps.
5. The integrated manufacturing method of the tail wing made of composite materials according to claim 2, wherein in the step S4, the first layer and the last layer of the unidirectional carbon fiber prepreg are subjected to lap joint treatment, the unidirectional carbon fiber prepreg between the first layer and the second layer is in butt joint and paving, and the butt joint positions between the two adjacent layers are staggered.
6. The integrated manufacturing method of the tail fin made of composite material according to claim 2, wherein in the step S6, the concrete steps of curing and molding are as follows:
s6.1, placing the second forming die to be treated into a hot press;
s6.2, raising the temperature in the cavity of the second forming die to be treated to 70-90 ℃, starting to pressurize, and exhausting for multiple times in the pressurizing process;
S6.2, keeping the temperature of the second forming die to be treated in the environment of 115-135 ℃ for 110-130 minutes.
7. The integrated manufacturing method of a composite tail fin according to claim 6, wherein in the step S6.2, the pressurizing pressure is 8 to 10MPa.
8. The method of manufacturing a composite tail fin as claimed in claim 6, wherein in step S6.2, the air is exhausted no less than 3 times during the pressurization.
9. The method for integrally manufacturing a composite tail wing according to claim 2, wherein in step S5, the specific step of clamping is:
S5.1, placing the second core mould preformed body in a second lower mould, and fixing the second core mould preformed body through a second locating pin;
s5.2, after the second wedge-shaped pressurizing movable block and the product cavity movable block are installed on the second lower die, the second upper die is combined on the second lower die, and die combination is completed, so that the second forming die to be processed is obtained.
10. The integrated manufacturing method of a composite tail fin according to claim 2, wherein in the step S6, the curing process of curing and shaping the second molding die to be processed is: the cavity surfaces of the second upper die and the second lower die are pressurized to the upper surface and the lower surface of the second core die preformed body, the second wedge-shaped pressurizing movable block extrudes the die cavity and pressurizes the side edges of the upper side and the lower side of the second core die preformed body, and redundant material edges and gas in the second core die preformed body can flow into glue overflow grooves on the two sides of the second lower die along with resin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410594006.XA CN118438580A (en) | 2024-05-14 | 2024-05-14 | Forming die of composite material tail wing and integrated manufacturing method |
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| CN202410594006.XA CN118438580A (en) | 2024-05-14 | 2024-05-14 | Forming die of composite material tail wing and integrated manufacturing method |
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