CN114274549B - Preparation facilities of fibre reinforced composite material honeycomb core - Google Patents
Preparation facilities of fibre reinforced composite material honeycomb core Download PDFInfo
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- CN114274549B CN114274549B CN202111605021.2A CN202111605021A CN114274549B CN 114274549 B CN114274549 B CN 114274549B CN 202111605021 A CN202111605021 A CN 202111605021A CN 114274549 B CN114274549 B CN 114274549B
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Abstract
The invention discloses a preparation device of a fiber reinforced composite material honeycomb core material, which comprises a positioning bottom plate, a positioning die, a shaping die and an in-plane pressurizing device, wherein the positioning bottom plate is provided with a positioning hole; the two sides of the positioning bottom plate are provided with connecting holes and positioning holes, and the middle part is provided with corresponding positioning grooves according to the designed honeycomb configuration; the positioning die comprises a hexagonal positioning die, a square positioning die, a first half-reentrant angle hexagonal positioning die and a second half-reentrant angle hexagonal positioning die; the shaping mold comprises a trapezoidal shaping mold, a quadrilateral shaping mold and a half-reentrant angle hexagonal shaping mold; the in-plane pressurizing device comprises a thin side plate, a thick side plate and a bolt. The preparation device adopted by the invention realizes the preparation of various single-layer or multi-layer fiber reinforced composite material honeycomb core materials, ensures the preparation precision and the interface performance of the honeycomb structure, and solves the problems of insufficient curing pressure, poor interface performance, low fiber volume content, easy deformation and wrinkling of fibers and the like existing in the prior art for preparing composite material honeycombs.
Description
Technical Field
The invention belongs to the field of composite material preparation and forming, and particularly relates to a preparation device of a fiber reinforced composite material honeycomb core material.
Background
As a traditional light structure, the excellent mechanical property of the honeycomb sandwich structure is mainly derived from the structure and not the performance of a base material, so that the honeycomb structure can obtain high specific strength and high specific rigidity only through thin walls. Meanwhile, the direction of the honeycomb structure is changed, so that the interior of the sandwich structure can be kept open, the multifunctional characteristics of integrating bearing and thermal control, stealth, energy absorption, protection, actuation, energy storage and damping are easy to realize, and the functions of pre-burying, heat transfer and the like are easy to realize. Due to good mechanical properties and excellent designability, the honeycomb material serving as a main type of the light porous material is widely applied to various fields including aerospace, transportation, surface ships, heavy machinery, military protection and the like. Common honeycomb materials comprise stainless steel, aluminum alloy and aramid paper, but the defects of high density, easy buckling failure, low strength, poor thermal stability and the like of the materials prevent the honeycomb sandwich structure from being applied in wider fields.
The use of fiber reinforced composites is an effective method for developing ultralight honeycomb materials with excellent mechanical properties. In recent years, a fiber reinforced composite honeycomb structure which is light and excellent in mechanical properties attracts attention in replacing the conventional aluminum honeycomb and aramid paper honeycomb. Compared to metal, polymer and aramid paper, fiber reinforced composites have outstanding advantages such as high specific strength, high specific stiffness, excellent fatigue resistance, corrosion resistance and high temperature resistance. The low thermal deformation capability and high stability of the all-carbon fiber honeycomb sandwich structure make the all-carbon fiber honeycomb sandwich structure hopeful to be applied to a supporting structure, an antenna reflecting surface, a gravity gradiometer base and the like of an optical instrument. At present, the all-carbon fiber honeycomb sandwich structure is successfully applied to the all-carbon fiber space telescope of the American ULTRA project.
The fiber reinforced resin matrix composite material is an anisotropic material, and the forming process has strong dependence on a mold. Compared with a metal honeycomb structure, the preparation of the fiber reinforced resin matrix composite material honeycomb structure has great difficulty in the early stage. The preparation technology is the most critical link for promoting the wide application of the sandwich structure of the related composite material in engineering, and the sandwich structure of the related composite material is often required to produce high-quality products with low cost and high efficiency. The failure modes and the structural defects of the material structures prepared by different preparation methods are different, and the main preparation technologies of the composite material honeycomb core material at the present stage are divided into five types:
(1) The traditional hot-press forming technology comprises the following steps: the method comprises the steps of preparing a single prepreg strip of the honeycomb core material by utilizing a metal mold hot press molding technology, and then bonding a plurality of prepreg strips to form the complete composite material honeycomb core material. However, the process needs secondary hot-pressing bonding, the prepared honeycomb structure is irregular in shape, and the preparation of the small-size honeycomb structure cannot be realized.
(2) Vacuum assisted resin mold transfer technique: and (3) paving the dry fiber unidirectional cloth or fabric between the molds, and curing and molding after soaking the dry fiber unidirectional cloth or fabric in resin. The honeycomb structure fiber prepared by the method has low volume content and weak mechanical property, and cannot exert the advantages of a composite material.
(3) The interlocking assembly forming technology comprises the following steps: the honeycomb core material with a specific structure is formed by interlocking the composite material rib plates after machining and grooving. The structure prepared by the method has original defects at the interlocking part, and the mechanical property of the composite material is seriously reduced because the composite material is subjected to grooving by machining so that the fibers are discontinuous. In addition, the method cannot realize the preparation of the special-shaped honeycomb, such as a half-concave hexagonal honeycomb with a zero poisson ratio structure and a negative poisson ratio structure concave hexagonal honeycomb.
(4) 3D printing and forming technology: the honeycomb structure is prepared by short or long fiber printing. However, due to the limitation of the prior art, the direction of the fiber is single, so that the bearing capacity of the honeycomb structure in some directions is weak, and the mechanical property requirement of the bearing structure cannot be met.
(5) Cutting-folding preparation technology: the honeycomb core material is prepared by cutting, folding, assembling and curing the fiber prepreg. However, the method needs to be rolled and folded in a low-temperature environment, operation difficulty is high, and extrusion friction is generated between the core mold and the fiber prepreg when the core mold is assembled, so that the fiber prepreg is easy to deform and wrinkle. In addition, due to the lack of transverse curing pressure, the prepared honeycomb core material has poor interface performance.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a preparation device of a fiber reinforced composite material honeycomb core material, which can be used for preparing various types and specifications of thin-wall fiber reinforced composite material honeycomb core materials; the preparation technology has high material utilization rate and is suitable for honeycomb structures of large-size cells and small-size cells; in the preparation stage, a mould is adopted for high-precision positioning and shaping, so that the honeycomb structures prepared in different batches have stable performance; in the assembling stage, in-plane pressurization is carried out, in the curing stage, pressure is maintained in a vacuum environment, and the interface performance of the demolded honeycomb core material is excellent; in addition, the preparation technology can also be used for realizing the preparation of the integrally formed fiber reinforced composite material honeycomb sandwich structure of the panel-core material co-curing in a specific direction.
The invention is realized by adopting the following technical scheme:
a preparation device of a fiber reinforced composite material honeycomb core material comprises a positioning bottom plate, a positioning die, a shaping die and an in-plane pressurizing device;
the two sides of the positioning bottom plate are provided with a counter bore and a first positioning hole, and the middle part is provided with a corresponding positioning groove according to the designed honeycomb configuration; processing shaping molds and positioning molds with different shapes according to the designed honeycomb configuration, wherein the shaping molds comprise a trapezoidal shaping mold, a quadrangular shaping mold and a half-reentrant angle hexagonal shaping mold; the positioning die comprises a hexagonal positioning die, a square positioning die, a first half reentrant angle hexagonal positioning die and a second half reentrant angle hexagonal positioning die; the in-plane pressurizing device comprises a thin side plate, a thick side plate and a bolt, a second threaded hole and a positioning hole are formed in the bottom of the thick side plate, a plurality of first threaded holes are formed in the side face of the thick side plate, and the in-plane pressurizing device is used for pressurizing a positioning die and a shaping die which are arranged in the middle of the positioning bottom plate through the thin side plate, the thick side plate and the bolt.
The invention has the further improvement that the bottoms of all the positioning moulds are provided with positioning columns which are in transition fit with the positioning grooves of the positioning bottom plate.
The invention has the further improvement that the trapezoidal shaping mould is one half of the main body of the half-reentrant angle hexagonal positioning mould, and the quadrilateral shaping mould is one half of the main body of the first half-reentrant angle hexagonal positioning mould; half reentrant angle hexagon design mould is unanimous with first half reentrant angle hexagon positioning die main part, assembles between hexagon positioning die and first half reentrant angle hexagon positioning die, and trapezoidal design mould and quadrangle design mould distribute in first half reentrant angle hexagon positioning die both sides.
The invention is further improved in that all the shaping molds are assembled by heating to 40-50 ℃, and the bottom surfaces of the shaping molds are tightly attached to the surface of the positioning bottom plate during assembly, assembled to a specified position along the Y direction and pressed tightly.
The invention has the further improvement that the second half reentrant angle hexagon positioning mould is used in the assembling stage and is disassembled before the curing stage; the size between two parallel surfaces of the second half-reentrant angle hexagon positioning die is smaller than that of the first half-reentrant angle hexagon positioning die, the second half-reentrant angle hexagon positioning die is in close contact with the half-reentrant angle hexagon shaping die in the assembling process, no interaction is generated with the prepreg rectangular strip, and the deformation and the folding of fibers are avoided.
The invention has the further improvement that the thick side plate and the positioning bottom plate form accurate and tight assembly through the bolt and the positioner, and the in-plane pressurization is realized by driving the thin side plate to press the positioning mould, the shaping mould and the semi-concave angle hexagonal honeycomb structure preformed body paved with the fiber prepreg through the bolt.
The invention has the further improvement that the square positioning mould which is closely contacted with the in-plane pressurizing device is made of non-metallic material polytetrafluoroethylene with high thermal expansion coefficient and easy demoulding, and other positioning moulds and shaping moulds are made of metal material with high thermal expansion coefficient.
The invention is further improved in that a single-layer or multi-layer rectangular strip of fiber prepreg is laid on one side of the thin panel, and is directly contacted with a shaping mould, a positioning mould and the rectangular strip of fiber prepreg which are assembled in the middle, and then the honeycomb sandwich structure of the X-direction fiber reinforced composite material which is formed integrally by co-curing the panel and the core material can be prepared by pressurizing and curing.
The invention has the further improvement that the Y-direction fiber reinforced composite material honeycomb sandwich structure which is formed by integrally co-curing the panel and the core material can be prepared by improving the positioning bottom plate and supplementing in-plane pressurizing devices on two Y-direction sides;
or, by improving the positioning bottom plate, the in-plane pressurizing devices are supplemented on two sides in the Y direction, so that the in-plane bidirectional pressurization in the X direction and the Y direction is completed, and the preparation of the multilayer fiber reinforced composite material honeycomb core material can be completed;
or, by replacing the positioning bottom plate, the positioning die and the shaping die, the preparation device can be used for preparing the fiber reinforced composite material honeycomb core materials and sandwich structures with different shapes and structures.
Compared with the prior art, the invention has at least the following beneficial technical effects:
the invention provides a preparation device of a fiber reinforced composite material honeycomb core material, which comprises a positioning bottom plate, a positioning die, a shaping die and an in-plane pressurizing device, wherein the positioning bottom plate is provided with a positioning hole; wherein, the positioning bottom plate both sides are equipped with the counter sink of connecting the use and fix a position the first locating hole of use, and the middle part sets up corresponding constant head tank according to the honeycomb configuration that designs. And designing and processing shaping molds and positioning molds in different shapes according to the designed configuration of the honeycomb core material. Taking a half-concave hexagonal honeycomb structure with zero Poisson's ratio mechanical characteristics as an example, the positioning mold comprises a hexagonal positioning mold, a square positioning mold, a first half-concave angle hexagonal positioning mold and a second half-concave angle hexagonal positioning mold. And the positioning cylinders are arranged below the positioning dies and form transition fit with the positioning grooves of the positioning bottom plate, so that the shaping dies can be accurately positioned in the assembling process. The hexagonal positioning die, the first half-reentrant angle hexagonal positioning die and the second half-reentrant angle hexagonal positioning die need to be matched with the shaping die in the assembling process, certain curing pressure needs to be provided through thermal expansibility assistance in the curing process, and a metal material with good thermal expansibility, such as aluminum alloy, is preferably selected; the square positioning die and the outermost side shaping die form matching positioning in the assembling stage, the square positioning die is turned and assembled after being disassembled in the curing stage, and the square positioning die and the pressurizing device are matched to complete in-plane pressurization, so that a non-metal material which is good in thermal expansion and easy to demould, such as polytetrafluoroethylene, is preferably selected.
The shaping mold comprises a trapezoidal shaping mold, a quadrilateral shaping mold and a half-reentrant angle hexagonal shaping mold. The trapezoid shaping mold is one half of the half concave angle hexagon positioning mold main body, and the quadrilateral shaping mold is one half of the first half concave angle hexagon positioning mold main body. Half reentrant angle hexagon design mould is unanimous with first half reentrant angle hexagon positioning die main part, assembles between hexagon positioning die and first half reentrant angle hexagon positioning die, and trapezoidal design mould and quadrangle design mould distribute in first half reentrant angle hexagon positioning die both sides, make the mould outside parallel and level after whole assembly, are favorable to in-plane pressure device to evenly pressurize the fibre preimpregnation material rectangle strip in the outside.
The in-plane pressurizing device comprises a thin side plate, a thick side plate and a bolt, wherein a first threaded hole is formed in the side face of the thick side plate, and a second positioning hole and a second threaded hole are formed in the bottom of the thick side plate. The thick side plates and the positioning bottom plate are accurately positioned and connected by using the positioner and the bolts, and pressure is applied to the thin side plates by the bolts so as to transmit the pressure to the assembled shaping mold and positioning mold, so that the semi-reentrant hexagonal honeycomb structure pre-formed body paved by the fiber prepreg assembled between the molds keeps enough curing pressure.
After the rectangular fiber prepreg strip, the positioning die and the shaping die are assembled, the in-plane pressurizing device applies certain pressure to reduce gaps among the dies, so that the dies are attached to the rectangular fiber prepreg strip and maintain certain pressure. Placing the whole set of preparation device in a vacuum oven, and setting curing temperature and time according to the curing process of the selected prepreg in a vacuum environment for curing; after the solidification is finished, demolding is carried out when the preparation device is cooled to below 60 ℃ to obtain the required fiber reinforced resin matrix honeycomb core material; and finally, bonding a composite material panel on the symmetrical surface of the honeycomb core material according to the design to obtain the fiber reinforced composite material honeycomb sandwich structure.
Furthermore, a single-layer or multi-layer rectangular prepreg strip is paved on the thin side plate and is in direct contact with the shaping mold, the positioning mold and the rectangular fiber prepreg strip which are assembled in the middle, and then the integral positioning mold and the shaping mold are applied with in-plane pressure in the X direction, so that the honeycomb structure preform paved with the fiber prepreg is compressed and keeps a certain curing pressure. And stopping pressurizing when the distance between the two thin side plates reaches the structural design requirement. And then curing and removing the die to complete the panel-core material co-curing and integral molding of the X-direction fiber reinforced composite material honeycomb sandwich structure. Compared with a fiber reinforced composite material honeycomb sandwich structure prepared by panel-core material bonding, the structure has more excellent panel-core material interface performance by adopting co-curing and integral forming.
Further, by improving the positioning bottom plate, an in-plane pressurizing device can be supplemented on two sides in the Y direction, and the method is utilized to prepare the integrally formed Y-direction fiber reinforced composite material honeycomb sandwich structure.
Further, by improving the positioning bottom plate, an in-plane pressurizing device can be supplemented on two sides in the Y direction, and in-plane X-direction and Y-direction bidirectional pressurization can be completed, so that the preparation of the multilayer fiber reinforced composite material honeycomb core material is completed.
Further, according to different honeycomb configurations, corresponding positioning bottom plates, shaping molds and positioning molds are designed, and fiber reinforced composite material honeycomb core materials and sandwich structures with different geometric shapes, such as rectangular, triangular, hexagonal and negative poisson ratio structure concave hexagonal honeycomb structures and other shapes, can be prepared.
In summary, the present invention has the following advantages:
1. compared with a fiber reinforced composite material honeycomb sandwich structure prepared by panel-core material bonding, the fiber reinforced composite material honeycomb sandwich structure has more excellent panel-core material interface performance by adopting co-curing and integral forming.
2. According to the invention, through improvement of the positioning bottom plate, the in-plane pressurizing devices can be supplemented on the two sides in the Y direction, and the integrally formed Y-direction fiber reinforced composite material honeycomb sandwich structure is prepared by using the method.
3. By improving the positioning bottom plate, the invention can supplement in-plane pressurizing devices on two sides in the Y direction, can complete in-plane X-direction and Y-direction bidirectional pressurization, and can complete the preparation of the multilayer fiber reinforced composite material honeycomb core material.
4. According to different honeycomb configurations, the invention designs corresponding positioning bottom plates, shaping molds and positioning molds, and can prepare fiber reinforced composite material honeycomb core materials and sandwich structures with different geometric shapes, such as rectangular, triangular, hexagonal, concave hexagonal structures with negative Poisson ratio structures and other shapes.
Drawings
FIG. 1 is an overall isometric view of a manufacturing apparatus of the present invention;
FIG. 2 shows a semi-reentrant hexagonal honeycomb structure preform and a cured and secondarily processed honeycomb core material, which are laid by the fiber prepreg;
FIGS. 3 (a) and (b) are schematic views of the positioning base plate for preparing the semi-reentrant hexagonal honeycomb structure of the fiber reinforced composite material according to the present invention;
FIGS. 4 (a) to (c) are schematic views of three positioning molds of the manufacturing apparatus of the present invention;
FIGS. 5 (a) to (c) are schematic views of three types of molding dies of the manufacturing apparatus of the present invention;
FIG. 6 is a schematic view of a thin side plate of the in-plane pressurizing apparatus of the present invention;
FIG. 7 is a schematic view of a thick side plate of the in-plane pressurization apparatus of the present invention;
FIGS. 8 (a) and (b) are schematic views of the retainer of the in-plane pressurizing apparatus of the present invention;
FIG. 9 is an exploded view of an assembly step of the manufacturing apparatus of the present invention;
FIG. 10 is a schematic view of a second half-reentrant hexagonal positioning die used in the assembly process of the present invention;
FIGS. 11 (a) to (c) are schematic views of the structure of the fiber reinforced composite honeycomb core in three different directions;
FIG. 12 is a schematic view of an X-direction fiber reinforced composite honeycomb sandwich structure integrally prepared by a panel and a core material and a preparation device thereof;
FIG. 13 is a schematic view of a device for producing a hexagonal honeycomb structure coated with a fibrous prepreg according to the present invention;
FIG. 14 is a schematic view of a fiber reinforced composite hexagonal honeycomb core of the present invention after curing and secondary processing;
FIG. 15 is a schematic view of a locating base plate for use in making a hexagonal honeycomb of fiber reinforced composite material according to the present invention;
FIG. 16 is a schematic view of a hexagonal shaped die for making hexagonal honeycomb structures of fiber reinforced composites according to the present invention.
Description of the reference numerals:
1. the method comprises the following steps of (1) laying a fiber prepreg on a semi-reentrant angle hexagonal honeycomb structure preform, 2, positioning a bottom plate, 3, a hexagonal positioning mold, 4, a trapezoidal shaping mold, 5, a quadrilateral shaping mold, 6, a semi-reentrant angle hexagonal shaping mold, 7, a square positioning mold, 8, a first semi-reentrant angle hexagonal positioning mold, 9, a thin side plate, 10, a thick side plate, 11, a bolt, 12, a positioner male pin, 13, a positioner female pin, 14, a fiber prepreg rectangular strip, 15 and a second semi-reentrant angle hexagonal positioning mold; 16. the honeycomb sandwich structure comprises a Z-direction fiber reinforced composite material honeycomb sandwich structure, 17 and Y-direction fiber reinforced composite material honeycomb sandwich structures, 18 and X-direction fiber reinforced composite material honeycomb sandwich structures, 19, a second positioning bottom plate, 20, a hexagonal shaping mold and 21, and a hexagonal honeycomb structure preformed body paved by fiber prepreg;
101. the cured and secondarily processed hexagonal honeycomb core material with half concave angles comprises a cured and secondarily processed hexagonal honeycomb core material with half concave angles, 201, a first positioning hole, 202, a first positioning groove, 203, a mixed type positioning groove, 204, a second positioning groove, 205, a counter bore, 206, a third positioning groove, 301, a hexagonal positioning mold main body, 302, a hexagonal positioning mold positioning cylinder, 701, a square positioning mold main body, 702, a square positioning mold positioning cylinder, 801, a first hexagonal positioning mold main body with half concave angles, 802, a first hexagonal positioning mold positioning cylinder with half concave angles, 1001, a first threaded hole, 1002, a second positioning hole, 1003, a second threaded hole, 1201, a positioning device male pin positioning cylinder, 1202, a positioning device male pin main body, 1301, a positioning device female pin positioning round hole, 1302, a positioning device female pin main body, 1501, a second hexagonal positioning mold main body with half concave angles, 1502, a hexagonal positioning mold positioning cylinder with half concave angles, 2101, a cured and secondarily processed hexagonal honeycomb core material.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, the device for preparing the fiber reinforced composite material honeycomb core material provided by the invention comprises a semi-reentrant angle hexagonal honeycomb structure preform 1 paved with fiber prepreg, a positioning bottom plate 2, a positioning die, a shaping die and an in-plane pressurizing device.
As shown in fig. 3, the positioning bottom plate 2 is provided with connecting counter bores 205 and positioning first positioning holes 201 on both sides, and the middle part is provided with a first positioning groove 202, a hybrid positioning groove 203, a second positioning groove 204 and a third positioning groove 206 according to the designed honeycomb configuration.
Fig. 4 shows three positioning molds used in the assembly of the manufacturing apparatus of the present invention to the curing stage: the positioning device comprises a hexagonal positioning die 3, a square positioning die 7 and a first half-reentrant angle hexagonal positioning die 8. The positioning mould comprises a main body part and a positioning cylinder at the bottom, and is integrally formed by machining, and materials are selected according to the functions and the assembly positions of the positioning mould. The hexagonal positioning mold main body 301 and the first half-reentrant angle hexagonal positioning mold main body 801 need to be matched with a shaping mold in an assembling process, certain curing pressure needs to be provided through thermal expansibility of the hexagonal positioning mold main body and the shaping mold in a curing process, and a metal material with good thermal expansibility, such as aluminum alloy, is preferably selected; the square positioning die main body 701 is matched and positioned with the outermost shaping die in the assembling stage, is turned over and assembled after being disassembled in the curing stage, and is matched with an in-plane pressurizing device to complete pressurization, so that a non-metal material which is good in thermal expansion and easy to demould, such as polytetrafluoroethylene, is preferably selected. The positioning cylinder at the bottom of the positioning mold and the positioning groove in the middle of the positioning bottom plate 2 form transition fit, so that the accurate positioning in the assembling process of the sizing mold is completed, and the geometric precision of the fiber prepreg paved semi-reentrant hexagonal honeycomb structure preform 1 is ensured. Wherein the hexagonal positioning mold positioning cylinder 302 and the third positioning groove 206 form a transition fit; the square positioning die positioning cylinder 702 forms transition fit with the first positioning groove 202; the first half-reentrant-angle hexagonal positioning mold positioning cylinder 802 and the second positioning groove 204 form transition fit; hybrid detent 203 is a hybrid of first detent 202 and second detent 204 and may form a transition fit with square positioning die positioning cylinder 702 and first half-reentrant hexagonal positioning die positioning cylinder 802.
Fig. 5 shows three types of shaping molds of the manufacturing apparatus of the present invention, including: a trapezoid shaping mold 4, a quadrilateral shaping mold 5 and a half-reentrant angle hexagon shaping mold 6. The positioning die is preferably made of a metal material (such as aluminum alloy) with good thermal expansion, and the positioning die and the aluminum alloy are integrally formed by machining. The trapezoid shaping mold 4 is one half of the hexagonal positioning mold main body, the quadrilateral shaping mold 5 is one half of the half-reentrant angle hexagonal shaping mold 6, and the trapezoid shaping mold and the quadrilateral shaping mold are assembled on the outermost side, so that the outer side of the integrally assembled mold is flush, and uniform pressurization of the rectangular fiber prepreg strips 14 on the outermost side by an in-plane pressurization device is facilitated; the half reentrant angle hexagon shaping mold 6 is identical to the first half reentrant angle hexagon positioning mold main body 801, and is assembled between the hexagon positioning mold and the first half reentrant angle hexagon positioning mold. And a plurality of rectangular strips 14 of the fiber prepreg are paved between the positioning mould and the shaping mould to form the fiber prepreg paved semi-reentrant angle hexagonal honeycomb structure preform 1.
In the case of the thin panel 9 shown in fig. 6, which requires a flat surface and a certain deformation resilience, a metal material such as aluminum alloy or stainless steel is preferable.
As shown in fig. 7, the thick side plate 10 has a plurality of first threaded holes 1001 on the side surface, a second threaded hole 1003 in the middle of the bottom surface, and second positioning holes 1002 on the two sides of the bottom.
As shown in fig. 8, the male locator pin 12 and the female locator pin 13 are both made of high-hardness, wear-resistant and rust-proof S136 die steel, the male pin body 1202 is in interference fit with the first locating hole 201, and the female locator pin body 1302 is in interference fit with the second locating hole 1002 of the thick side plate 10. The concentricity of the locator male pin positioning round column 1201 and the locator female pin positioning round hole 1301 is less than or equal to 0.003mm, and high-precision matched positioning can be realized.
The thick side plate assembled with the locator female pin 13 is positioned and assembled with the locating bottom plate 2 assembled with the locator male pin 12, and the two are locked by screws through the counter sunk hole 205 and the second threaded hole 1003. The bolts 11 with the same number are tightly pressed on the thin side plate 9 through the first threaded holes 1001 to push the sizing die and the positioning die to clamp the semi-reentrant hexagonal honeycomb structure preformed body 1 paved with the fiber prepreg, so that the interface is tightly attached and a certain pressure is kept.
The following discussion of the process for preparing a single layer fiber fabric reinforced composite honeycomb sandwich structure according to the above apparatus:
firstly, cleaning the surfaces of the positioning bottom plate 2, the shaping mold, the positioning mold and the transverse pressurizing device and coating a release agent for 3 times at intervals of at least 20 minutes. In order to better lay the fiber prepreg on the surface of the mold, the shaping mold is placed in an oven and heated to 40-50 ℃, and the fiber prepreg is taken out of the oven after being assembled.
Fig. 9 is an exploded view of the assembly steps of the manufacturing device of the present invention, and the rectangular strip of fiber prepreg 14 may be any type of fiber prepreg, such as glass fiber prepreg, carbon fiber prepreg, aramid fiber prepreg, plant fiber prepreg, etc. If single-layer coating is adopted, in order to ensure the mechanical property of the structure in all directions, fabric type fiber prepreg is preferably selected.
As shown in fig. 9 (a), which is a plan view of a center positioning groove for positioning the base plate 2, the assembling process will be discussed in steps as follows:
the first step is as follows: as shown in fig. 9 (b), the hexagonal positioning mold 3 is fitted into the rightmost side of the third positioning groove 206, two rectangular strips 14 of fiber prepreg are laid on the left side of the hexagonal positioning mold 3, and the assembly of the hexagonal positioning mold 3 is continued on the left side thereof. Eight hexagonal positioning molds 3 and 14 rectangular strips of fiber prepreg 14 are fitted in the third positioning grooves 206 according to the above steps, then the hexagonal positioning molds 3 on the left and right outermost sides are replaced with trapezoidal setting molds 4, and square positioning molds 7 are fitted on both sides of the third positioning grooves 206 on the outer sides.
The second step: as shown in fig. 9 (c), starting from the left side, the two rectangular strips of fibrous prepreg 14 laid down in the middle of trapezoidal shaped mold 4 and hexagonal positioning mold 3 in the first step are separated with a special laying tool and pre-laid down along the shape of the mold, and then half-reentrant hexagonal shaped mold 6 is taken out of the oven, fitted between the two separated rectangular strips of fibrous prepreg 14 and pressed in the Y direction for 5 to 10 seconds. When assembling the half-reentrant hexagonal shaping mold 6, the bottom surface thereof is required to be closely attached to the surface of the positioning base plate 2, and then assembled to a designated position in the Y direction and pressed. If the shaping die is assembled in the direction perpendicular to the positioning bottom plate 2, the surface of the die and the surface of the fiber prepreg are extruded and rubbed, so that the fibers are deformed and folded, and the mechanical property of the honeycomb structure is influenced. Next, a second half-reentrant hexagonal positioning mold 15 is fitted tightly against half-reentrant hexagonal sizing mold 6 to second positioning groove 204 of row 1 of positioning base plate 2, and second half-reentrant hexagonal positioning mold positioning cylinder 1502 is in transition fit with second positioning groove 204. And then assembling the rest half concave angle hexagon shaping die 6 and the second half concave angle hexagon positioning die 15 according to the steps. The size of the second half reentrant angle hexagonal positioning die main body 1501 along the X direction is smaller than that of the half reentrant angle hexagonal shaping die 6, so that friction extrusion with the fiber prepreg rectangular strip 14 in the assembling process is avoided.
The third step: as shown in fig. 9 (d), the two second half-reentrant hexagonal positioning dies 15 fitted on the leftmost side of the row 1 in the second step are first disassembled, and the half-reentrant hexagonal sizing die 6 and the second half-reentrant hexagonal positioning dies 15 are fitted on the row 2 in the method of the second step. The remaining molds are then assembled in sequence from left to right.
Fourthly, as shown in fig. 9 (e), after the half-reentrant angle hexagonal shaping mold 6 and the second half-reentrant angle hexagonal positioning mold 15 are assembled at the position of the row 3 according to the method of the third step, the bottom surface of the quadrilateral shaping mold 5 is attached to the surface of the positioning base plate 2, and the residual space of the second half-reentrant angle hexagonal positioning mold 15 assembled in the second step and the fourth step is pushed and compressed; finally, the square type positioning mold 7 is fitted in the hybrid type positioning groove 203. The square positioning die 7 is higher than the shaping die, and the square positioning dies 7 on the two sides can be tightened by means of the rubber band, so that the assembled die still keeps the original position in the subsequent assembling step.
The fifth to eighth steps assemble the sizing die and the positioning die in fig. 9 (f) - (i) according to the method in the second to fourth steps.
Ninth, as shown in fig. 9 (j), the second half-reentrant hexagonal positioning mold 15 assembled in the eighth step in row 7 is disassembled and replaced with the first half-reentrant hexagonal positioning mold 8 having the same size in the X direction as the half-reentrant hexagonal setting mold 6, and the excess rectangular fiber prepreg strips 14 are cut.
Tenth, as shown in fig. 9 (k), the thick thin plate 10, the positioning base plate 2, the thin side plate 9, and the bolts 11 are initially assembled as shown in the drawing; then all the square positioning moulds 7 are disassembled and turned over to be tightly attached to the thin side plate 9; and finally, screwing the bolt 11 by using a torque wrench, and applying an in-plane pressure in the X direction to the integral positioning die and the shaping die to compress the semi-reentrant angle hexagonal honeycomb structure pre-formed body 1 paved and covered by the fiber prepreg and keep a certain pressure. And stopping pressurizing when the distance between the two thin side plates reaches the structural design requirement.
After the assembly is completed according to the steps shown in FIG. 9, the integral preparation device shown in FIG. 1 is placed in a vacuum oven, and is vacuumized for 10-15 minutes and is heated and cured under negative pressure of-0.1 MPa according to the curing process of the prepreg; after the solidification is finished, the integral preparation device can be taken out for demoulding after being naturally cooled to 60 ℃, and the demoulding process is as follows:
firstly, removing force of all bolts 11, and detaching the thin side plate 9, the square positioning mould 7 and the thick side plate 10;
secondly, after the device is turned over, two sides of the positioning bottom plate 2 are placed on a supporting seat, so that the suspended heights of the shaping mold and the positioning mold in the middle are larger than the self heights;
thirdly, tapping the hexagonal positioning mold positioning cylinder 702 and the first half-reentrant-angle hexagonal positioning mold positioning cylinder 802 from the back of the positioning base plate 2 by using a rubber hammer and a wooden cylinder to separate all molds in the middle and the cured composite material honeycomb structure from the positioning base plate 2;
and fourthly, because the mould and the composite material honeycomb core material can not be automatically separated after curing, the whole body is required to be placed on the supporting seat, and the mould is vertically tapped by utilizing a rubber hammer and a wooden cylinder until the mould and the composite material honeycomb core material are completely separated.
And fifthly, polishing the surface of the composite material honeycomb structure after demolding, and removing redundant parts through machining to obtain the cured and secondarily processed semi-reentrant angle hexagonal honeycomb core material 101.
After the composite material honeycomb core material is prepared, the composite material panel can be bonded to the symmetrical surface of the honeycomb core material through the adhesive film by using the adhesive film through a hot pressing process, and fiber reinforced composite material honeycomb sandwich structures with three directions and different mechanical properties are prepared, as shown in fig. 11, a Z-direction fiber reinforced composite material honeycomb sandwich structure 16, a Y-direction fiber reinforced composite material honeycomb sandwich structure 17 and an X-direction fiber reinforced composite material honeycomb sandwich structure 18 are respectively arranged. The honeycomb structure is changed in direction, so that the interior of the sandwich structure can be kept open, the multifunctional characteristics of integrating bearing, thermal control, stealth, energy absorption, protection, actuation, energy storage and damping are easy to realize, and the functions of pre-embedding, heat transfer and the like are easy to realize.
Example 1
As shown in fig. 1 and fig. 11, the whole set of preparation apparatus is used to complete the preparation of the half-reentrant angle hexagonal honeycomb sandwich structure of fiber reinforced composite material in three different directions according to the above-mentioned process flows of assembling, curing, demoulding, post-treatment and panel pasting.
Example 2
As shown in fig. 12, in the ninth step of fig. 9 (j), the square positioning molds 7 on both sides are disassembled, then a single-layer or multi-layer rectangular strip 14 of fiber prepreg is laid on one side of the thin panel 9 and is directly contacted with the shaping mold, the positioning mold and the rectangular strip 14 of fiber prepreg which are assembled in the middle, and then the in-plane pressure in the X direction is applied to the positioning mold and the shaping mold which are integrated, so that the semi-concave hexagonal honeycomb structure preform 1 laid by the fiber prepreg is compressed and kept at a certain pressure. And stopping pressurizing when the distance between the two thin side plates reaches the structural design requirement. And then curing and demolding are carried out, so that the X-direction fiber reinforced composite material honeycomb sandwich structure 18 which is formed by integrally curing the panel and the core material can be obtained. Compared with the fiber reinforced composite material honeycomb sandwich structure prepared by bonding, the sandwich structure integrally formed by co-curing has more excellent panel-core material interface performance.
By improving the positioning bottom plate 2, an in-plane pressurizing device can be supplemented on two sides in the Y direction, and the Y-direction fiber reinforced composite material honeycomb sandwich structure 17 which is formed by integrally co-curing the panel and the core material is prepared by the method.
Example 3
By improving the positioning bottom plate 2, the in-plane pressurizing devices are supplemented on two sides in the Y direction, so that the in-plane X-direction and Y-direction bidirectional pressurization is completed, and the preparation of the multilayer fiber reinforced composite material honeycomb sandwich structure can be completed.
Example 4
In addition to example 1, the positioning bottom plate 2 is replaced by a second positioning bottom plate 19 (see fig. 15), the half-reentrant hexagonal shaping mold 6 is replaced by a hexagonal shaping mold 20 (fig. 16), the assembly process is performed as shown in fig. 13 with reference to the assembly step of fig. 9, and then curing-demolding-post-treatment is performed, so that a cured and secondary-processed hexagonal honeycomb core 2101 (fig. 14) can be obtained. Similarly, the fiber reinforced composite material honeycomb core material and sandwich structure with different shapes and structures, such as rectangular, triangular and negative Poisson ratio structure concave hexagon, can be prepared by improving the positioning bottom plate.
Although the present invention has been described in detail with reference to the above embodiments, it should be understood by those skilled in the art that: the invention can be modified and substituted with equivalents without departing from the spirit and scope of the invention, which should be construed as being limited only by the claims.
Claims (9)
1. The preparation device of the fiber reinforced composite material honeycomb core material is characterized by comprising a positioning bottom plate (2), a positioning die, a shaping die and an in-plane pressurizing device;
the two sides of the positioning bottom plate (2) are provided with countersunk holes and first positioning holes, and the middle part is provided with corresponding positioning grooves according to the designed honeycomb configuration; processing shaping molds and positioning molds with different shapes according to the designed honeycomb configuration, wherein the shaping molds comprise a trapezoidal shaping mold (4), a quadrilateral shaping mold (5) and a half-reentrant angle hexagonal shaping mold (6); the positioning die comprises a hexagonal positioning die (3), a square positioning die (7), a first half-reentrant-angle hexagonal positioning die (8) and a second half-reentrant-angle hexagonal positioning die (15); the in-plane pressurizing device comprises a thin side plate (9), a thick side plate (10) and a bolt (11), a second threaded hole and a positioning hole are formed in the bottom of the thick side plate (10), a plurality of first threaded holes are formed in the side face of the thick side plate, and the in-plane pressurizing device is used for pressurizing a positioning die and a shaping die which are arranged in the middle of the positioning bottom plate (2) through the thin side plate (9), the thick side plate (10) and the bolt (11).
2. The device for preparing the fiber reinforced composite honeycomb core material according to claim 1, wherein the bottom of each positioning mold is provided with a positioning cylinder, and the positioning cylinders are in transition fit with the positioning grooves of the positioning bottom plate (2).
3. The device for preparing the fiber reinforced composite honeycomb core material according to claim 1, wherein the trapezoidal shaping mold (4) is one half of the main body of the half-reentrant angle hexagonal positioning mold, and the quadrilateral shaping mold (5) is one half of the main body of the first half-reentrant angle hexagonal positioning mold (8); half reentrant angle hexagon design mould is unanimous with first half reentrant angle hexagon positioning die (8) main part, assembles between hexagon positioning die (3) and first half reentrant angle hexagon positioning die (8), and trapezoidal design mould (4) and quadrangle design mould (5) distribute in first half reentrant angle hexagon positioning die (8) both sides.
4. The device for preparing the fiber reinforced composite material honeycomb core material according to claim 1, wherein all the sizing molds are assembled by heating to 40-50 ℃, and the bottom surfaces of the sizing molds are tightly attached to the surface of the positioning bottom plate (2) during assembly, assembled to a specified position along the Y direction and pressed tightly.
5. The apparatus for manufacturing a fiber reinforced composite honeycomb core material according to claim 1, wherein the second half-reentrant hexagonal positioning mold (15) is used in an assembly stage, and is disassembled before a curing stage; the size between two parallel surfaces of the second half-reentrant angle hexagon positioning die (15) is smaller than that of the first half-reentrant angle hexagon positioning die (8), the second half-reentrant angle hexagon positioning die is in close contact with the half-reentrant angle hexagon sizing die (6) in the assembling process, no interaction is generated with the fiber prepreg rectangular strip (14), and the deformation and the folding of fibers are avoided.
6. The device for preparing the fiber reinforced composite material honeycomb core material according to claim 1, wherein the thick side plate (10) and the positioning bottom plate (2) form accurate close assembly through bolts and a positioner, and the in-plane pressurization is realized by driving the thin side plate (9) to press the positioning mold, the shaping mold and the half-reentrant hexagonal honeycomb structure preform (1) paved with the fiber prepreg through the bolts (11).
7. The device for preparing the fiber reinforced composite material honeycomb core material according to claim 1, wherein the square positioning mold (7) in close contact with the in-plane pressurizing device is made of a non-metal material polytetrafluoroethylene with a high thermal expansion coefficient and easy demoulding, and other positioning molds and shaping molds are made of a metal material with a high thermal expansion coefficient.
8. The device for preparing the fiber reinforced composite material honeycomb core material is characterized in that a single-layer or multi-layer rectangular fiber prepreg strip (14) is laid on one side of a thin side plate (9) and is in direct contact with a shaping mold, a positioning mold and the rectangular fiber prepreg strip (14) which are assembled in the middle, and then the X-direction fiber reinforced composite material honeycomb sandwich structure (18) which is formed by panel-core material co-curing and integral molding is prepared by pressure curing.
9. The apparatus for manufacturing a fiber reinforced composite honeycomb core material according to claim 1 or 8, wherein a Y-direction fiber reinforced composite honeycomb sandwich structure (17) formed by co-curing a panel-core material and integrally molding can be manufactured by modifying the positioning base plate (2) and adding an in-plane pressurizing device to both sides in the Y direction;
or, the positioning bottom plate (2) is improved, and an in-plane pressurizing device is supplemented on two sides in the Y direction, so that in-plane bidirectional pressurization in the X direction and the Y direction is completed, and the preparation of the multilayer fiber reinforced composite material honeycomb core material can be completed;
or the positioning bottom plate (2), the positioning die and the shaping die are replaced, and the fiber reinforced composite material honeycomb core materials and sandwich structures with different shapes and structures can be prepared by the preparation device.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5128192A (en) * | 1990-02-02 | 1992-07-07 | Northrop Corporation | Braided preform process for thermoplastic honeycomb cores |
| CN102343680A (en) * | 2011-09-29 | 2012-02-08 | 哈尔滨工业大学 | Mould and method for integrally forming fiber reinforced hexagonal honeycomb-structured core |
| CN105946246A (en) * | 2016-05-10 | 2016-09-21 | 河北科技大学 | Preparation method for carbon fiber honeycomb core materials |
| CN109532165A (en) * | 2019-01-22 | 2019-03-29 | 杭州友凯船艇有限公司 | A kind of honeycomb core composite material and its preparation method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105584058B (en) * | 2015-12-16 | 2017-12-19 | 上海晋飞复合材料科技有限公司 | The technique that composite makes high ferro equipment ceiling board |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5128192A (en) * | 1990-02-02 | 1992-07-07 | Northrop Corporation | Braided preform process for thermoplastic honeycomb cores |
| CN102343680A (en) * | 2011-09-29 | 2012-02-08 | 哈尔滨工业大学 | Mould and method for integrally forming fiber reinforced hexagonal honeycomb-structured core |
| CN105946246A (en) * | 2016-05-10 | 2016-09-21 | 河北科技大学 | Preparation method for carbon fiber honeycomb core materials |
| CN109532165A (en) * | 2019-01-22 | 2019-03-29 | 杭州友凯船艇有限公司 | A kind of honeycomb core composite material and its preparation method |
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