CN111674058B - Preparation device and method of carbon fiber three-dimensional woven honeycomb composite material - Google Patents
Preparation device and method of carbon fiber three-dimensional woven honeycomb composite material Download PDFInfo
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- CN111674058B CN111674058B CN202010484057.9A CN202010484057A CN111674058B CN 111674058 B CN111674058 B CN 111674058B CN 202010484057 A CN202010484057 A CN 202010484057A CN 111674058 B CN111674058 B CN 111674058B
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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
- B29C70/40—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
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
Abstract
The invention discloses a preparation device and a preparation method of a carbon fiber three-dimensional woven honeycomb composite material, wherein the preparation device comprises a mould, a first core rod, a second core rod and a resin diversion and vacuumizing device; the mould is provided with fixing holes and demoulding holes, the outermost circle of the mould is completely provided with the fixing holes, a plurality of demoulding holes and fixing holes are arranged in the area surrounded by the fixing holes of the outermost circle, each demoulding hole is correspondingly provided with a second core rod, and each fixing hole is correspondingly provided with a first core rod; the positions and the intervals of the fixed holes and the demoulding holes are set according to the size of the cell of the carbon fiber honeycomb composite material to be formed, after the first core rod and the second core rod are installed, the adjacent surfaces between the first core rod and the second core rod are provided with the honeycomb cell intervals, the honeycomb cell intervals are used for accommodating carbon fiber honeycombs, and the honeycomb cell intervals are used as resin flow channels. The invention provides a forming device and a forming method for a continuous carbon fiber three-dimensional woven honeycomb composite material, and fills the gap in the preparation process of three-dimensional woven carbon fiber honeycombs.
Description
Technical Field
The invention relates to a preparation method of a three-dimensional braided composite material, in particular to a preparation device and a preparation method of a carbon fiber three-dimensional braided honeycomb composite material, and belongs to the field of preparation and forming of composite materials.
Background
The composite material with high size and stability is an important development direction of light and high-precision aviation and spacecraft structures. Zero-expansion and high/ultrahigh-stability spacecraft composite material structures are researched from 90 s in the 20 th century in the United states and Western European countries, and are mainly used for supporting structures, antenna reflecting surfaces, gravity gradiometer bases and the like of space telescopes and other optical instruments. At present, the research projects developed by the european space agency "2015-2025 universe vision project" include solar orbiters, euclidean detectors, plato space telescopes, and the like, and a plurality of optical instruments and detection equipment with very high precision are loaded on the spacecrafts. In order to ensure the working precision of the instruments and equipment, a structural platform with high/ultrahigh stability must be provided for the instruments and equipment, and meanwhile, in order to reduce the structural weight of the detector, the instruments and equipment need to be made of light composite materials.
The honeycomb sandwich plate structure is an important component of a spacecraft structure such as a satellite, and the proportion of the honeycomb sandwich plate structure in a plate structure can be 80-90%. The honeycomb sandwich structure consists of three parts, namely a middle core layer, an upper panel and a lower panel. The upper and lower panels are thin and mainly bear various loads including temperature loads in the plane, and the core layer structure bonded with the upper and lower panels mainly plays a role in supporting and insulating and is responsible for resisting compression, shear loads and deformation resistance. The traditional sandwich structure for the spacecraft is mainly an aluminum panel-aluminum honeycomb and other metal structures; with the continuous improvement of the requirements on light weight and high stability of the spacecraft, the carbon fiber composite material gradually replaces aluminum alloy and titanium alloy to be used as a panel structure of a sandwich structure of the spacecraft due to good conductive property, excellent mechanical property, low thermal expansion coefficient and strong designability. However, at present, due to the obvious difference of thermal expansion coefficients of carbon fiber and aluminum alloy, the carbon fiber panel-aluminum honeycomb structure used by various types of spacecrafts at home and abroad cannot realize ultrahigh stability under temperature alternation, and the problem of thermal deformation still stands out; meanwhile, the carbon fiber and the aluminum alloy have obvious potential difference, so that the corrosion phenomenon is easy to occur. The development of a carbon fiber panel-carbon fiber honeycomb low-expansion and high-stability structure is a key technical problem to be solved urgently for high-precision and light spacecrafts.
Compared with the traditional metal honeycomb or paper honeycomb, the carbon fiber honeycomb relates to the compounding of two materials of fiber and resin, and the manufacturing process is complicated by considering the fiber orientation and the structure. Meanwhile, the prepared honeycomb is a carbon fiber honeycomb formed by bonding layer-to-layer honeycombs by using a stretching method, an assembling method, a die pressing method and the like which are initially researched at present, and a remarkable interface exists; the carbon fiber has poor compression performance and impact performance, and the structure cannot fully exert the performance advantages of the carbon fiber honeycomb.
The three-dimensional woven carbon fiber honeycomb has high specific strength and specific modulus, is not easy to delaminate and crack, has good thermal stability and excellent mechanical property, and has good designability, but an effective preparation method is not available at present due to complex weaving structure and high demoulding difficulty.
Disclosure of Invention
The invention provides a device and a method for preparing a carbon fiber three-dimensional woven honeycomb composite material aiming at the defects of the prior art.
The technical scheme of the invention is as follows:
a preparation device of a carbon fiber three-dimensional woven honeycomb composite material comprises a mold (1), a first core rod (4), a second core rod (5) and a resin flow guiding and vacuumizing device; the die (1) is provided with fixing holes (2) and demolding holes (3), the outermost circle is completely provided with the fixing holes (2), a plurality of demolding holes (3) and fixing holes (2) are arranged in an area surrounded by the outermost circle of fixing holes (2), each demolding hole (3) is correspondingly provided with a second core rod (5), and each fixing hole (2) is correspondingly provided with a first core rod (4); the positions and the intervals of the fixed holes (2) and the demoulding holes (3) are set according to the size of a cell of a carbon fiber honeycomb composite material to be formed, after the first core rod (4) and the second core rod (5) are installed, the adjacent surfaces between the first core rod (4) and the second core rod (5) are provided with a honeycomb cell interval (16), the honeycomb cell interval (16) is used for accommodating a carbon fiber honeycomb, and the honeycomb cell interval (16) is used as a resin flow channel.
In the preparation device, the area surrounded by the outermost circle of fixing holes (2) is a rectangular area, and a plurality of rows of demoulding holes (3) and fixing holes (2) are arranged in the area surrounded by the outermost circle of fixing holes (2); the rows of demoulding holes (3) and the fixing holes (2) are alternately arranged, and one row of fixing holes (2) is arranged at intervals in every 1-3 rows of demoulding holes (3).
In the preparation device, the fixing holes (2) are in the shape of a half regular hexagon, the demoulding holes (3) can be round holes or polygonal holes, and the mould (1) is in a plate-shaped structure with the thickness of 12-15 mm; one end of the first core rod (4) is a regular hexagonal prism, the other end of the first core rod is a semi-regular hexagonal pyramid, and the length of the semi-regular hexagonal pyramid is 1/2-1 times of the total length of the first core rod (4); the top of the semi-regular hexagonal pyramid is positioned at the end of the first core rod (4), and the external profile of the bottom of the semi-regular hexagonal pyramid is the same as that of the fixing hole (2).
According to the preparation device, the top of one end of the regular hexagonal prism of the first core rod (4) is provided with the screw hole (6), the screw is screwed into the screw hole (6), and the screw is used after forming is finished so that the first core rod (4) can be conveniently pulled out of the carbon fiber honeycomb.
According to the preparation device, the second core rod (5) is a regular hexagonal prism, the external outline size of the regular hexagonal prism of the first core rod (4) and the second core rod (5) is the same as the outline structure of the honeycomb holes of the carbon fiber honeycomb, and the regular hexagonal prisms of the first core rod (4) and the second core rod (5) can be inserted into the honeycomb holes of the carbon fiber honeycomb; the top of the second core rod (5) is provided with a screw hole (6), a screw can be screwed into the screw hole (6), and the second core rod (5) can be conveniently pulled out of the carbon fiber honeycomb by the screw.
The preparation device comprises a resin diversion and vacuum pumping device and a resin diversion and vacuum pumping device, wherein the resin diversion and vacuum pumping device comprises a vacuum bag (10), a diversion net (11) and an object stage (12), a plurality of holes corresponding to fixing holes (2) on a mould (1) are formed in the object stage (12), after the mould (1), a first core rod (4), a second core rod (5) and a carbon fiber honeycomb (7) are assembled, a semi-hexagonal pyramid is inserted into the plurality of holes for fixing, the diversion net (11) is laid on the object stage (12) to integrally cover the mould (1), the first core rod (4), the second core rod (5) and the carbon fiber honeycomb (7), the vacuum bag (10) is sleeved outside the diversion net (11), diversion holes (13) are formed in the vacuum bag (10), a diversion pipe (9) and an air valve (8) are arranged on the diversion holes (13), a circle of sealant (14) is laid between the vacuum bag (10) and the object stage to realize sealing, the carbon fiber honeycomb is soaked with resin by vacuumizing through a guide pipe (9).
The preparation device also comprises a demolding tool (15), wherein the demolding tool (15) is of a rake-shaped structure and comprises 3-5 brads and a handle, after resin curing is completed, the brads are inserted into demolding holes (3) behind the mold, the handle is knocked, the first core rod (4) and the second core rod (5) can be separated from the mold (1), demolding of the carbon fiber honeycomb composite material is realized, the first core rod (4) and the second core rod (5) which are difficult to demold in individual honeycomb holes can be pulled out by screws fixed in screw holes (6) in the tops of the first core rod (4) and the second core rod (5).
The method for preparing the carbon fiber three-dimensional woven honeycomb composite material according to any one of the preparation devices comprises the following steps:
the first step is as follows: spraying or soaking a release agent on the mold, the first core rod (4) and the second core rod (5);
the second step is that: taking a carbon fiber honeycomb woven structure, inserting a first core rod (4) and a second core rod (5) into carbon fiber honeycomb holes according to the arrangement sequence of fixing holes (2) and demolding holes (3) arranged on a mold (1), inserting one end of a semi-hexagonal pyramid of the first core rod (4) into the fixing hole (2) on the mold (1) according to the position of the fixing hole (2) on the mold (1), and enabling the second core rod (5) to correspond to the demolding hole (3) on the mold;
the third step: inserting a first core rod (4), a second core rod (5) and a mold (1) after the carbon fiber honeycomb is assembled in the second step into a hole of an objective table (12) through a semi-hexagonal pyramid at one end of the first core rod (4), laying a flow guide net (11) at the upper ends of the first core rod (4) and the second core rod (5), arranging a vacuum bag (10) and a flow guide hole (13) outside the flow guide net (11), and vacuumizing to soak resin by adopting conventional epoxy resin or polyimide resin;
the fourth step: after the diversion is finished, curing according to a resin process curve, taking out after curing, adopting a designed rake-shaped demolding tool (15), enabling rake teeth to correspond to the centers of demolding holes (3) on the reverse side of the mold one by one, and then knocking a handle of the rake by a hammer to rapidly demold;
the fifth step: and cutting the carbon fiber honeycomb by using a precision cutting machine, and cutting off the residual materials around to finally obtain the carbon fiber honeycomb.
In the first step, the mould, the first core rod (4) and the second core rod (5) are sprayed or soaked with a release agent for 4-5 times, the drying is carried out at the interval of 5 minutes between each operation, 4-5 layers of thin and uniform wet films are formed through 4-5 operations, and the coating is solidified by standing for 30 minutes at room temperature.
In the method, in the second step, after all the first core rods and the second core rods are assembled, screws are screwed into the tops of the first core rods (4) and the second core rods (5), and the screws are 5mm higher than the tops of the first core rods (4) and the second core rods (5).
The invention has the beneficial effects that:
(1) the invention provides a forming method for a continuous carbon fiber three-dimensional woven honeycomb composite material through the design of a die, a core rod structure and a process, and fills the blank of the preparation process of the three-dimensional woven carbon fiber honeycomb.
(2) The forming method provided by the invention has the advantages that the production efficiency is high, the forming regularity of the carbon fiber honeycomb is high, the bonding performance of the woven carbon fiber honeycomb interface is good, the structure is stable, and the overall mechanical performance is excellent; the mold can be repeatedly used, only a simple mold and a core rod are needed, the flexibility is high, the manufacturing cost of the carbon fiber honeycomb is favorably reduced, and the engineering application of the carbon fiber honeycomb is promoted.
(3) The invention provides an effective idea for the design of other three-dimensional braided composite materials, particularly the forming process of the hollow three-dimensional braided composite material, and has important significance for solving the technical problems of manufacturing various three-dimensional braided structures with complex shapes and reducing the production cost of the hollow composite material.
Drawings
FIG. 1 is a schematic view of a mold of the present invention.
FIG. 2 is a schematic view of the first mandrel of the present invention.
FIG. 3 is a schematic view of the structure of a second mandrel bar according to the present invention.
Fig. 4 is a schematic structural view of the assembled die, first and second mandrels, and carbon fiber honeycomb.
Fig. 5 is a schematic view of the structure shown in fig. 4 with portions of the first mandrel and the second mandrel removed.
Fig. 6 is a top view of the structure shown in fig. 4 with a honeycomb cell spacing between the first mandrel and the second mandrel.
FIG. 7 is a schematic view of the resin guiding and evacuating apparatus.
Fig. 8 is a schematic view of the structure of the demolding tool.
In the figure, 1-mould, 2-fixing hole, 3-demoulding hole, 4-first core rod, 5-second core rod, 6-screw hole, 7-carbon fiber honeycomb, 8-air valve, 9-draft tube, 10-vacuum bag, 11-flow guide net, 12-objective table, 13-flow guide hole, 14-sealant, 15-demoulding tool and 16-honeycomb cell space.
Detailed Description
The present invention will be described in detail with reference to specific examples.
Referring to fig. 1-7, a device for preparing a carbon fiber three-dimensional woven honeycomb composite material comprises a mold 1, a first core rod 4, a second core rod 5 and a resin flow guiding and vacuumizing device; the die 1 is of a plate-shaped structure with the thickness of 12-15mm, the die 1 is provided with fixing holes 2 and demolding holes 3, the outermost ring is completely provided with the fixing holes 2, a plurality of rows of demolding holes 3 and fixing holes 2 are arranged in an area surrounded by the fixing holes 2 of the outermost ring, the demolding holes 3 and the fixing holes 2 are alternately arranged, for example, one row of fixing holes 2 is arranged at intervals in every 1-3 rows of demolding holes 3; each demoulding hole 3 is correspondingly provided with a second core rod 5, and each fixing hole 2 is correspondingly provided with a first core rod 4.
The shape of fixed orifices 2 is half regular hexagon, be about to regular hexagon along the central line cutting that crosses two summits and obtain half regular hexagon (also be the isosceles trapezoid that a topside and waist are equal in fact), drawing of patterns hole 3 can be the round hole also can be the polygon, the position and the interval of fixed orifices 2 and drawing of patterns hole 3 are set for according to the cell size of the carbon fiber honeycomb combined material of wanting the shaping, after first plug 4, second plug 5 have been installed, adjacent surface has honeycomb cell interval 16 between first plug 4, the second plug 5, honeycomb cell interval 16 is used for holding the carbon fiber honeycomb, and honeycomb cell interval 16 is as resin flow channel.
One end of the first mandrel 4 is a regular hexagonal prism, and the other end of the first mandrel 4 is a semi-regular hexagonal pyramid (namely, the hexagonal pyramid is vertically cut along a center line passing through two vertexes on the bottom surface to obtain the semi-regular hexagonal pyramid), and the length of the semi-regular hexagonal pyramid accounts for 1/2-1 of the total length of the first mandrel 4; the top of the half regular hexagonal pyramid is located at the end of the first mandrel 4, the outer contour of the bottom of the half regular hexagonal pyramid is the same as that of the fixing hole 2, and therefore the half regular hexagonal pyramid can be tightly matched with the mold 1 after being inserted into the fixing hole 2, and the demolding is facilitated due to the fact that one end of the half regular hexagonal pyramid is small and the other end of the half regular hexagonal pyramid is large.
The top of one end of the regular hexagonal prism of the first mandrel 4 is provided with a screw hole 6, a screw can be screwed into the screw hole 6, and the first mandrel 4 can be conveniently pulled out of the carbon fiber honeycomb by the screw.
The second core rod 5 is a regular hexagonal prism, the external outline size of the regular hexagonal prism of the first core rod 4 and the second core rod 5 is the same as the outline structure of the honeycomb holes of the carbon fiber honeycomb, and the regular hexagonal prism of the first core rod 4 and the second core rod 5 can be inserted into the honeycomb holes of the carbon fiber honeycomb; the top of the second core rod 5 is provided with a screw hole 6, and a screw can be screwed into the screw hole 6, so that the second core rod 5 can be conveniently pulled out of the carbon fiber honeycomb by the screw.
The resin diversion and vacuumizing device comprises a vacuum bag 10, a diversion net 11 and an objective table 12, wherein a plurality of holes corresponding to fixing holes 2 in a mold 1 are formed in the objective table 12, the mold 1, a first core rod 4, a second core rod 5 and a carbon fiber honeycomb 7 are assembled, a semi-hexagonal pyramid is inserted into the plurality of holes for fixing, the diversion net 11 is laid on the objective table 12 to integrally cover the mold 1, the first core rod 4, the second core rod 5 and the carbon fiber honeycomb 7, the vacuum bag 10 is sleeved outside the diversion net 11, a diversion hole 13 is formed in the vacuum bag 10, a diversion pipe 9 and an air valve 8 are arranged in the diversion hole 13, and a circle of sealant 14 is laid between the vacuum bag 10 and the objective table to realize sealing.
Referring to fig. 8, the mold releasing device 15 is further included, the mold releasing device 15 is a rake-shaped structure and includes 3-5 rake nails and a handle, after the resin is cured, the rake nails are inserted into the mold releasing holes 3 behind the mold, the handle is knocked, the first core rod 4 and the second core rod 5 can be separated from the mold 1, the mold releasing of the carbon fiber honeycomb composite material is realized, the first core rod 4 and the second core rod 5 which are difficult to release in the individual honeycomb holes can be pulled out by screws fixed in screw holes 6 at the tops of the first core rod 4 and the second core rod 5. The demolding tool 15 may also be made into double rows or multiple rows of rake teeth, the size of which is 1.5-2mm smaller than the size of the demolding holes in the mold.
Example 1
The first step is as follows: firstly, spraying a mold and a core rod with a release agent, drying at the interval of 5 minutes between each layer of operation, forming 4 layers of thin and uniform wet films through four operations, standing for 30 minutes at room temperature to cure the coating(ii) a The thickness of the die 1 used in this embodiment is 12mm, and the fixing holes 2 in the die 1 are arranged as follows: the fixing holes 2 on the outermost ring are enclosed into a rectangular area, one row of fixing holes 2 are arranged in every other row of demoulding holes 3 in the rectangular area, the number of the fixing holes 2 is about 60 percent of the number of the whole mould cells, and the diameter of each demoulding hole 3 is 4.5 mm; the core rod is made of 310S stainless steel and has a thermal expansion coefficient of 15.9 multiplied by 10-6The angle is 30 degrees;
the second step is that: taking a carbon fiber honeycomb weaving structure with the height of 30mm, the length and the width of 200 multiplied by 60mm and complete periphery lock seaming, inserting a first core rod 4 and a second core rod 5 into a carbon fiber honeycomb hole according to the arrangement sequence of a fixed hole 2 and a demoulding hole 3 which are arranged on a mould 1, inserting one end of a semi-hexagonal pyramid of the first core rod 4 into the fixed hole 2 on the mould 1 according to the position of the fixed hole 2 on the mould 1, and enabling the second core rod 5 to correspond to the demoulding hole 3 on the mould; after all the first core rods and the second core rods are assembled, screws are screwed into the tops of the first core rods 4 and the second core rods 5, the thread specification is M2, and the screws are 5mm higher than the tops of the first core rods 4 and the second core rods 5;
the third step: inserting the first core rod 4, the second core rod 5 and the mold 1 which are assembled with the carbon fiber honeycomb in the second step into a hole of an objective table 12 through a semi-hexagonal pyramid at one end of the first core rod 4, laying a flow guide net 11 at the upper ends of the first core rod 4 and the second core rod 5, arranging a vacuum bag 10 and a flow guide hole 13 outside the flow guide net 11, adopting conventional epoxy resin, wherein the viscosity of the resin is 170mPa & s, the vacuum degree is 0.8bar, the temperature is 22 ℃, and vacuumizing to soak the resin;
the fourth step: and (3) curing according to a resin process curve after the diversion is finished, wherein the curing conditions are as follows: curing at normal temperature for 24 hours, then placing the materials into an oven for gradient heating, preserving heat at 60 ℃ for 0.5 hour, preserving heat at 100 ℃ for 0.5 hour, preserving heat at 150 ℃ for 0.5 hour, preserving heat at 195 ℃ for 2 hours, cooling and then taking out, adopting a designed rake-shaped demolding tool 15, enabling rake teeth to correspond to the centers of demolding holes 3 on the reverse side of the mold one by one, then knocking a handle of a rake by a hammer for rapid demolding, wherein the number of the rake teeth is 4;
the fifth step: cutting the carbon fiber honeycomb by using a precision cutting machine, wherein the rotating speed of the cutting machine is 2800r/s, the feed rate is 1.5mm/min, and cutting off the residual materials around by using a silicon carbide grinding wheel sheet with the diameter of phi 100mm to finally obtain the carbon fiber honeycomb.
Example 2
The first step is as follows: firstly, spraying a mold and soaking a core rod by using a release agent to form 5 layers of thin and uniform wet films; drying at the interval of 6 minutes for each layer of operation, then putting the mould and the core rod into an oven, and heating at 150 ℃ for 5 minutes for curing; the thickness of the die 1 used in this embodiment is 14mm, and the fixing holes 2 in the die 1 are arranged as follows: the fixing holes 2 on the outermost ring enclose a rectangular area, one row of fixing holes are arranged in every two rows of demoulding holes 3 in the rectangular area, the number of the fixing holes is about 50% of the number of the whole mould cells, and the diameter of each demoulding hole 3 is 5.5 mm; the core rod is made of 309S stainless steel and has a thermal expansion coefficient of 16.81 multiplied by 10-6The angle is 25 degrees;
the second step is that: taking a carbon fiber honeycomb weaving structure with the height of 80mm, the length and the width of 200 multiplied by 60mm and complete peripheral overlock, and performing the other operations in the second step of the embodiment 1;
the third step: inserting the first core rod 4, the second core rod 5 and the mold 1 which are assembled with the carbon fiber honeycomb in the second step into holes of an objective table 12 through a semi-hexagonal pyramid at one end of the first core rod 4, laying a flow guide net 11 at the upper ends of the first core rod 4 and the second core rod 5, arranging a vacuum bag 10 and 2 flow guide holes 13 outside the flow guide net 11, adopting polyimide resin, wherein the viscosity of the resin is 225mPa & s, the vacuum degree is 0.95bar, the temperature is 25 ℃, and vacuumizing to soak the resin;
the fourth step: and (3) curing according to a resin process curve after the diversion is finished, wherein the curing conditions are as follows: preserving heat at 80 ℃ for 90min, preserving heat at 120 ℃ for 90min, preserving heat at 160 ℃ for 90min, preserving heat at 200 ℃ for 90min, preserving heat at 280 ℃ for 30min, preserving heat at 325 ℃ for 120min, cooling and taking out, adopting a designed rake-shaped demolding tool 15, enabling rake teeth to correspond to the centers of demolding holes 3 on the reverse side of a mold one by one, then knocking the rake by a hammer to rapidly demold, wherein the number of the rake teeth is 4;
the fifth step: cutting the carbon fiber honeycomb by using a precision cutting machine, wherein the rotating speed of the cutting machine is 3200r/s, the feed rate is 1.5mm/min, a brown corundum grinding wheel is adopted, the diameter of the grinding wheel is phi 150mm, and the residual materials at the periphery are cut off to finally obtain the carbon fiber honeycomb.
Example 3
The first step is as follows: firstly, spraying a mold and soaking a core rod by using a release agent to form 4 layers of thin and uniform wet films; drying at the interval of 5 minutes for each layer of operation, then putting the mould and the core rod into an oven, and heating at 150 ℃ for 5 minutes for curing; the thickness of the used die 1 is 15mm, and the fixing holes 2 in the die are arranged as follows: the fixing holes 2 on the outermost circle enclose a rectangular area, one row of fixing holes are arranged in every three rows of demoulding holes 3 in the rectangular area, the number of the fixing holes is about 50% of the number of the whole mould cells, and the diameter of each demoulding hole 3 is 5.5 mm; the core rod is made of 304 stainless steel and has a thermal expansion coefficient of 17.3 × 10-6The angle is 35 degrees;
the second step is that: the carbon fiber honeycomb weaving structure with the height of 120mm, the length and the width of 250 multiplied by 80mm and complete peripheral lock seaming is carried out, and the rest of the operation is the same as that of the embodiment 1;
the third step: inserting the first core rod 4, the second core rod 5 and the mold 1 which are assembled with the carbon fiber honeycomb in the second step into holes of an objective table 12 through a semi-hexagonal pyramid at one end of the first core rod 4, laying a flow guide net 11 at the upper ends of the first core rod 4 and the second core rod 5, arranging a vacuum bag 10 and a flow guide hole 13 outside the flow guide net 11, adopting novel epoxy resin which presents thermoplastic characteristics at the temperature of more than 80 ℃, wherein the viscosity of the resin is 190mPa & s, the vacuum degree is 0.9bar, the temperature is 25 ℃, and vacuumizing to soak the resin;
the fourth step: and (3) curing according to a resin process curve after the diversion is finished, wherein the curing conditions are as follows: curing at normal temperature for 12 hours, keeping the temperature at 60 ℃ for 60min, keeping the temperature at 100 ℃ for 60min, keeping the temperature at 165 ℃ for 120min, cooling, taking out, adopting a designed rake-shaped demolding tool 15, enabling rake teeth to correspond to the centers of demolding holes 3 on the reverse side of a mold one by one, and then knocking the rake by a hammer to rapidly demold, wherein the number of the rake teeth is 6;
the fifth step: cutting the carbon fiber honeycomb by using a precision cutting machine, wherein the rotating speed of the cutting machine is 3200r/s, the feed rate is 1.5mm/min, a silicon carbide grinding wheel sheet is adopted, the diameter of the grinding wheel is phi 200mm, and the residual materials around the grinding wheel sheet are cut off to finally obtain the carbon fiber honeycomb.
It will be understood that modifications and variations can be made by persons skilled in the art in light of the above teachings and all such modifications and variations are intended to be included within the scope of the invention as defined in the appended claims.
Claims (10)
1. The preparation device of the carbon fiber three-dimensional woven honeycomb composite material is characterized by comprising a mold (1), a first core rod (4), a second core rod (5) and a resin flow guiding and vacuumizing device; the die (1) is provided with fixing holes (2) and demolding holes (3), the outermost circle is completely provided with the fixing holes (2), a plurality of demolding holes (3) and fixing holes (2) are arranged in an area surrounded by the outermost circle of fixing holes (2), each demolding hole (3) is correspondingly provided with a second core rod (5), and each fixing hole (2) is correspondingly provided with a first core rod (4); the positions and the intervals of the fixed holes (2) and the demoulding holes (3) are set according to the size of a cell of a carbon fiber honeycomb composite material to be formed, after the first core rod (4) and the second core rod (5) are installed, the adjacent surfaces between the first core rod (4) and the second core rod (5) are provided with a honeycomb cell interval (16), the honeycomb cell interval (16) is used for accommodating a carbon fiber honeycomb, and the honeycomb cell interval (16) is used as a resin flow channel; the shape of the fixing hole (2) is a half regular hexagon; one end of the first core rod (4) is a regular hexagonal prism, and the other end of the first core rod is a semi-regular hexagonal pyramid.
2. The preparation device according to claim 1, wherein the area enclosed by the outermost circle of fixing holes (2) is a rectangular area, and a plurality of rows of demoulding holes (3) and fixing holes (2) are arranged in the area enclosed by the outermost circle of fixing holes (2); the rows of demoulding holes (3) and the fixing holes (2) are alternately arranged, and one row of fixing holes (2) is arranged at intervals in every 1-3 rows of demoulding holes (3).
3. The preparation device according to claim 1, characterized in that the demoulding hole (3) can be a round hole or a polygonal hole, and the mould (1) is a plate-shaped structure with the thickness of 12-15 mm; the length of the semi-regular hexagonal pyramid accounts for 1/2-1 times of the total length of the first core rod (4); the top of the semi-regular hexagonal pyramid is positioned at the end of the first core rod (4), and the external profile of the bottom of the semi-regular hexagonal pyramid is the same as that of the fixing hole (2).
4. The manufacturing apparatus according to claim 1, wherein the first core rod (4) is provided with a screw hole (6) at the top of one end of the regular hexagonal prism, and a screw is screwed into the screw hole (6), so that the screw is utilized to pull the first core rod (4) out of the carbon fiber honeycomb after the forming is finished.
5. The manufacturing apparatus according to claim 1, wherein the second mandrel (5) is a regular hexagonal prism, the outer contour size of the regular hexagonal prism of the first mandrel (4) and the second mandrel (5) is the same as the contour structure of the honeycomb holes of the carbon fiber honeycomb, and the regular hexagonal prism of the first mandrel (4) and the second mandrel (5) can be inserted into the honeycomb holes of the carbon fiber honeycomb; the top of the second core rod (5) is provided with a screw hole (6), a screw can be screwed into the screw hole (6), and the second core rod (5) can be conveniently pulled out of the carbon fiber honeycomb by the screw.
6. The manufacturing device according to claim 1, wherein the resin diversion and vacuum-pumping device comprises a vacuum bag (10), a diversion net (11) and an object stage (12), the object stage (12) is provided with a plurality of holes corresponding to the fixing holes (2) on the mold (1), after the mold (1), the first core rod (4), the second core rod (5) and the carbon fiber honeycomb (7) are assembled, the semi-regular hexagonal pyramid is inserted into the plurality of holes for fixing, the diversion net (11) is laid on the object stage (12) to integrally cover the mold (1), the first core rod (4), the second core rod (5) and the carbon fiber honeycomb (7), the vacuum bag (10) is sleeved outside the diversion net (11), the diversion holes (13) are arranged on the vacuum bag (10), the diversion pipes (9) and the air valves (8) are arranged on the diversion holes (13), a circle of sealant (14) is laid between the vacuum bag (10) and the object stage for sealing, the carbon fiber honeycomb is soaked with resin by vacuumizing through a guide pipe (9).
7. The preparation device according to claim 1, characterized in that the device further comprises a demolding tool (15), the demolding tool (15) is a rake-shaped structure and comprises 3-5 brads and a handle, after the resin is cured, the brads are inserted into the demolding holes (3) after the mold, the handle is knocked to separate the first core rod (4) and the second core rod (5) from the mold (1) to realize demolding of the carbon fiber honeycomb composite material, the first core rod (4) and the second core rod (5) which are difficult to demold in the individual honeycomb holes can be pulled out by screws fixed in screw holes (6) at the tops of the first core rod (4) and the second core rod (5).
8. The method for preparing the carbon fiber three-dimensional woven honeycomb composite material according to any one of claims 1 to 7, comprising the steps of:
the first step is as follows: spraying or soaking a release agent on the mold, the first core rod (4) and the second core rod (5);
the second step is that: taking a carbon fiber honeycomb woven structure, inserting a first core rod (4) and a second core rod (5) into carbon fiber honeycomb holes according to the arrangement sequence of fixing holes (2) and demolding holes (3) arranged on a mold (1), inserting one end of a semi-regular hexagonal pyramid of the first core rod (4) into the fixing hole (2) on the mold (1) according to the position of the fixing hole (2) on the mold (1), and enabling the second core rod (5) to correspond to the demolding hole (3) on the mold;
the third step: inserting a first core rod (4), a second core rod (5) and a mold (1) after the carbon fiber honeycomb is assembled in the second step into a hole of an objective table (12) through a semi-regular hexagonal pyramid at one end of the first core rod (4), laying a flow guide net (11) at the upper ends of the first core rod (4) and the second core rod (5), arranging a vacuum bag (10) and a flow guide hole (13) outside the flow guide net (11), and vacuumizing to soak resin by adopting conventional epoxy resin or polyimide resin;
the fourth step: after the diversion is finished, curing according to a resin process curve, taking out after curing, adopting a designed rake-shaped demolding tool (15), enabling rake teeth to correspond to the centers of demolding holes (3) on the reverse side of the mold one by one, and then knocking a handle of the rake by a hammer to rapidly demold;
the fifth step: and cutting the carbon fiber honeycomb by using a precision cutting machine, and cutting off the residual materials around to finally obtain the carbon fiber honeycomb.
9. The method according to claim 8, wherein in the first step, the mold, the first core rod (4) and the second core rod (5) are sprayed or soaked with the release agent for 4-5 times, the drying time is set between each operation, 4-5 layers of thin and uniform wet films are formed after 4-5 operations, and the coating is solidified after standing for 30 minutes at room temperature.
10. The method according to claim 8, characterized in that in the second step, after all the first and second mandrels have been assembled, screws are screwed into the tops of the first and second mandrels (4, 5), the screws being 5mm higher than the tops of the first and second mandrels (4, 5).
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| CN112331375B (en) * | 2020-11-23 | 2022-09-20 | 四川玄武岩纤维新材料研究院(创新中心) | Fiber honeycomb fabric nuclear shielding composite material and preparation method and application thereof |
| CN113561522B (en) * | 2021-07-19 | 2022-09-16 | 南京航空航天大学 | Three-dimensional woven fiber reinforced honeycomb preparation device and method based on thermal expansion flexible core mold |
| CN113665034B (en) * | 2021-07-30 | 2023-04-28 | 南京玻璃纤维研究设计院有限公司 | Composite material forming die and forming method |
| CN114193677A (en) * | 2021-11-30 | 2022-03-18 | 天津大学 | Rapid curing device, curing system and curing method for composite honeycomb |
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