CN113910636A - Fiber-reinforced concave hexagonal honeycomb core and forming die and forming method thereof - Google Patents
Fiber-reinforced concave hexagonal honeycomb core and forming die and forming method thereof Download PDFInfo
- Publication number
- CN113910636A CN113910636A CN202111160853.8A CN202111160853A CN113910636A CN 113910636 A CN113910636 A CN 113910636A CN 202111160853 A CN202111160853 A CN 202111160853A CN 113910636 A CN113910636 A CN 113910636A
- Authority
- CN
- China
- Prior art keywords
- concave hexagonal
- concave
- fiber
- reinforced
- trapezoidal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 239000000835 fiber Substances 0.000 claims abstract description 27
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 17
- 230000002787 reinforcement Effects 0.000 claims description 7
- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000000465 moulding Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 229920005989 resin Polymers 0.000 claims description 4
- 239000011347 resin Substances 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 239000010410 layer Substances 0.000 description 8
- 239000002356 single layer Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000002360 preparation method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000010146 3D printing Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000007373 indentation Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
Abstract
The invention belongs to the field of honeycomb sandwich structures, and particularly discloses a fiber-reinforced concave hexagonal honeycomb core, a forming die and a forming method thereof, wherein the forming die comprises an assembly component and a reinforcing component, wherein: the assembly comprises concave hexagonal columns, trapezoidal units and end clamping blocks, the concave hexagonal columns and the trapezoidal units are transversely and alternately arranged, and both sides of each concave hexagonal column are concave hexagonal columns; the trapezoidal unit comprises two trapezoidal bodies which are symmetrical in the vertical direction relative to the lower bottom surface; the two end clamping blocks are respectively matched with the concave hexagonal columns on the two sides, so that all the concave hexagonal columns, the trapezoidal units and the end clamping blocks form a plate-shaped structure; gaps are reserved between the adjacent concave hexagonal columns and the trapezoidal units, between the concave hexagonal columns on the two sides and the end clamping blocks, and between the lower bottom surfaces of the two trapezoidal bodies; the reinforcing component is used for fixing the plate-shaped structure. The invention can form the fiber reinforced concave hexagonal honeycomb sandwich structure core with the negative Poisson ratio characteristic.
Description
Technical Field
The invention belongs to the field of honeycomb sandwich structures, and particularly relates to a fiber-reinforced concave hexagonal honeycomb core, a forming die and a forming method thereof.
Background
The honeycomb sandwich structure has excellent mechanical properties as a light structure, and the composite material with high specific stiffness and high specific strength is used as a matrix material of the honeycomb sandwich structure, so that the mechanical properties of the formed fiber reinforced honeycomb sandwich structure are obviously improved. The fiber-reinforced concave hexagonal honeycomb sandwich structure consists of a front panel, a rear panel and a concave hexagonal honeycomb core, the honeycomb sandwich structure has a negative Poisson ratio effect due to the special structural deformation characteristics, and has high shear modulus, indentation resistance, fracture toughness and good sound absorption and vibration reduction capability compared with other structures with positive Poisson ratios, so that the composite material honeycomb sandwich structure with the negative Poisson ratio property has a deeper application prospect in the fields of aerospace, ships, automobiles and the like.
However, because the forming process of the honeycomb sandwich structure is relatively complex, the preparation method of the fiber-reinforced concave hexagonal honeycomb sandwich structure is few, and the existing 3D printing preparation method mainly adopted cannot better exert the performance of unidirectional fiber reinforcement, so that the mechanical property of the prepared fiber-reinforced concave hexagonal honeycomb sandwich structure is poor.
Disclosure of Invention
Aiming at the defects or improvement requirements of the prior art, the invention provides a fiber-reinforced concave hexagonal honeycomb core, a forming die and a forming method thereof, and aims to quickly and effectively prepare a fiber-reinforced concave hexagonal honeycomb sandwich structure with a negative poisson ratio property and better exert the potential of unidirectional fiber reinforcement.
To achieve the above object, according to a first aspect of the present invention, there is provided a forming mold for a fiber-reinforced concave hexagonal honeycomb core, comprising an assembling member and a reinforcing member, wherein:
the assembly comprises concave hexagonal columns, trapezoidal units and end clamping blocks, wherein the concave hexagonal columns and the trapezoidal units are arranged alternately along the transverse direction, and both sides of the concave hexagonal columns are concave hexagonal columns; the trapezoidal unit comprises two trapezoidal bodies which are symmetrically arranged in the vertical direction relative to the lower bottom surface of the trapezoidal body; the two end clamping blocks are respectively matched with the concave hexagonal columns on the two sides, so that the plurality of concave hexagonal columns, the plurality of trapezoidal units and the two end clamping blocks form a plate-shaped structure together; gaps are reserved between adjacent concave hexagonal columns and the trapezoidal units, between concave hexagonal columns on two sides and the end clamping blocks, and between the lower bottom surfaces of the two trapezoidal bodies; the reinforcing component is used for fixing the plate-shaped structure.
Preferably, the reinforcing assembly comprises a horizontal stud bolt, two ends of the concave hexagonal cylinder along the length direction of the concave hexagonal cylinder are respectively provided with a clamping groove, the positions of the end part clamping blocks, which are close to the two ends, are provided with through holes, and the through holes and the clamping grooves at the same end are communicated with each other; the horizontal stud bolt is placed in the clamping groove, and two ends of the horizontal stud bolt penetrate through the through hole, so that the concave hexagonal cylinder and the end clamping block are fixed in the transverse direction.
Preferably, the reinforcing component comprises a clamping plate, the upper surfaces and the lower surfaces of the concave hexagonal columns, the trapezoidal units and the end clamping blocks, which are close to the two ends, are respectively provided with a communicated rectangular groove, and one side of the clamping plate, which faces the plate-shaped structure, is provided with a rectangular boss, and the rectangular boss is arranged in the rectangular groove.
As further preferred, the reinforcement assembly includes vertical stud bolts, square through holes have been seted up near horizontal both ends to the splint, vertical stud bolts pass the square through holes on two upper and lower splint that correspond, thereby will indent hexagon cylinder, trapezoidal unit and tip clamp splice are fixed on vertical direction.
Preferably, the reinforcing component comprises cover plates, and the two cover plates are respectively located on the upper plane and the lower plane of the plate-shaped structure and are used for covering the prepregs on the upper surface and the lower surface of the concave hexagonal cylinder.
As a further preferred, the assembly member is made of a die steel material.
Preferably, the inclined angles of the two inclined planes of the trapezoid body are the same as the inclined angle of the concave inclined plane of the concave hexagonal cylinder, and the inclined angle of the concave inclined plane of the concave hexagonal cylinder is the same as the inclined plane of the end clamping block.
According to a first aspect of the invention, a method for forming a fiber-reinforced concave hexagonal honeycomb core is provided, which is realized by adopting the forming die, and comprises the following steps:
s1, laying fiber reinforced prepreg on two inclined planes and the bottom surface of the trapezoid body, the concave inclined plane of the concave hexagonal cylinder and the inclined plane of the end clamping block matched with the concave hexagonal cylinder, and then assembling a plate-shaped structure;
s2, laying fiber reinforced prepregs on the upper and lower surfaces of the inner concave hexagonal cylinder, and fixing the plate-shaped structure through a reinforcing component to obtain a combined body;
and S3, heating the combined body, cooling, and then taking down the forming die to obtain the fiber-reinforced concave hexagonal honeycomb core.
Preferably, the fiber-reinforced prepreg is a fiber-reinforced resin-based prepreg, in step S3, the heating temperature is 120-130 ℃, the temperature is kept for 1-3 h, the curing molding is performed, and the forming mold is taken down after the temperature is cooled to room temperature, so as to obtain the fiber-reinforced concave hexagonal honeycomb core.
According to a third aspect of the present invention, there is provided a fiber-reinforced concave hexagonal honeycomb core, which is manufactured by the above-described molding method.
Generally, compared with the prior art, the above technical solution conceived by the present invention mainly has the following technical advantages:
1. compared with the prior preparation methods such as 3D printing and the like, the method can ensure more continuous distribution of fibers through a mold hot-pressing forming method, the core unit cells are well connected, the prepared fiber-reinforced concave hexagonal honeycomb sandwich structure can better exert the potential of unidirectional fiber reinforcement, and the mechanical property of the fiber-reinforced concave hexagonal honeycomb sandwich structure is further improved. Meanwhile, the concave hexagonal honeycomb sandwich structure prepared by the invention has a transverse contraction phenomenon under the compression action, has a negative Poisson's ratio effect due to the special structural deformation characteristic, and has high shear modulus, indentation resistance, fracture toughness and good sound absorption and vibration reduction capability compared with other positive Poisson's ratio honeycomb sandwich structures.
2. The structure of the concave hexagonal honeycomb sandwich structure is ingeniously realized through the alternative arrangement of the concave hexagonal columns and the two trapezoidal bodies, and the mold is simple in structure and convenient to assemble and mold, and is beneficial to quickly and effectively preparing the fiber reinforced concave honeycomb sandwich structure.
3. The clamping groove is used for accommodating the horizontal stud bolt, so that the concave hexagonal cylinder can be prevented from being staggered front and back; the corresponding upper clamping plate and the corresponding lower clamping plate are detachably connected through the vertical stud bolts, so that the trapezoidal body is prevented from being moved out in a staggered manner, the stable positioning of the concave hexagonal cylinder and the trapezoidal body is ensured, and the quality of the prepared honeycomb core is improved; in addition, the communicated rectangular grooves are adopted to accommodate the rectangular bosses of the clamping plates, so that the stability of connection between the clamping plates and the concave hexagonal columns, the trapezoidal bodies and the end clamping blocks is ensured.
4. The plate-shaped structure formed by the concave hexagonal cylinder, the trapezoidal unit and the end clamping block is made of die steel materials, so that the plate-shaped structure can bear higher-strength pressure and has stronger thermal fatigue resistance in the subsequent forming process, the deformation of a die in the forming process of the fiber reinforced resin-based prepreg can be effectively prevented, the influence of a high-temperature environment is avoided, and the quality and the stability of the concave hexagonal honeycomb sandwich structure can be improved.
5. The invention is not limited to the fiber reinforced concave honeycomb sandwich structure with specific layer number, and the fiber reinforced concave hexagonal honeycomb sandwich structure with different layer numbers can be prepared by the method, thereby increasing the diversity of the honeycomb sandwich structure.
Drawings
FIG. 1 is a schematic structural diagram of a forming mold for a fiber-reinforced concave hexagonal honeycomb core according to an embodiment of the present invention;
FIG. 2 is an exploded view of a mold for forming a fiber-reinforced concave hexagonal honeycomb core according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a forming mold for prepreg layup according to an embodiment of the invention;
FIG. 4 is a schematic diagram of a concave hexagonal cylinder in a forming mold according to an embodiment of the present invention;
FIG. 5 is a schematic view of a trapezoidal body in a forming die according to an embodiment of the invention;
FIG. 6 is a schematic view of an end clamp block in a forming die according to an embodiment of the present invention;
FIG. 7 is a front view of a fiber reinforced internal concave hexagonal honeycomb sandwich structure single layer core prepared in accordance with an embodiment of the present invention;
FIG. 8 is a perspective view of a fiber reinforced internal concave hexagonal honeycomb sandwich structure single layer core prepared in accordance with an embodiment of the present invention;
FIG. 9 is a perspective view of a fiber reinforced internal concave hexagonal honeycomb sandwich structure multi-layer core prepared in accordance with an embodiment of the present invention.
The same reference numbers will be used throughout the drawings to refer to the same or like elements or structures, wherein: 1-concave hexagonal cylinder, 2-trapezoidal body, 3-end clamping block, 4-clamping plate, 5-cover plate, 6-horizontal stud bolt and 7-vertical stud bolt.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The forming mold of the fiber reinforced concave hexagonal honeycomb core provided by the embodiment of the invention, as shown in fig. 1 and fig. 2, comprises an assembling component and a reinforcing component, wherein:
the assembly comprises a plurality of concave hexagonal columns 1, a plurality of trapezoidal units and two end clamping blocks 3, wherein: the concave hexagonal columns 1 and the trapezoidal units are arranged alternately along the transverse direction, and both sides of the outer part of each concave hexagonal column 1 are concave hexagonal columns 1; as shown in fig. 4, the cross section of the concave hexagonal cylinder 1 perpendicular to the length direction (longitudinal direction) is a concave hexagon, and a plurality of concave hexagonal cylinders 1 are arranged at intervals along the direction perpendicular to the cross section; the trapezoidal unit comprises two trapezoidal bodies 2, as shown in fig. 5, the two trapezoidal bodies 2 are in a group, are symmetrically arranged about the lower bottom surface of the trapezoidal body, and jointly form a hexagonal cylinder, the cross section of the trapezoidal body 2 perpendicular to the length direction of the trapezoidal body is an isosceles trapezoid, and the cross section of the hexagonal cylinder perpendicular to the length direction of the hexagonal cylinder is a hexagon; as shown in fig. 6, the two end clamping blocks 3 are respectively located at the left and right sides of the recessed hexagonal columns 1 at the two sides, and the shape of the gap between two adjacent recessed hexagonal columns 1 corresponds to the shape of the hexagonal column, so that the plurality of recessed hexagonal columns 1, the plurality of trapezoidal bodies 2, and the two end clamping blocks 3 together form a plate-shaped structure.
Specifically, the inclination angles of the two inclined planes of the trapezoid body 2 are respectively the same as the inclination angles of the concave inclined planes of the concave hexagonal cylinder 1, so as to ensure that the trapezoid body 2 and the concave hexagonal cylinder 1 in the same group can be mutually combined; the inclination angle of the concave inclined plane of the concave hexagonal cylinder 1 is respectively the same as that of the inclined plane of the end clamping block 3, so as to ensure that the concave hexagonal cylinder 1 and the end clamping block 3 can be mutually combined. In addition, between adjacent interior concave hexagon cylinder 1 and the trapezoidal unit, all there is the clearance between interior concave hexagon cylinder 1 and the tip clamp splice 3 in both sides to and two trapezoidal bodies 2 undersurfaces for lay the fibre reinforcing preimpregnation material when the shaping.
The reinforcement component is used for fixing the plate-shaped structure, and comprises four clamping plates 4, an upper cover plate 5, a lower cover plate 5, two horizontal stud bolts 6 and four vertical stud bolts 7, wherein: two horizontal stud bolts 6 are positioned in the rectangular clamping grooves at the front and rear ends of the plurality of concave hexagonal columns 1, and two ends of each horizontal stud bolt 6 respectively penetrate through the two end clamping blocks 3 to connect the plate-shaped structures together; the four clamping plates 4 are arranged on the upper surface and the lower surface of the plate-shaped structure in pairs respectively, and the vertical stud bolts 7 penetrate through the corresponding upper clamping plate 4 and the corresponding lower clamping plate 4 respectively to connect the upper clamping plate and the lower clamping plate; the two cover plates 5 are located on the upper plane and the lower plane of the plate-shaped structure, are located between the two adjacent clamping plates 4, and are used for covering the prepreg on the upper plane and the lower plane of the concave hexagonal cylinder 1.
Specifically, two ends of the recessed hexagonal column 1 along the length direction of the recessed hexagonal column are respectively provided with a clamping groove, the positions of the end part clamping blocks 3 close to the two ends are provided with rectangular through holes, and the through holes at the same end are communicated with the clamping grooves on the recessed hexagonal columns 1; the horizontal stud bolt 6 is placed in the clamping groove, and two ends of the horizontal stud bolt penetrate through the through hole and are used for fixing the concave hexagonal cylinder 1 and the end clamping block 3 in the transverse direction.
Rectangular grooves are respectively formed in the upper and lower surfaces, close to the end part, of the concave hexagonal cylinder 1, the same group of trapezoidal bodies 2 and the end part clamping block 3, and the rectangular grooves in the same end and the same surface are mutually communicated; and a rectangular boss is formed on one surface of the clamping plate 4 facing the plate-shaped structure, and is placed in the communicated rectangular grooves and used for connecting the concave hexagonal cylinder 1, the same group of trapezoidal bodies 2 and the end clamping block 3 together.
The position that splint 4 is close to the tip has seted up square through hole, vertical stud 7 passes two about corresponding splint 4 square through hole is used for with interior concave hexagon cylinder 1, trapezoidal body 2 with tip clamp splice 3 is fixed on the vertical direction.
Adopt above-mentioned forming die to carry out the shaping of fibre reinforcing indent hexagon honeycomb core, specifically include following step:
the method comprises the following steps: n/2 layers of fiber-reinforced prepregs, preferably fiber-reinforced resin-based prepregs, are laid on the two inclined planes and the bottom surface of the trapezoid body 2, the inner concave inclined planes of the inner concave hexagonal columns 1 and the inclined planes of the end clamping blocks 3 opposite to the adjacent inner concave hexagonal columns 1 at preset angles;
step two: symmetrically placing the same group of trapezoidal bodies 2 on which the prepreg is laid along the lower bottom surface to form a hexagonal cylinder, and then combining the end clamp blocks 3, the concave hexagonal cylinder 1 and the hexagonal cylinder on which the prepreg is laid with one another according to the sequence from left to right to form a core unit cell with n layers of fiber reinforced prepreg; sequentially assembling the rest of the concave hexagonal columns 1 and the rest of the hexagonal columns until the other end clamping blocks 3 are assembled, so that the plurality of concave hexagonal columns 1, the same group of trapezoidal bodies 2 and the two end clamping blocks 3 which are laid with the prepreg jointly form a complete plate-shaped structure, and two horizontal stud bolts 6 are utilized to transversely clamp the plate-shaped structure;
step three: the plate-shaped structure is divided into an upper surface and a lower surface, n/2 layers of prepreg are laid on the upper surface of the concave hexagonal cylinder 1, the clamping plate 4 is installed at the groove of the upper surface of the plate-shaped structure, and the cover plate 5 is covered after the prepreg is laid on the upper surface of the concave hexagonal cylinder 1;
step four: turning over the plate-shaped structure, laying n/2 layers of prepreg on the lower surface of the concave hexagonal cylinder 1, and mounting the splint 4 at the groove on the lower surface of the structure as shown in figure 3 after all the prepreg is laid; the clamping plate 4 and the plate-shaped structure are completely matched, and the four vertical stud bolts 7 are used for clamping the clamping plate 4 and the plate-shaped structure in the vertical direction;
step five: after the prepreg is laid on the lower surface of the inner concave hexagonal cylinder 1, covering the cover plate 5, so that the plate-shaped structure, the clamping plate 4 and the cover plate 5 form a combined body, and then clamping the upper surface and the lower surface of the cover plate 5 by using a rigid clamp to fasten the four peripheral edges of the combined body;
step six: and heating the combined body to 120-130 ℃, preferably 125 ℃, keeping the temperature for 1-3 hours, preferably 2 hours, solidifying and forming the combined body, cooling the combined body to room temperature, and taking the combined body down from the mold to obtain the single-layer core with the fiber-reinforced concave hexagonal honeycomb sandwich structure, as shown in figures 7 and 8.
Step seven: the prepared single-layer honeycomb cores can be further bonded by using epoxy resin glue to form a multi-layer concave hexagonal honeycomb structure core, as shown in fig. 9.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. The utility model provides a forming die of hexagonal honeycomb core is inwards sunken in fiber reinforcement which characterized in that, includes equipment subassembly and reinforcement component, wherein:
the assembling assembly comprises concave hexagonal columns (1), trapezoidal units and end clamping blocks (3), wherein the concave hexagonal columns (1) and the trapezoidal units are arranged alternately along the transverse direction, and both sides of the concave hexagonal columns (1) are arranged alternately; the trapezoid unit comprises two trapezoids (2), and the two trapezoids (2) are symmetrically arranged in the vertical direction relative to the lower bottom surface of the trapezoid unit; the two end clamping blocks (3) are respectively matched with the concave hexagonal columns (1) on the two sides, so that the plurality of concave hexagonal columns (1), the plurality of trapezoidal units and the two end clamping blocks (3) form a plate-shaped structure together; gaps are reserved between adjacent concave hexagonal columns (1) and the trapezoidal units, between concave hexagonal columns (1) on two sides and the end clamping blocks (3), and between the lower bottom surfaces of the two trapezoidal bodies (2), and the gaps are used for laying fiber reinforced prepreg; the reinforcing component is used for fixing the plate-shaped structure.
2. The forming die of the fiber-reinforced concave hexagonal honeycomb core according to claim 1, wherein the reinforcing component comprises a horizontal stud bolt (6), two ends of the concave hexagonal cylinder (1) along the length direction thereof are respectively provided with a clamping groove, the position of the end clamping block (3) close to the two ends is provided with a through hole, and the through hole and the clamping groove at the same end are communicated with each other; the horizontal stud bolts (6) are placed in the clamping grooves, and two ends of the horizontal stud bolts penetrate through the through holes, so that the concave hexagonal columns (1) and the end clamping blocks (3) are fixed in the transverse direction.
3. The forming mold of the fiber reinforced internal concave hexagonal honeycomb core according to claim 1, wherein the reinforcing component comprises a clamping plate (4), the upper and lower surfaces of the internal concave hexagonal cylinder (1), the trapezoidal unit and the end clamping block (3) near the two ends are respectively provided with a communicated rectangular groove, and one side of the clamping plate (4) facing the plate-shaped structure is provided with a rectangular boss which is arranged in the rectangular groove.
4. The mold for molding a fiber-reinforced concave hexagonal honeycomb core according to claim 3, wherein the reinforcing member comprises vertical stud bolts (7), the clamping plates (4) are provided with square through holes near the two lateral ends, and the vertical stud bolts (7) pass through the corresponding square through holes of the upper and lower clamping plates (4), thereby fixing the concave hexagonal cylinder (1), the trapezoidal unit and the end clamping block (3) in the vertical direction.
5. The forming die for the fiber reinforced internal concave hexagonal honeycomb core according to claim 1, wherein the reinforcing component comprises cover plates (5), and the two cover plates (5) are respectively positioned on the upper plane and the lower plane of the plate-shaped structure and are used for covering the prepreg on the upper surface and the lower surface of the internal concave hexagonal cylinder (1).
6. The mold for forming a fiber reinforced internally concave hexagonal honeycomb core according to claim 1, wherein the assembly member is made of a mold steel material.
7. The mold for molding a fiber-reinforced concave hexagonal honeycomb core according to any one of claims 1 to 6, wherein the inclination angles of the two inclined planes of the trapezoidal body (2) are the same as the inclination angles of the concave inclined planes of the concave hexagonal cylinder (1), and the inclination angles of the concave inclined planes of the concave hexagonal cylinder (1) are the same as the inclination angles of the inclined planes of the end clamp blocks (3).
8. A method for forming a fiber-reinforced concave hexagonal honeycomb core, which is implemented by using the forming mold according to any one of claims 1 to 7, comprising the following steps:
s1, laying fiber reinforced prepreg on two inclined planes and the bottom surface of the trapezoid body (2), the concave inclined plane of the concave hexagonal cylinder (1) and the inclined plane of the end clamping block (3) matched with the concave hexagonal cylinder (1), and then assembling a plate-shaped structure;
s2, laying fiber reinforced prepregs on the upper and lower surfaces of the inner concave hexagonal cylinder (1), and fixing the plate-shaped structure through a reinforcing component to obtain a combined body;
and S3, heating the combined body, cooling, and then taking down the forming die to obtain the fiber-reinforced concave hexagonal honeycomb core.
9. The method for forming the fiber-reinforced concave hexagonal honeycomb core according to claim 8, wherein the fiber-reinforced prepreg is a fiber-reinforced resin-based prepreg, the heating temperature is 120 ℃ to 130 ℃ in step S3, the temperature is kept for 1h to 3h, the prepreg is cured and formed, and the forming mold is taken down after the prepreg is cooled to room temperature, so that the fiber-reinforced concave hexagonal honeycomb core is obtained.
10. A fiber reinforced internal concave hexagonal honeycomb core formed by the molding method of claim 8 or 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111160853.8A CN113910636B (en) | 2021-09-30 | 2021-09-30 | Fiber-reinforced concave hexagonal honeycomb core and forming die and forming method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111160853.8A CN113910636B (en) | 2021-09-30 | 2021-09-30 | Fiber-reinforced concave hexagonal honeycomb core and forming die and forming method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113910636A true CN113910636A (en) | 2022-01-11 |
| CN113910636B CN113910636B (en) | 2022-09-27 |
Family
ID=79237406
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111160853.8A Active CN113910636B (en) | 2021-09-30 | 2021-09-30 | Fiber-reinforced concave hexagonal honeycomb core and forming die and forming method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113910636B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080075917A1 (en) * | 2004-11-03 | 2008-03-27 | Hoejung YANG | Curved Honeycomb Structure and Method for Producing the Same |
| 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 |
| US20190126572A1 (en) * | 2017-10-31 | 2019-05-02 | Airbus Operations S.L. | Modular mold and method for manufacturing a panel of fiber reinforced material |
| CN111844803A (en) * | 2020-06-29 | 2020-10-30 | 华中科技大学 | Forming die and method for fiber-reinforced X-shaped core sandwich board |
| CN112109398A (en) * | 2020-09-22 | 2020-12-22 | 南京理工大学 | Bottom protection structure containing negative Poisson ratio honeycomb material |
| CN112227187A (en) * | 2020-09-30 | 2021-01-15 | 北京工业大学 | Pier buffer stop is filled to negative poisson's ratio honeycomb of layering gradient |
| CN112277310A (en) * | 2019-12-06 | 2021-01-29 | 同济大学 | 3D printing method and application of negative Poisson ratio honeycomb type short fiber composite high-strength material |
| CN112519330A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Damping metamaterial damping plate |
| CN212860698U (en) * | 2020-07-31 | 2021-04-02 | 重庆文理学院 | Bumper reinforcing plate with excellent impact resistance and bending resistance |
-
2021
- 2021-09-30 CN CN202111160853.8A patent/CN113910636B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080075917A1 (en) * | 2004-11-03 | 2008-03-27 | Hoejung YANG | Curved Honeycomb Structure and Method for Producing the Same |
| 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 |
| US20190126572A1 (en) * | 2017-10-31 | 2019-05-02 | Airbus Operations S.L. | Modular mold and method for manufacturing a panel of fiber reinforced material |
| CN112277310A (en) * | 2019-12-06 | 2021-01-29 | 同济大学 | 3D printing method and application of negative Poisson ratio honeycomb type short fiber composite high-strength material |
| CN111844803A (en) * | 2020-06-29 | 2020-10-30 | 华中科技大学 | Forming die and method for fiber-reinforced X-shaped core sandwich board |
| CN212860698U (en) * | 2020-07-31 | 2021-04-02 | 重庆文理学院 | Bumper reinforcing plate with excellent impact resistance and bending resistance |
| CN112109398A (en) * | 2020-09-22 | 2020-12-22 | 南京理工大学 | Bottom protection structure containing negative Poisson ratio honeycomb material |
| CN112227187A (en) * | 2020-09-30 | 2021-01-15 | 北京工业大学 | Pier buffer stop is filled to negative poisson's ratio honeycomb of layering gradient |
| CN112519330A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Damping metamaterial damping plate |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113910636B (en) | 2022-09-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102343680B (en) | Mould and method for integrally forming fiber reinforced hexagonal honeycomb-structured core | |
| US8431214B2 (en) | Composite structure having reinforced core and method of making same | |
| AU2008203134B2 (en) | Composite structure having reinforced core and method of making same | |
| CN103252929B (en) | Imitating eastward diving beetle wing case plate and preparation method thereof | |
| US20100080980A1 (en) | Molding process for core-containing composites and composites formed thereby | |
| US20100196654A1 (en) | Process for producing composite laminate structures and composite laminate structures formed thereby | |
| CN107891631A (en) | A kind of composite pilotaxitic texture and its laying method | |
| CN112265347A (en) | Structural bearing-ablation heat-proof integrated composite material and preparation method thereof | |
| CN112677362B (en) | Preforming body for forming grid reinforced foam sandwich composite material and forming method thereof | |
| CN113910636B (en) | Fiber-reinforced concave hexagonal honeycomb core and forming die and forming method thereof | |
| CN111844803B (en) | Forming die and method for fiber-reinforced X-shaped core sandwich board | |
| CN109572075B (en) | Sandwich structure of fiber tape toughening honeycomb core | |
| CN116176001A (en) | Continuous fiber reinforced thermoplastic composite material honeycomb sandwich structure, preparation device and preparation method | |
| CN115991014A (en) | Carbon fiber microstructure material and preparation method thereof | |
| CN112318895B (en) | Spatial light high-rigidity porous grid carbon fiber honeycomb, and preparation method and application thereof | |
| CN113500798A (en) | Forming method of rigidity-variable sandwich structure of thermoplastic composite material | |
| US7208063B2 (en) | Double walled structural reinforcement | |
| CN112810185A (en) | Preparation device and preparation method of honeycomb core material | |
| CN114654761B (en) | Z-splicing preparation method of corrugated sandwich board | |
| CN114274549B (en) | Preparation facilities of fibre reinforced composite material honeycomb core | |
| CN211000263U (en) | Polymer substrate composite material supporting structure | |
| CN100402278C (en) | Composite section bar of fiber, pure titanium and gold foil, method for producing the same and solidifying mould thereof | |
| CN217531534U (en) | Assembled composite material forming tool | |
| CN114055825B (en) | Preparation method of composite material curved honeycomb | |
| CN214774508U (en) | Honeycomb structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240126 Address after: Building 2, Innovation and Entrepreneurship Square, Science and Technology Innovation City, High tech Industrial Development Zone, Harbin City, Heilongjiang Province, 150023 (No. 719, Science and Technology First Street) A205-14 Patentee after: Harbin Deye Hangyu New Material Technology Co.,Ltd. Country or region after: China Address before: 430074 Hubei Province, Wuhan city Hongshan District Luoyu Road No. 1037 Patentee before: HUAZHONG University OF SCIENCE AND TECHNOLOGY Country or region before: China |
|
| TR01 | Transfer of patent right |