CN111634026A - Hot-pressing die for composite material product for aviation and manufacturing method - Google Patents
Hot-pressing die for composite material product for aviation and manufacturing method Download PDFInfo
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- CN111634026A CN111634026A CN202010522786.9A CN202010522786A CN111634026A CN 111634026 A CN111634026 A CN 111634026A CN 202010522786 A CN202010522786 A CN 202010522786A CN 111634026 A CN111634026 A CN 111634026A
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- plate
- plate frame
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- die
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/30—Mounting, exchanging or centering
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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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
Abstract
The invention relates to a hot-pressing die and a manufacturing method for an aviation composite material product, which solve the problems of long cloth laying time, low production efficiency and high production cost of laying and forming composite material prepreg cloth due to complicated processing, heavy weight, poor die positioning accuracy and complicated process assembly of die parts in the manufacturing process and the production process of the aviation composite material product hot-pressing die. In order to overcome the defects, the invention provides a hot-pressing die for composite material products for aviation and a manufacturing method thereof.
Description
Technical Field
The invention relates to a hot-pressing die and a manufacturing method of an aviation composite material product.
Background
At present, a male die and a female die on a hot-pressing die of a traditional composite material product for aviation are usually manufactured in a mode of integral blanking processing, heat dissipation holes need to be processed except for a profile to be processed, and the composite material product for aviation is complex in processing, high in cost, heavy in die weight and poor in positioning accuracy. In the process of manufacturing products, the composite material prepreg cloth is usually used for layering and forming, the cloth laying time is long, the production efficiency is low, and the production cost is high. Therefore, how to design a hot-pressing die with light weight and low cost on the premise of improving the production efficiency of products, ensuring the strength of the die and improving the positioning accuracy requirement of the male die and the female die of the die is a difficult problem to be solved urgently in the manufacturing process of the hot-pressing die of the composite material product for aviation.
Disclosure of Invention
The invention aims to solve the technical problems that in the process of manufacturing a hot-pressing die of an aviation composite material product and producing the aviation product, the die parts are complex to process, heavy in weight, poor in die positioning accuracy, complex in process assembly and complex in installation, the composite material prepreg cloth is used for laying and forming, the laying time is long, the production efficiency is low, and the production cost is high. In order to overcome the defects, the invention relates to a hot-pressing die for composite material products for aviation, which mainly comprises a female die template, a female die plate frame, a female die base plate, a stroke limiting block, a guide pillar, a joint assembly, a male die plate frame, a male die base plate, a self-lubricating wear-resisting plate, a guide sleeve, a heat-insulating system, a vacuum auxiliary RTM system, an oil filtering system, a heating system, a cooling system and the like, laminating a product piece with the same thickness on the female die template in a form of carbon fiber composite dry cloth and an adhesive film, the male die frame structure and the female die frame structure are accurately positioned and pressed through mechanisms such as a guide pillar, a guide sleeve, a stroke limiting block, a self-lubricating wear-resisting plate and the like, and then are subjected to heat preservation, vacuum assisted RTM, oil filtration, heating and cooling through a heat preservation system, and vacuumizing the product, and curing and forming the product into an integral product structure once after pressure and temperature are adjusted. Compared with the traditional method for forming the prepreg cloth by using the carbon fiber composite material, the product piece is laminated by adopting the form of dry cloth and glue film of the carbon fiber composite material, the production efficiency is greatly improved, and the positioning form mainly comprising the guide pillar, the guide sleeve, the stroke limiting block and the self-lubricating wear-resisting plate can realize the accurate positioning between the female die frame structure and the male die frame structure. The female die frame and the male die frame structure formed by combining the plate frames are adopted, so that the processing and manufacturing cost and the die weight are reduced. Compared with the traditional composite material product hot-pressing mold for aviation, the composite material product hot-pressing mold has the advantages of capability of realizing accurate positioning of the mold, high production efficiency of the product, low manufacturing cost and light weight of the mold.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the utility model provides a combined material product hot pressing mold for aviation, by die template (1), die template frame (2), die base (3), stroke stopper (4), guide pillar (5), joint Assembly (6), die template (7), die template grillage (8), punch base (9), self-lubricating antifriction plate (10), guide pin bushing (11), heat preservation system (12), vacuum auxiliary RTM system (13), oil filtration system (14), heating system (15), cooling system (16), die frame structure (17), punch frame structure (18) are constituteed, its characterized in that: the female die frame structure (17) is mainly formed by welding and rigidly connecting female die plates (1), female die plate frames (2), a female die base (3), a stroke limiting block (4), a guide pillar (5) and a joint assembly (6) mutually; the male die frame structure (18) is mainly formed by welding and rigidly connecting a connector assembly (6), a male die plate (7), a male die plate frame (8), a male die base (9), a self-lubricating wear-resisting plate (10) and a guide sleeve (11); the guide post (5) is connected with the guide sleeve (11) in a clearance fit manner, and the guide post (5) is rigidly connected with the female die base (3) by a positioning pin and a screw; the pattern template frame (8) and the self-lubricating wear-resisting plate (10) are rigidly connected by adopting a positioning pin and a screw; the female die base (3) is provided with a rectangular notch and a threaded hole, the notch is communicated with the latticed female die plate frame (2), and the notch is rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded hole by adopting screws; the male die base (9) is provided with a notch and a threaded hole, the notch is communicated with the latticed male die plate frame (8), and the notch is rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded hole by adopting screws;
the method comprises the following steps that a carbon fiber composite material product piece with the same thickness is laminated on a female die template (1) in a form of carbon fiber composite material dry cloth and glue film, the male die and female die frame structures are accurately positioned and pressed through mechanisms such as a guide pillar (5), a guide sleeve (11), a stroke limiting block (4) and a self-lubricating wear plate (10), and then the product is vacuumized through a heat insulation system (12), a vacuum assisted RTM (resin transfer molding) system (13), an oil filtering system (14), a heating system (15) and a cooling system (16), and is subjected to pressure and temperature control and primary hot-pressing curing molding to form an integral product structure;
the female die template (1) is integrally formed by hot curing of a carbon fiber composite material with a molding surface consistent with a carbon fiber composite material product part process digital model, and consists of a female die front convex block (1-1), a female die convex arc (1-2), a female die rear convex block (1-3), a female die middle convex block (1-4), a female die lower bottom plate (1-5), a female die concave arc (1-6), a female die upper boss (1-7) and a female die upper top plate (1-8);
the female die plate frame (2) is made of common steel and comprises 2 female die plate frame peripheral transverse plates (2-1), 2 female die plate frame peripheral longitudinal plates (2-2), 3 female die plate frame internal partition longitudinal plates (2-3), 3 female die plate frame internal partition transverse plates I (2-4) and 4 female die plate frame internal partition transverse plates II (2-5), the female die plate frame peripheral transverse plates (2-1) and the female die plate frame peripheral longitudinal plates (2-2) are rigidly connected with each other by welding, the 3 female die plate frame internal partition longitudinal plates (2-3), the 3 female die plate frame internal partition longitudinal plates I (2-4) and the 4 female die plate frame internal partition longitudinal plates II (2-5) are respectively staggered into a grid structure with equal interval distance through slots (2-8), and the grid interval size is 200-300 mm, the number of grids is determined by the size of carbon fiber composite product parts, 3 female die plate frame inner partition longitudinal plates (2-3) are rigidly connected with clamping grooves (2-7) of 2 female die plate frame peripheral transverse plates by adopting buckles (2-6), 3 female die plate frame inner partition transverse plates (2-4) and 4 female die plate frame inner partition transverse plates (2-5) are rigidly connected with the clamping grooves (2-7) of 2 female die plate frame peripheral longitudinal plates respectively by adopting buckles (2-6) and clamping grooves (2-7), the female die plate frame inner partition transverse plates (2-4) are arranged at the lower parts of female die rear convex blocks (1-3), and the female die plate frame inner partition transverse plates (2-5) are arranged at the lower parts of female die front convex blocks (1-1); the peripheral transverse plate (2-1) of the female die plate frame consists of 6 clamping grooves (2-7), a peripheral transverse plate matrix (2-9) of the female die plate frame and 2 peripheral transverse plate holes (2-10) of the female die plate frame; the peripheral longitudinal plate (2-2) of the female die type plate frame consists of 14 clamping grooves (2-7) and a peripheral longitudinal plate base body (2-11) of the female die type plate frame; the female die type plate frame inner longitudinal partition plate (2-3) consists of 2 groups of buckles (2-6), 7 slots (2-8), female die type plate frame inner longitudinal partition plate concave surfaces (2-12), 8 female die type plate frame inner longitudinal partition plate rectangular notches (2-13) and a female die type plate frame inner longitudinal partition plate base body (2-14), wherein 2 groups of buckles (2-6) are arranged at two ends of the female die type plate frame inner longitudinal partition plate (2-3), and the female die type plate frame inner longitudinal partition plate concave surfaces (2-12) are consistent with a carbon fiber composite material product part process digital model; the first partition transverse plate (2-4) in the female die plate frame consists of 2 groups of buckles (2-6), 3 slots (2-8), 2C-shaped notches (2-15) in the female die plate frame, 2 rectangular notches (2-16) in the female die plate frame, a first concave surface (2-18) in the female die plate frame and a first matrix (2-18) in the female die plate frame, the first partition transverse plate (2-4) in the female die plate frame is provided with 2 groups of buckles (2-6), and the first concave surface (2-18) in the female die plate frame is consistent with a carbon fiber composite product part process digital model; the second partition transverse plate (2-5) in the female die plate frame consists of 2 groups of buckles (2-6), 3 slots (2-8), a second matrix (2-19) of the second partition transverse plate in the female die plate frame, a second female mold surface (2-20) of the second partition transverse plate in the female die plate frame and 4 second rectangular notches (2-21) of the second partition transverse plate in the female die plate frame, wherein 2 groups of buckles (2-6) are arranged at two ends of the second partition transverse plate (2-5) in the female die plate frame, and the second female mold surface (2-20) of the second partition transverse plate in the female die plate frame is consistent with a carbon fiber composite product part process digital-analog;
the female die base (3) consists of 2 guide post transverse plates (3-1), 2 guide post longitudinal plates (3-2), a female die base transverse plate (3-3), a female die adjusting support (3-4), a female die base plate (3-5), a female die base longitudinal plate (3-6), guide post transverse plate rib plates (3-7) and guide post transverse plates (3-8), wherein a welding rigid connection mode is adopted, the guide post transverse plate (3-1) is provided with 2 through holes and threaded holes which are rigidly connected with the guide posts (5) by positioning pins and screws, the guide post longitudinal plates (3-2) adopt a groove structure, the female die base plate (3-5) is provided with rectangular notches which are communicated with the latticed female die plate frame (2), the female die base transverse plates (3-3) and the female die base longitudinal plates (3-6) are arranged at intervals to form latticed welding rigid connection, the transverse plate (3-3) of the female die base and the longitudinal plate (3-6) of the female die base are made of square steel respectively, rectangular notches and threaded holes are designed, the notches are communicated with the latticed female die plate frame (2), and the notches are rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded holes by screws;
the male die plate (7) is made of a steel plate with a molded surface consistent with the process data of a carbon fiber composite product and consists of a male die front concave block (7-1), a male die concave arc (7-2), a male die rear concave block (7-3), a male die middle concave block (7-4), a male die lower base plate (7-5), a male die convex arc (7-6), a male die upper concave table (7-7) and a male die upper top plate (7-8);
the material used by the convex model plate frame (8) is common steel, and consists of 2 convex model plate frame peripheral transverse plates (8-1), 2 convex model plate frame peripheral longitudinal plates (8-2), 3 convex model plate frame internal separation longitudinal plates (8-3), 3 convex model plate frame internal separation transverse plates (8-4) and 4 convex model plate frame internal separation transverse plates (8-5), wherein the convex model plate frame peripheral transverse plates (8-1) and the convex model plate frame peripheral longitudinal plates (8-2) are rigidly connected with each other by welding, the 3 convex model plate frame internal separation longitudinal plates (8-3), the 3 convex model plate frame internal separation longitudinal plates (8-4) and the 4 convex model plate frame internal separation longitudinal plates (8-5) are respectively staggered with each other through slots (8-8) to form a grid structure with the same spacing distance, and the grid spacing size is 200-300 mm, the number of grids is determined by the size of carbon fiber composite product parts, 3 internal parting longitudinal plates (8-3) of the male model plate frame are rigidly connected with the clamping grooves (8-7) of the peripheral transverse plates of the male model plate frame by adopting buckles (8-6), 3 internal parting transverse plates (8-4) of the male model plate frame and 4 internal parting transverse plates (8-5) of the male model plate frame are rigidly connected by adopting buckles (8-6) and the clamping grooves (8-7) of the peripheral longitudinal plates of the male model plate frame respectively, the internal parting transverse plates (8-4) of the male model plate frame are arranged at the upper part of a rear concave block (7-3) of a male die, and the internal parting transverse plates (8-5) of the male model plate frame are arranged at the upper part of a front concave block (7-1) of the male die; the peripheral transverse plate (8-1) of the convex model plate frame consists of 6 clamping grooves (8-7), a peripheral transverse plate base body (8-1) of the convex model plate frame and 4 peripheral transverse plate holes (8-1) of the convex model plate frame; the peripheral longitudinal plate (8-2) of the convex model plate frame consists of 14 clamping grooves (8-7) and a peripheral longitudinal plate base body (8-11) of the convex model plate frame; the inner longitudinal partition plate (8-3) of the convex model plate frame consists of 2 groups of buckles (8-6), 7 slots (8-8), 2 angular notches (8-12) of the inner longitudinal partition plate of the convex model plate frame, 6 rectangular notches (8-13) of the inner longitudinal partition plate of the convex model plate frame, a base body (8-14) of the inner longitudinal partition plate of the convex model plate frame and convex surfaces (8-15) of the inner longitudinal partition plate of the convex model plate frame, wherein two ends of the inner longitudinal partition plate (8-3) of the convex model plate frame are provided with 2 groups of buckles (8-6), and the convex surfaces (8-15) of the inner longitudinal partition plate of the convex model plate frame are consistent with a part process digital-analog model of a carbon fiber composite material product; the first partition transverse plate (8-4) in the convex model plate frame consists of 2 groups of buckles (8-6), 3 slots (8-8), a first convex surface (8-16) of the first partition transverse plate in the convex model plate frame, 2 square notches (8-17) of the first partition transverse plate in the convex model plate frame and 2 rectangular notches (8-18) of the first partition transverse plate in the convex model plate frame, wherein 2 groups of buckles (8-6) are arranged at two ends of the first partition transverse plate (8-4) in the convex model plate frame, and the first convex surface (8-16) of the first partition transverse plate in the convex model plate frame is consistent with a part process digital-analog of a carbon fiber composite product; the second partition transverse plate (8-5) in the convex model plate frame consists of 2 groups of buckles (8-6), 3 slots (8-8), 2 polygonal notches (8-19) in the convex model plate frame, two convex surfaces (8-20) in the convex model plate frame and two rectangular notches (8-21) in the convex model plate frame, wherein the two ends of the second partition transverse plate (8-5) in the convex model plate frame are provided with 2 groups of buckles (8-6), and the two convex surfaces (8-20) in the convex model plate frame are consistent with the part process digital model of the carbon fiber composite material product;
the male die base (9) consists of a guide post transverse plate (9-1), a guide post longitudinal plate (9-2), a male die base transverse plate (9-3), a male die adjusting support (9-4), a male die base longitudinal plate (9-5) and a male die base plate (9-6), wherein welding rigid connection modes are adopted among the guide post transverse plate (9-1), 2 through holes are drilled in the guide post transverse plate (9-1), the guide post longitudinal plate (9-2) adopts a groove type structure, 2 positioning holes and 2 threaded holes are respectively designed in 2 side faces, the self-lubricating wear-resisting plate (10) is rigidly connected with the positioning pins and the screws, 1 positioning hole is designed in the male die base plate (9-6) and is rigidly connected with a guide sleeve (11) in an interference fit mode, and the male die base plate (9-6) is designed with 2 positioning holes and 2 threaded, The stroke limiting block (4) is rigidly connected, a rectangular notch is designed on a male die base plate (9-6) and is communicated with a latticed male die template frame (8), a transverse plate (9-3) of a male die base and a longitudinal plate (9-5) of the male die base are arranged at intervals and are welded in a latticed manner to form rigid connection, the transverse plate (9-3) of the male die base and the longitudinal plate (9-5) of the male die base are respectively made of square steel and are respectively provided with notches and threaded holes, the notches are communicated with the latticed male die template frame (8), and the notches are rigidly connected with a vacuum auxiliary RTM system (13), a heat preservation system (12), a heating system (15) and a cooling system (;
the manufacturing method of the aviation product part assembly on-line measuring device specifically comprises the following process steps:
(1) firstly, opening a male die frame structure (18) in a hot-pressing die, and laminating a carbon fiber composite material dry cloth and an adhesive film on a female die template (1) to form an aviation composite material product with the same thickness;
(2) the male die frame structure (18) and the female die frame structure (17) are accurately positioned and pressed through a guide pillar (5), a guide sleeve (11), a stroke limiting block (4) and a self-lubricating wear plate (10) mechanism;
(3) then, a vacuum auxiliary RTM system (13) is used for vacuumizing the product, after the product is confirmed to have no air leakage phenomenon, the pressure of the product is adjusted, a heating system (15) is used for heating a female die plate frame (2) with a female die frame structure (17) in a latticed manner and a male die plate frame (8) with a male die frame structure (18) in a latticed manner through hot air, the heating is uniform, and after the preset temperature is reached, the heat preservation control is carried out through a heat preservation system (12);
(4) after the preset time for forming the composite material product for aviation is reached, the cooling system (16) and the oil filtering system (14) cool the composite material product for aviation and the die through hydraulic oil, and mainly cool through a female die base (3) of a female die frame structure (17) and a male die base (9) of a male die frame structure (18);
(5) and opening the male die frame structure (18) after the regulation by the pressure regulation and vacuum auxiliary RTM system (13), and taking out the aeronautical composite material product which is subjected to thermosetting molding.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a schematic diagram of the structure of the explosion diagram of the present invention.
Fig. 3 is a schematic perspective view of the female pattern plate (1) of the present invention.
Fig. 4 is a schematic perspective view of the female pattern plate frame (2) of the present invention.
Fig. 5 is a schematic perspective view of the peripheral transverse plate (2-1) of the female die plate frame of the invention.
Fig. 6 is a schematic perspective view of the peripheral vertical plate (2-2) of the female die type plate frame of the present invention.
Fig. 7 is a schematic perspective view of the longitudinal partition (2-3) in the female die type plate frame of the present invention.
Fig. 8 is a schematic perspective view of the first partition transverse plate (2-4) in the female die plate frame.
FIG. 9 is a schematic perspective view of a second partition transverse plate (2-5) in the female die plate frame of the present invention.
Fig. 10 is a schematic front perspective view of the die base (3) of the present invention.
Fig. 11 is a schematic view of the negative perspective structure of the die base (3) of the present invention.
Fig. 12 is a schematic perspective view of the male pattern plate (7) of the present invention.
Fig. 13 is a schematic view of the reverse side of the raised pattern plate frame (8) of the present invention.
Fig. 14 is a schematic perspective view of the peripheral cross plate (8-1) of the raised pattern plate frame of the present invention.
Fig. 15 is a schematic perspective view of the peripheral longitudinal plate (8-2) of the raised pattern plate frame of the present invention.
Fig. 16 is a schematic perspective view of the inner longitudinal partition (8-3) of the raised pattern plate frame of the present invention.
Fig. 17 is a schematic perspective view of the partition transverse plate i (8-4) in the raised pattern plate frame of the present invention.
Fig. 18 is a schematic perspective view of a second partition transverse plate (8-5) in the raised pattern plate frame.
Figure 19 is a schematic front perspective view of the punch base (9) of the present invention.
Figure 20 is a schematic view of the negative perspective of the punch base (9) of the present invention.
The self-lubricating wear-resisting plate comprises a female die template 1, a female die plate frame 2, a female die base plate 3, a stroke limiting block 4, a guide pillar 5, a connector assembly 6, a male die plate 7, a male die plate 8, a male die plate frame 9, a male die base plate 10, a self-lubricating wear-resisting plate 11, a guide sleeve 12, a heat preservation system 13, a vacuum auxiliary RTM system 14, an oil filtering system 14, a heating system 15, a cooling system 16, a female die frame structure 17 and a male die frame structure 18.
Detailed Description
The technical solution is realized by the following technical measures and is further described below:
fig. 1 is a schematic perspective view of the composite material product hot press mold for aviation, and fig. 2 is a schematic structural view of an explosion diagram of the composite material product hot press mold for aviation, which is composed of a female die plate (1), a female die plate frame (2), a female die base (3), a stroke limit block (4), a guide pillar (5), a joint assembly (6), a male die plate (7), a male die plate frame (8), a male die base (9), a self-lubricating wear-resisting plate (10), a guide sleeve (11), a heat insulation system (12), a vacuum auxiliary RTM system (13), an oil filtering system (14), a heating system (15), a cooling system (16), a female die frame structure (17) and a male die frame structure (18), and is characterized in that: the female die frame structure (17) is mainly formed by welding and rigidly connecting female die plates (1), female die plate frames (2), a female die base (3), a stroke limiting block (4), a guide pillar (5) and a joint assembly (6) mutually; the male die frame structure (18) is mainly formed by welding and rigidly connecting a connector assembly (6), a male die plate (7), a male die plate frame (8), a male die base (9), a self-lubricating wear-resisting plate (10) and a guide sleeve (11); the guide post (5) is in clearance fit connection with the guide sleeve (11), and the guide post (5) is in rigid connection with the female die base (3) by a positioning pin and a screw; the convex model plate frame (8) and the self-lubricating wear-resisting plate (10) are rigidly connected by adopting a positioning pin and a screw; the female die base (3) is provided with a rectangular notch and a threaded hole, the notch is communicated with the latticed female die plate frame (2), and the notch is rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded hole by adopting screws; the male die base (9) is provided with a notch and a threaded hole, the notch is communicated with the latticed male die plate frame (8), and the notch is rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded hole by adopting screws; adopt the form lamination of carbon-fibre composite dry cloth with the glued membrane to become a carbon-fibre composite product spare that thickness is the same on die template (1), pass through guide pillar (5) with terrace die frame structure, guide pin bushing (11), stroke stopper (4), mechanism such as self-lubricating antifriction plate (10) carry out protruding, the accurate location of die frame structure compresses tightly, rethread heat preservation system (12), vacuum auxiliary RTM system (13), oil filtration system (14), heating system (15), cooling system (16), to the product evacuation, pressure, the once hot pressing solidification of temperature control is integral product structure.
FIG. 3 is a schematic diagram of a three-dimensional structure of a female die template (1), wherein the female die template (1) is integrally formed by thermosetting a carbon fiber composite material with a molded surface consistent with a carbon fiber composite material product part process digital-analog, and comprises a female die front convex block (1-1), a female die convex arc (1-2), a female die rear convex block (1-3), a female die middle convex block (1-4), a female die lower bottom plate (1-5), a female die concave arc (1-6), a female die upper boss (1-7) and a female die upper top plate (1-8).
FIG. 4 is a schematic perspective view of a female mold plate frame (2) of the present invention, FIG. 5 is a schematic perspective view of a transverse plate (2-1) at the periphery of the female mold plate frame of the present invention, FIG. 6 is a schematic perspective view of a longitudinal plate (2-2) at the periphery of the female mold plate frame of the present invention, FIG. 7 is a schematic perspective view of a longitudinal plate (2-3) at the inside of the female mold plate frame of the present invention, FIG. 8 is a schematic perspective view of a transverse plate (2-4) at the inside of the female mold plate frame of the present invention, FIG. 9 is a schematic perspective view of a transverse plate (2-5) at the inside of the female mold plate frame of the present invention, the female mold plate frame (2) is made of a common steel material, and the female mold plate frame comprises 2-1 at the periphery of the female mold plate frame, 2-2 longitudinal plates (2-2) at the periphery of the female mold, 3 female die plate frame internal partition transverse plates (2-4) and 4 female die plate frame internal partition transverse plates (2-5), wherein the female die plate frame peripheral transverse plates (2-1) and the female die plate frame peripheral longitudinal plates (2-2) are in rigid connection by welding, the 3 female die plate frame internal partition longitudinal plates (2-3), the 3 female die plate frame internal partition longitudinal plates (2-4) and the 4 female die plate frame internal partition longitudinal plates (2-5) are respectively staggered into a grid structure with the same interval distance through slots (2-8), the grid interval size is 200-300 mm, the grid number is determined by the size of a carbon fiber composite product part, the 3 female die plate frame internal partition longitudinal plates (2-3) are in rigid connection with clamping grooves (2-7) of the 2 female die plate frame peripheral transverse plates by adopting buckles (2-6), the 3 female die type plate frame inner partition transverse plates (2-4) and the 4 female die type plate frame inner partition transverse plates (2-5) are respectively rigidly connected by a buckle (2-6) and a clamping groove (2-7) of a peripheral longitudinal plate of the 2 female die type plate frames, the female die type plate frame inner partition transverse plates (2-4) are arranged at the lower part of a female die rear convex block (1-3), and the female die type plate frame inner partition transverse plates (2-5) are arranged at the lower part of a female die front convex block (1-1); the peripheral transverse plate (2-1) of the female die plate frame consists of 6 clamping grooves (2-7), a peripheral transverse plate matrix (2-9) of the female die plate frame and 2 peripheral transverse plate holes (2-10) of the female die plate frame; the peripheral longitudinal plate (2-2) of the female die type plate frame consists of 14 clamping grooves (2-7) and a peripheral longitudinal plate base body (2-11) of the female die type plate frame; the female die type plate frame inner longitudinal partition plate (2-3) consists of 2 groups of buckles (2-6), 7 slots (2-8), female die type plate frame inner longitudinal partition plate concave surfaces (2-12), 8 female die type plate frame inner longitudinal partition plate rectangular notches (2-13) and a female die type plate frame inner longitudinal partition plate base body (2-14), wherein 2 groups of buckles (2-6) are arranged at two ends of the female die type plate frame inner longitudinal partition plate (2-3), and the female die type plate frame inner longitudinal partition plate concave surfaces (2-12) are consistent with a carbon fiber composite material product part process digital model; the first partition transverse plate (2-4) in the female die plate frame consists of 2 groups of buckles (2-6), 3 slots (2-8), 2C-shaped notches (2-15) in the female die plate frame, 2 rectangular notches (2-16) in the female die plate frame, a first concave surface (2-18) in the female die plate frame and a first matrix (2-18) in the female die plate frame, the first partition transverse plate (2-4) in the female die plate frame is provided with 2 groups of buckles (2-6), and the first concave surface (2-18) in the female die plate frame is consistent with a carbon fiber composite product part process digital model; the second partition transverse plate (2-5) in the female die plate frame is composed of 2 groups of buckles (2-6), 3 slots (2-8), a second matrix (2-19) of the second partition transverse plate in the female die plate frame, a second female mold surface (2-20) of the second partition transverse plate in the female die plate frame and 4 rectangular notches (2-21) of the second partition transverse plate in the female die plate frame, 2 groups of buckles (2-6) are arranged at two ends of the second partition transverse plate (2-5) in the female die plate frame, and the second female mold surface (2-20) in the female die plate frame is consistent with a carbon fiber composite product part process digital model.
FIG. 10 is a schematic view of the front side three-dimensional structure of the female die base (3) of the present invention, FIG. 11 is a schematic view of the back side three-dimensional structure of the female die base (3) of the present invention, the female die base (3) is composed of 2 guide post transverse plates (3-1), 2 guide post longitudinal plates (3-2), a female die base transverse plate (3-3), a female die adjusting support (3-4), a female die base plate (3-5), a female die base longitudinal plate (3-6), a guide post transverse plate rib plate (3-7), and a guide post transverse plate (3-8), which are rigidly connected by welding, the guide post transverse plate (3-1) is designed with 2 through holes and threaded holes, and is rigidly connected with the guide posts (5) by positioning pins and screws, the guide post longitudinal plate (3-2) is designed with a groove structure, the female die base plate (3-5) is designed with, the transverse plate (3-3) of the female die base and the longitudinal plate (3-6) of the female die base are arranged at intervals in a latticed manner and welded into rigid connection, the transverse plate (3-3) of the female die base and the longitudinal plate (3-6) of the female die base are respectively made of square steel, rectangular notches and threaded holes are designed, the notches are communicated with the latticed female die plate frame (2), and the notches are in rigid connection with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded holes by screws.
FIG. 12 is a schematic perspective view of a convex mold plate (7) according to the present invention, wherein the convex mold plate (7) is made of a steel plate having a profile consistent with process data of a carbon fiber composite product, and comprises a convex mold front concave block (7-1), a convex mold concave arc (7-2), a convex mold rear concave block (7-3), a convex mold middle concave block (7-4), a convex mold lower base plate (7-5), a convex mold convex arc (7-6), a convex mold upper concave table (7-7), and a convex mold upper top plate (7-8).
Fig. 13 is a schematic view of the reverse side of a convex model plate frame (8) of the present invention, fig. 14 is a schematic view of the three-dimensional structure of a lateral plate (8-1) at the periphery of the convex model plate frame of the present invention, fig. 15 is a schematic view of the three-dimensional structure of a longitudinal plate (8-2) at the periphery of the convex model plate frame of the present invention, fig. 16 is a schematic view of the three-dimensional structure of a longitudinal plate (8-3) at the inside of the convex model plate frame of the present invention, fig. 17 is a schematic view of the three-dimensional structure of a lateral plate (8-4) at the inside of the convex model plate frame of the present invention, fig. 18 is a schematic view of the three-dimensional structure of a lateral plate (8-5) at the inside of the convex model plate frame of the present invention, the convex model plate frame (8) is made of a common steel material, and is composed of 2 lateral plates (8-, 3 first partition transverse plates (8-4) in the model plate frame and 4 second partition transverse plates (8-5) in the model plate frame, the peripheral transverse plates (8-1) of the model plate frame and the peripheral longitudinal plates (8-2) of the model plate frame are rigidly connected by welding, 3 first partition longitudinal plates (8-3) in the model plate frame, 3 first partition longitudinal plates (8-4) in the model plate frame and 4 second partition longitudinal plates (8-5) in the model plate frame are respectively staggered into a grid structure with the same interval distance through slots (8-8), the grid interval size is 200-300 mm, the grid number is determined by the size of a carbon fiber composite product part, 3 first partition longitudinal plates (8-3) in the model plate frame are rigidly connected with 2 clamp grooves (8-7) in the peripheral transverse plates of the model plate frame by fasteners (8-6), the first partition transverse plates (8-4) in the 3 convex model plate racks and the second partition transverse plates (8-5) in the 4 convex model plate racks are respectively and rigidly connected by a buckle (8-6) and a clamping groove (8-7) of the peripheral longitudinal plate of the 2 convex model plate racks, the first partition transverse plates (8-4) in the convex model plate racks are arranged at the upper parts of the rear concave blocks (7-3) of the convex dies, and the second partition transverse plates (8-5) in the convex model plate racks are arranged at the upper parts of the front concave blocks (7-1) of the convex dies; the peripheral transverse plate (8-1) of the convex model plate frame consists of 6 clamping grooves (8-7), a peripheral transverse plate base body (8-1) of the convex model plate frame and 4 peripheral transverse plate holes (8-1) of the convex model plate frame; the peripheral longitudinal plate (8-2) of the convex model plate frame consists of 14 clamping grooves (8-7) and a peripheral longitudinal plate base body (8-11) of the convex model plate frame; the inner longitudinal partition plate (8-3) of the convex model plate frame consists of 2 groups of buckles (8-6), 7 slots (8-8), 2 angular notches (8-12) of the inner longitudinal partition plate of the convex model plate frame, 6 rectangular notches (8-13) of the inner longitudinal partition plate of the convex model plate frame, a base body (8-14) of the inner longitudinal partition plate of the convex model plate frame and convex surfaces (8-15) of the inner longitudinal partition plate of the convex model plate frame, wherein two ends of the inner longitudinal partition plate (8-3) of the convex model plate frame are provided with 2 groups of buckles (8-6), and the convex surfaces (8-15) of the inner longitudinal partition plate of the convex model plate frame are consistent with a part process digital-analog model of a carbon fiber composite material product; the first partition transverse plate (8-4) in the convex model plate frame consists of 2 groups of buckles (8-6), 3 slots (8-8), a first convex surface (8-16) of the first partition transverse plate in the convex model plate frame, 2 square notches (8-17) of the first partition transverse plate in the convex model plate frame and 2 rectangular notches (8-18) of the first partition transverse plate in the convex model plate frame, wherein 2 groups of buckles (8-6) are arranged at two ends of the first partition transverse plate (8-4) in the convex model plate frame, and the first convex surface (8-16) of the first partition transverse plate in the convex model plate frame is consistent with a part process digital-analog of a carbon fiber composite product; the second partition transverse plate (8-5) in the convex model plate frame consists of 2 groups of buckles (8-6), 3 slots (8-8), 2 polygonal notches (8-19) in the convex model plate frame, two convex surfaces (8-20) in the convex model plate frame and two rectangular notches (8-21) in the partition transverse plate in the convex model plate frame, wherein 2 groups of buckles (8-6) are arranged at two ends of the second partition transverse plate (8-5) in the convex model plate frame, and the two convex surfaces (8-20) in the convex model plate frame are consistent with the carbon fiber composite product part process digital-analog.
FIG. 19 is a schematic view of a front side three-dimensional structure of a male die base (9) of the invention, FIG. 20 is a schematic view of a reverse side three-dimensional structure of the male die base (9) of the invention, the male die base (9) is composed of a guide post transverse plate (9-1), a guide post longitudinal plate (9-2), a male die base transverse plate (9-3), a male die adjusting support (9-4), a male die base longitudinal plate (9-5) and a male die base plate (9-6), which are mutually welded and rigidly connected, the guide post transverse plate (9-1) is drilled with 2 through holes, the guide post longitudinal plate (9-2) adopts a groove-shaped structure, 2 side surfaces are respectively provided with 2 positioning holes and 2 threaded holes, the self-lubricating wear-resisting plate (10) is rigidly connected by positioning pins and screws, 1 positioning hole is designed on the male die base plate (9, the male die base plate (9-6) is provided with 2 positioning holes and 2 threaded holes which are rigidly connected with the connector assembly (6) and the stroke limiting block (4) by positioning pins and screws, the male die base plate (9-6) is provided with rectangular notches which are communicated with the latticed male die plate frame (8), the transverse plate (9-3) of the male die base and the longitudinal plate (9-5) of the male die base are arranged at intervals to be welded in a latticed manner to form rigid connection, the transverse plate (9-3) of the male die base and the longitudinal plate (9-5) of the male die base are respectively made of square steel, and are provided with notches and threaded holes, the notches are communicated with the latticed male die plate frame (8), and are rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (.
The manufacturing method of the aviation product part assembly on-line measuring device specifically comprises the following process steps:
(1) firstly, opening a male die frame structure (18) in a hot-pressing die, and laminating a carbon fiber composite material dry cloth and an adhesive film on a female die template (1) to form an aviation composite material product with the same thickness;
(2) the male die frame structure (18) and the female die frame structure (17) are accurately positioned and pressed through a guide pillar (5), a guide sleeve (11), a stroke limiting block (4) and a self-lubricating wear plate (10) mechanism;
(3) then, a vacuum auxiliary RTM system (13) is used for vacuumizing the product, after the product is confirmed to have no air leakage phenomenon, the pressure of the product is adjusted, a heating system (15) is used for heating a female die plate frame (2) with a female die frame structure (17) in a latticed manner and a male die plate frame (8) with a male die frame structure (18) in a latticed manner through hot air, the heating is uniform, and after the preset temperature is reached, the heat preservation control is carried out through a heat preservation system (12);
(4) after the preset time for forming the composite material product for aviation is reached, the cooling system (16) and the oil filtering system (14) cool the composite material product for aviation and the die through hydraulic oil, and mainly cool through a female die base (3) of a female die frame structure (17) and a male die base (9) of a male die frame structure (18);
(5) and opening the male die frame structure (18) after the regulation by the pressure regulation and vacuum auxiliary RTM system (13), and taking out the aeronautical composite material product which is subjected to thermosetting molding.
Claims (8)
1. The utility model provides a combined material product hot pressing mold for aviation, by die template (1), die template frame (2), die base (3), stroke stopper (4), guide pillar (5), joint Assembly (6), protruding model template (7), protruding model grillage (8), terrace die base (9), self-lubricating antifriction plate (10), guide pin bushing (11), heat preservation system (12), vacuum auxiliary RTM system (13), oil filtration system (14), heating system (15), cooling system (16) are constituteed, its characterized in that: the female die frame structure (17) is mainly formed by welding and rigidly connecting female die plates (1), female die plate frames (2), a female die base (3), a stroke limiting block (4), a guide pillar (5) and a joint assembly (6) mutually; the male die frame structure (18) is mainly formed by welding and rigidly connecting a connector assembly (6), a male die plate (7), a male die plate frame (8), a male die base (9), a self-lubricating wear-resisting plate (10) and a guide sleeve (11); the guide post (5) is connected with the guide sleeve (11) in a clearance fit manner, and the guide post (5) is rigidly connected with the female die base (3) by a positioning pin and a screw; the pattern template frame (8) and the self-lubricating wear-resisting plate (10) are rigidly connected by adopting a positioning pin and a screw; the female die base (3) is provided with a rectangular notch and a threaded hole, the notch is communicated with the latticed female die plate frame (2), and the notch is rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded hole by adopting screws; the male die base (9) is provided with a notch and a threaded hole, the notch is communicated with the latticed male die plate frame (8), and the notch is rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16) through the threaded hole by adopting screws; adopt the form lamination of carbon-fibre composite dry cloth with the glued membrane to become a carbon-fibre composite product spare that thickness is the same on die template (1), pass through guide pillar (5) with terrace die frame structure, guide pin bushing (11), stroke stopper (4), mechanism such as self-lubricating antifriction plate (10) carry out protruding, the accurate location of die frame structure compresses tightly, rethread heat preservation system (12), vacuum auxiliary RTM system (13), oil filtration system (14), heating system (15), cooling system (16), to the product evacuation, pressure, the once hot pressing solidification of temperature control is integral product structure.
2. The composite product hot-pressing mold for aviation as claimed in claim 1, wherein: the die template (1) is integrally formed by thermal curing of a carbon fiber composite material with a molded surface consistent with a carbon fiber composite material product part process digital model, and comprises a die front convex block (1-1), a die convex arc (1-2), a die rear convex block (1-3), a die middle convex block (1-4), a die lower bottom plate (1-5), a die concave arc (1-6), a die upper boss (1-7) and a die upper top plate (1-8).
3. The composite product hot-pressing mold for aviation as claimed in claim 1, wherein: the female die plate frame (2) is made of common steel and comprises 2 female die plate frame peripheral transverse plates (2-1), 2 female die plate frame peripheral longitudinal plates (2-2), 3 female die plate frame internal partition longitudinal plates (2-3), 3 female die plate frame internal partition transverse plates (2-4) and 4 female die plate frame internal partition transverse plates (2-5), the female die plate frame peripheral transverse plates (2-1) and the female die plate frame peripheral longitudinal plates (2-2) are rigidly connected with each other by welding, the 3 female die plate frame internal partition longitudinal plates (2-3), the 3 female die plate frame internal partition longitudinal plates (2-4) and the 4 female die plate frame internal partition longitudinal plates (2-5) are respectively staggered with each other through slots (2-8) to form a grid structure with the same interval distance, and the grid interval size is 200-300 mm, the number of grids is determined by the size of carbon fiber composite product parts, 3 female die plate frame inner partition longitudinal plates (2-3) are rigidly connected with clamping grooves (2-7) of 2 female die plate frame peripheral transverse plates by adopting buckles (2-6), 3 female die plate frame inner partition transverse plates (2-4) and 4 female die plate frame inner partition transverse plates (2-5) are rigidly connected with the clamping grooves (2-7) of 2 female die plate frame peripheral longitudinal plates respectively by adopting buckles (2-6) and clamping grooves (2-7), the female die plate frame inner partition transverse plates (2-4) are arranged at the lower parts of female die rear convex blocks (1-3), and the female die plate frame inner partition transverse plates (2-5) are arranged at the lower parts of female die front convex blocks (1-1); the peripheral transverse plate (2-1) of the female die plate frame consists of 6 clamping grooves (2-7), a peripheral transverse plate matrix (2-9) of the female die plate frame and 2 peripheral transverse plate holes (2-10) of the female die plate frame; the peripheral longitudinal plate (2-2) of the female die type plate frame consists of 14 clamping grooves (2-7) and a peripheral longitudinal plate base body (2-11) of the female die type plate frame; the female die type plate frame inner longitudinal partition plate (2-3) consists of 2 groups of buckles (2-6), 7 slots (2-8), female die type plate frame inner longitudinal partition plate concave surfaces (2-12), 8 female die type plate frame inner longitudinal partition plate rectangular notches (2-13) and a female die type plate frame inner longitudinal partition plate base body (2-14), wherein 2 groups of buckles (2-6) are arranged at two ends of the female die type plate frame inner longitudinal partition plate (2-3), and the female die type plate frame inner longitudinal partition plate concave surfaces (2-12) are consistent with a carbon fiber composite material product part process digital model; the first partition transverse plate (2-4) in the female die plate frame consists of 2 groups of buckles (2-6), 3 slots (2-8), 2C-shaped notches (2-15) in the female die plate frame, 2 rectangular notches (2-16) in the female die plate frame, a first concave surface (2-18) in the female die plate frame and a first matrix (2-18) in the female die plate frame, the first partition transverse plate (2-4) in the female die plate frame is provided with 2 groups of buckles (2-6), and the first concave surface (2-18) in the female die plate frame is consistent with a carbon fiber composite product part process digital model; the second partition transverse plate (2-5) in the female die plate frame is composed of 2 groups of buckles (2-6), 3 slots (2-8), a second matrix (2-19) of the second partition transverse plate in the female die plate frame, a second female mold surface (2-20) of the second partition transverse plate in the female die plate frame and 4 rectangular notches (2-21) of the second partition transverse plate in the female die plate frame, 2 groups of buckles (2-6) are arranged at two ends of the second partition transverse plate (2-5) in the female die plate frame, and the second female mold surface (2-20) in the female die plate frame is consistent with a carbon fiber composite product part process digital model.
4. The composite product hot-pressing mold for aviation as claimed in claim 1, wherein: the female die base (3) consists of 2 guide post transverse plates (3-1), 2 guide post longitudinal plates (3-2), a female die base transverse plate (3-3), a female die adjusting support (3-4), a female die base plate (3-5), a female die base longitudinal plate (3-6), guide post transverse plate rib plates (3-7) and guide post transverse plates (3-8), wherein a welding rigid connection mode is adopted, 2 through holes and threaded holes are designed on the guide post transverse plate (3-1) and are rigidly connected with guide posts (5) through positioning pins and screws, the guide post longitudinal plate (3-2) adopts a groove structure, a rectangular groove opening is designed on the female die base plate (3-5) and is communicated with the latticed female die plate frame (2), the female die base transverse plate (3-3) and the female die base longitudinal plates (3-6) are arranged at intervals to form latticed welding rigid connection, the transverse plate (3-3) of the female die base and the longitudinal plate (3-6) of the female die base are made of square steel respectively and are provided with rectangular notches and threaded holes, the notches are communicated with the latticed female die plate frame (2), and the notches are in rigid connection with the vacuum auxiliary RTM system (13), the heat insulation system (12), the heating system (15) and the cooling system (16) through the threaded holes by screws.
5. The composite product hot-pressing mold for aviation as claimed in claim 1, wherein: the convex die plate (7) is made of a steel plate with a molded surface consistent with the process data of a carbon fiber composite product and is composed of a convex die front concave block (7-1), a convex die concave arc (7-2), a convex die rear concave block (7-3), a convex die middle concave block (7-4), a convex die lower base plate (7-5), a convex die arc (7-6), a convex die upper concave table (7-7) and a convex die upper top plate (7-8).
6. The composite product hot-pressing mold for aviation as claimed in claim 1, wherein: the material used by the convex model plate frame (8) is common steel, and consists of 2 convex model plate frame peripheral transverse plates (8-1), 2 convex model plate frame peripheral longitudinal plates (8-2), 3 convex model plate frame inner partition longitudinal plates (8-3), 3 convex model plate frame inner partition transverse plates (8-4) and 4 convex model plate frame inner partition transverse plates (8-5), wherein the convex model plate frame peripheral transverse plates (8-1) and the convex model plate frame peripheral longitudinal plates (8-2) are rigidly connected with each other by welding, the 3 convex model plate frame inner partition longitudinal plates (8-3), the 3 convex model plate frame inner partition longitudinal plates (8-4) and the 4 convex model plate frame inner partition longitudinal plates (8-5) are respectively staggered with each other through slots (8-8) to form a grid structure with the same interval distance, and the grid interval size is 200-300 mm, the number of grids is determined by the size of carbon fiber composite product parts, 3 internal parting longitudinal plates (8-3) of the male model plate frame are rigidly connected with the clamping grooves (8-7) of the peripheral transverse plates of the male model plate frame by adopting buckles (8-6), 3 internal parting transverse plates (8-4) of the male model plate frame and 4 internal parting transverse plates (8-5) of the male model plate frame are rigidly connected by adopting buckles (8-6) and the clamping grooves (8-7) of the peripheral longitudinal plates of the male model plate frame respectively, the internal parting transverse plates (8-4) of the male model plate frame are arranged at the upper part of a rear concave block (7-3) of a male die, and the internal parting transverse plates (8-5) of the male model plate frame are arranged at the upper part of a front concave block (7-1) of the male die; the peripheral transverse plate (8-1) of the convex model plate frame consists of 6 clamping grooves (8-7), a peripheral transverse plate base body (8-1) of the convex model plate frame and 4 peripheral transverse plate holes (8-1) of the convex model plate frame; the peripheral longitudinal plate (8-2) of the convex model plate frame consists of 14 clamping grooves (8-7) and a peripheral longitudinal plate base body (8-11) of the convex model plate frame; the inner longitudinal partition plate (8-3) of the convex model plate frame consists of 2 groups of buckles (8-6), 7 slots (8-8), 2 angular notches (8-12) of the inner longitudinal partition plate of the convex model plate frame, 6 rectangular notches (8-13) of the inner longitudinal partition plate of the convex model plate frame, a base body (8-14) of the inner longitudinal partition plate of the convex model plate frame and convex surfaces (8-15) of the inner longitudinal partition plate of the convex model plate frame, wherein two ends of the inner longitudinal partition plate (8-3) of the convex model plate frame are provided with 2 groups of buckles (8-6), and the convex surfaces (8-15) of the inner longitudinal partition plate of the convex model plate frame are consistent with a part process digital-analog model of a carbon fiber composite material product; the first partition transverse plate (8-4) in the convex model plate frame consists of 2 groups of buckles (8-6), 3 slots (8-8), a first convex surface (8-16) of the first partition transverse plate in the convex model plate frame, 2 square notches (8-17) of the first partition transverse plate in the convex model plate frame and 2 rectangular notches (8-18) of the first partition transverse plate in the convex model plate frame, wherein 2 groups of buckles (8-6) are arranged at two ends of the first partition transverse plate (8-4) in the convex model plate frame, and the first convex surface (8-16) of the first partition transverse plate in the convex model plate frame is consistent with a part process digital-analog of a carbon fiber composite product; the second partition transverse plate (8-5) in the convex model plate frame consists of 2 groups of buckles (8-6), 3 slots (8-8), 2 polygonal notches (8-19) in the convex model plate frame, two convex surfaces (8-20) in the convex model plate frame and two rectangular notches (8-21) in the partition transverse plate in the convex model plate frame, wherein 2 groups of buckles (8-6) are arranged at two ends of the second partition transverse plate (8-5) in the convex model plate frame, and the two convex surfaces (8-20) in the convex model plate frame are consistent with the carbon fiber composite product part process digital-analog.
7. The composite product hot-pressing mold for aviation as claimed in claim 1, wherein: the male die base (9) is composed of a guide post transverse plate (9-1), a guide post longitudinal plate (9-2), a male die base transverse plate (9-3), a male die adjusting support (9-4), a male die base longitudinal plate (9-5) and a male die base plate (9-6), wherein a welding rigid connection mode is adopted among the guide post transverse plate, 2 through holes are drilled in the guide post transverse plate (9-1), the guide post longitudinal plate (9-2) is of a groove type structure, 2 positioning holes and 2 threaded holes are respectively designed in 2 side faces, the positioning holes and the threaded holes are rigidly connected with a self-lubricating wear-resisting plate (10) through positioning pins and screws, 1 positioning hole is designed in the male die base plate (9-6) and is rigidly connected with a guide sleeve (11) through interference fit, and the male die base plate (9-6) is designed with 2 positioning holes and, The stroke limiting block (4) is rigidly connected, a rectangular notch is designed on the male die base plate (9-6) and communicated with the latticed male die model plate frame (8), the transverse plate (9-3) of the male die base and the longitudinal plate (9-5) of the male die base are arranged at intervals and welded in a latticed manner to form rigid connection, the transverse plate (9-3) of the male die base and the longitudinal plate (9-5) of the male die base are respectively made of square steel, and are respectively provided with notches and threaded holes, the notches are communicated with the latticed male die model plate frame (8), and are rigidly connected with the vacuum auxiliary RTM system (13), the heat preservation system (12), the heating system (15) and the cooling system (16.
8. The method for manufacturing a composite aeronautical product hot-pressing mold according to claim 1, characterized in that: the manufacturing method of the aviation product part assembly on-line measuring device specifically comprises the following process steps:
(1) firstly, opening a male die frame structure (18) in a hot-pressing die, and laminating a carbon fiber composite material dry cloth and an adhesive film on a female die template (1) to form an aviation composite material product with the same thickness;
(2) the male die frame structure (18) and the female die frame structure (17) are accurately positioned and pressed through a guide pillar (5), a guide sleeve (11), a stroke limiting block (4) and a self-lubricating wear plate (10) mechanism;
(3) then, a vacuum auxiliary RTM system (13) is used for vacuumizing the product, after the product is confirmed to have no air leakage phenomenon, the pressure of the product is adjusted, a heating system (15) is used for heating a female die plate frame (2) with a female die frame structure (17) in a latticed manner and a male die plate frame (8) with a male die frame structure (18) in a latticed manner through hot air, the heating is uniform, and after the preset temperature is reached, the heat preservation control is carried out through a heat preservation system (12);
(4) after the preset time for forming the composite material product for aviation is reached, the cooling system (16) and the oil filtering system (14) cool the composite material product for aviation and the die through hydraulic oil, and mainly cool through a female die base (3) of a female die frame structure (17) and a male die base (9) of a male die frame structure (18);
(5) and opening the male die frame structure (18) after the regulation by the pressure regulation and vacuum auxiliary RTM system (13), and taking out the aeronautical composite material product which is subjected to thermosetting molding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010522786.9A CN111634026A (en) | 2020-06-10 | 2020-06-10 | Hot-pressing die for composite material product for aviation and manufacturing method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010522786.9A CN111634026A (en) | 2020-06-10 | 2020-06-10 | Hot-pressing die for composite material product for aviation and manufacturing method |
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| CN111634026A true CN111634026A (en) | 2020-09-08 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114103169A (en) * | 2021-11-19 | 2022-03-01 | 航天特种材料及工艺技术研究所 | Integral forming process for composite material complex frame |
| CN114654760A (en) * | 2022-03-23 | 2022-06-24 | 南京恒翔保温材料制造有限公司 | Manufacturing method of fireproof density board |
| CN115091786A (en) * | 2022-06-23 | 2022-09-23 | 航天特种材料及工艺技术研究所 | Forming method and forming die for conical-cylinder-shaped fiber reinforced composite material |
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2020
- 2020-06-10 CN CN202010522786.9A patent/CN111634026A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114103169A (en) * | 2021-11-19 | 2022-03-01 | 航天特种材料及工艺技术研究所 | Integral forming process for composite material complex frame |
| CN114103169B (en) * | 2021-11-19 | 2023-04-25 | 航天特种材料及工艺技术研究所 | Integral forming process of complex frame made of composite material |
| CN114654760A (en) * | 2022-03-23 | 2022-06-24 | 南京恒翔保温材料制造有限公司 | Manufacturing method of fireproof density board |
| CN114654760B (en) * | 2022-03-23 | 2023-10-20 | 南京恒翔保温材料制造有限公司 | Manufacturing method of fireproof density board |
| CN115091786A (en) * | 2022-06-23 | 2022-09-23 | 航天特种材料及工艺技术研究所 | Forming method and forming die for conical-cylinder-shaped fiber reinforced composite material |
| CN115091786B (en) * | 2022-06-23 | 2023-04-11 | 航天特种材料及工艺技术研究所 | Forming method and forming die for conical-cylinder-shaped fiber reinforced composite material |
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Inventor after: Wu Kebing Inventor after: Gao Xiang Inventor after: Lu Tianhao Inventor after: Yang Haibo Inventor after: Zhang Desheng Inventor after: Jiang Tao Inventor after: Yang Changbing Inventor before: Wu Kebing Inventor before: Gao Xiang Inventor before: Lu Tianhao Inventor before: Yang Haibo Inventor before: Zhang Desheng |