CN111098515B - Integrated carbon fiber composite grid structure and manufacturing method - Google Patents
Integrated carbon fiber composite grid structure and manufacturing method Download PDFInfo
- Publication number
- CN111098515B CN111098515B CN201911296602.5A CN201911296602A CN111098515B CN 111098515 B CN111098515 B CN 111098515B CN 201911296602 A CN201911296602 A CN 201911296602A CN 111098515 B CN111098515 B CN 111098515B
- Authority
- CN
- China
- Prior art keywords
- grid
- carbon fiber
- layer
- belt
- paved
- 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.)
- Active
Links
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 85
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 85
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 85
- 239000002131 composite material Substances 0.000 title claims abstract description 24
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 16
- 239000000835 fiber Substances 0.000 claims abstract description 48
- 238000004804 winding Methods 0.000 claims abstract description 7
- 230000003137 locomotive effect Effects 0.000 claims description 20
- 239000004744 fabric Substances 0.000 claims description 16
- 238000000034 method Methods 0.000 claims description 9
- 238000003825 pressing Methods 0.000 claims description 5
- 238000007711 solidification Methods 0.000 claims description 5
- 230000008023 solidification Effects 0.000 claims description 5
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 238000000465 moulding Methods 0.000 claims description 3
- 230000001502 supplementing effect Effects 0.000 abstract 1
- 238000002360 preparation method Methods 0.000 description 3
- 230000003014 reinforcing effect Effects 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 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
- 239000002184 metal Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3064—Trains
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses an integrated carbon fiber composite grid structure and a manufacturing method thereof. The ratio of the side length of the rectangular grid to the diameter of the circular section of the whole grid structure or the side length of the short side of the rectangular section is 1/8-1/500; the first fiber band at the grid node, the second fiber band and the third fiber band which are parallel to each other are vertically laid to form a gap, and the gap is supplemented by adopting a supplementing fiber band; the ratio of the height of the grid ribs to the short side length of the rectangular grid is 1/5-1/20; the central axis direction of the grid plane and the central axis direction of different structural members are 45 degrees or 0 degrees, and the skin is laid on one side surface or two side surfaces of the grid, and the thickness of the skin is not more than 1/5 of the thickness of the grid rib. The invention adopts the continuous winding forming of the grooved or slotless mould, and the manufacturing can realize full automation; compared with the laminated board with the same size, the laminated board has good rigidity, high strength and light weight. The structure is suitable for an integrated aircraft fuselage, a carrier rocket, a missile shell and a high-speed railway car body.
Description
Technical Field
The invention relates to a carbon fiber composite material grid structure and a manufacturing method thereof, in particular to an integrated carbon fiber composite material grid structure and a manufacturing method thereof for an integrated aircraft fuselage, a carrier rocket, a missile shell, a high-speed railway car body and the like.
Background
Carbon fiber composite materials have long been used in aircraft fuselage, missiles and high-speed railway car bodies, and are traditionally used in large aircraft, missiles and high-speed railway car body structures to add various reinforcing ribs to laminated plates, and the bearing main body of the structure is the reinforcing ribs and the laminated plates, and most of the reinforcing ribs are glued or riveted, are not manufactured in an integrated auxiliary layer, and are not sufficient in integrity. With the increasing demand for reduction in importance, the drawbacks of the existing structures are increasingly revealed with increasing safety and reliability. Therefore, providing an integrated structure with good rigidity and light weight has very important application value, and is a constantly pursuing safety target. The composite material integrated grid structure is a grid rib structure. The grid composite material structure is developed from a metal grid structure, and the grid structure has the outstanding advantages of higher rigidity/mass ratio and strength/mass ratio, so that the grid structure is widely applied to the aerospace fields such as various airplane fuselages, carrier rockets, missile shells, high-speed vehicle bodies and the like and the high-speed carrier field.
Disclosure of Invention
In order to overcome the problems in the background art, the invention aims to provide an integrated carbon fiber composite grid structure and a manufacturing method thereof, wherein the integrated carbon fiber composite grid structure adopts a quadrilateral grid structure, continuous winding forming of the grid structure is realized through machining, and the manufacturing process can be fully automated.
The technical scheme adopted by the invention is as follows:
1. An integrated carbon fiber composite grid structure:
According to different structural members and different geometric dimensions, rectangular grids with different dimensions are manufactured, and the ratio of the side length of each rectangular grid to the diameter of the circular section of the whole grid structure or the side length of the short side of each rectangular section is 1/8-1/500; forming a gap after the first fiber belt, the second fiber belt and the third fiber belt which are parallel to each other at the grid node are vertically laid, and carrying out layer missing on the fibers between the two nodes, wherein the fibers at the grid node are as high as the fibers at the non-node by adopting the flat-filling fiber belt; the ratio of the height of the grid ribs to the short side length of the rectangular grid is 1/5-1/20 according to structural rigidity and strength calculation; the central axis direction c-c of the grid plane forms 45 degrees or 0 degrees with the central axis direction a-a of different structural members, the skin is laid on one side face or two side faces of the integrated carbon fiber composite material grid, and the thickness of the skin layer is not more than 1/5 of the thickness of the grid ribs.
The taper ratio of the cross section surface of the grid rib of the rectangular grids with different sizes is 1:10-1:20.
The rectangular grid is a square grid or a rectangular grid.
2. The preparation method of the integrated carbon fiber composite material grid structure adopts a grooved mold forming method:
1) According to different structural members and different geometric dimensions, rectangular grids with different sizes are designed;
2) Manufacturing a die with a rectangular or cylindrical cross section, wherein a groove is formed in the die, the opening of the groove is wide, the lower bottom of the groove is narrow, and the taper of the cross section of the groove is 1: between 10 and 1 and 20, the groove bottom is transited by a round angle, a release agent is sprayed in the groove of the die, bearings are respectively arranged at two ends of a rotating shaft of the die, and a rotating system is formed by a shaft coupling of the rotating shaft through a motor; the carbon fiber belt is wound in the groove along one direction of the groove, the carbon fiber belt is wound after being tensioned by a cloth belt by prestress, the carbon fiber belt is wound on a disc rack rotating along a disc rack rotating shaft in a whole roll, the laying direction of the carbon fiber belt is adjusted by a cloth belt device, and the cloth belt device rotates along the cloth belt device rotating shaft; the carbon fiber belt is arranged on an auxiliary belt trolley which can move left and right on the screw rod; when the mould rotates, the auxiliary belt trolley moves along the screw rod simultaneously, so that the grooves are always aligned with the carbon fiber belts in a straight line, after the 1 st layer of carbon fiber belts are wound in one direction groove, the 1 st layer of carbon fiber belts are completely paved after the flat fiber belts are paved in the other direction groove, after the 2 nd layer of carbon fiber belts are paved in the other direction groove opposite to the 1 st layer, the 2 nd layer of carbon fiber belts are completely paved after the flat fiber belts are paved in the other opposite direction groove, the next layer of carbon fiber belts are sequentially paved in each groove in a winding mode, until the set thickness is reached, and the required grid structure can be obtained after curing forming.
The mould is manufactured by adopting a plurality of arc moulds, and finally is combined into an integral mould.
3. The other preparation method of the integrated carbon fiber composite material grid structure adopts a slotless mold forming method:
1) According to different structural members and different geometric dimensions, rectangular grids with different sizes are designed;
2) A skin with set thickness is manufactured on a die, a carbon fiber belt is laid at a set grid position by an automatic auxiliary belt machine at the outer side of the manufactured skin, and the whole body is solidified and formed after the set thickness is reached; the carbon fiber belt is laid on the skin by a belt laying locomotive arranged on the annular frame by using a pressing force and a pretension force; the carbon fiber belt is laid on the skin by a cloth tape device, a compression wheel and a tensioner on the tape-laying locomotive and is compressed, and the carbon fiber belt is cut off at a set place; the tape application locomotive can automatically rotate along the limiting shaft, so that the carbon fiber tape is applied to the skin along any angle, when the skin moves along the axial direction of the central shaft, the tape application locomotive moves along the annular frame at the same time, and walks back and forth until the tape is applied to a set thickness, the tape application is stopped, and the required grid structural member can be obtained after solidification; the tape applying locomotive is limited to move on a fixed rail on a circular frame through a limiting shaft, and the circular frame is fixed on the machine base; the carbon fiber strip is cut according to the required length on assisting the area machine, when laying the 1 st layer, lay the 1 st layer of net rib of a direction earlier and be continuous carbon fiber strip, the 1 st layer of net rib of another direction is mending the flat fiber strip, after the 1 st layer of all net ribs is laid, lay the 2 nd layer net rib, the 2 nd layer of net rib that the 1 st layer was continuous carbon fiber strip direction at this moment lays mending the flat fiber strip, the 1 st layer is the 2 nd layer of net rib of mending the flat fiber strip lays continuous carbon fiber strip, lay the 3 rd layer in proper order until the net rib height of settlement.
The fiber belts are prepreg carbon fiber belts which are rolled into discs with customized widths.
The invention has the beneficial effects that:
The invention adopts a quadrilateral grid structure, realizes continuous winding forming of the grid structure by machining, and can realize full automation of the manufacturing process. The continuous fiber winding is applied to the grid structure molding of the composite material, so that the manufacturing cost is reduced, the performance stability of the product is improved, and the mass production is easy to realize; compared with the laminated board with the same size, the laminated board has good rigidity, high strength and light weight. The structure is suitable for an integrated aircraft fuselage, a carrier rocket, a missile shell and a high-speed railway car body.
Drawings
Fig. 1 is a structural diagram of the present invention.
Fig. 2 is a D-D cross-sectional view of fig. 1.
Fig. 3 is a schematic view of a circular section slotted die forming of the present invention.
Fig. 4 is a right side view of fig. 3.
Fig. 5 is a schematic diagram of a rectangular section die-less forming of the present invention.
Fig. 6 is a partially expanded view of fig. 3 i.
Fig. 7 is a sectional view A-A of fig. 6.
Fig. 8 is a schematic representation of the fiber tape laying at two nodes.
In the figure: 1. the device comprises a rotating shaft, 2, a bearing, 3, a rectangular grid, 4, a groove, 5, a coupler, 6, a motor, 7, a carbon fiber belt, 8, a cloth belt device, 9, an auxiliary belt trolley, 10, a disc frame, 11, a screw rod, 12, an arc-shaped die, 13, a cloth belt device rotating shaft, 14, a disc frame rotating shaft, 15, a die, 16, a frame, 17, an auxiliary belt machine, 18, a limiting shaft, 19, wheels, 20, a belt applying locomotive, 21, a circular frame, 22, a tensioner, 23, a pinch roller, 24, a skin, 25, a flat fiber belt, 26, a first fiber belt, 27, a second fiber belt, 28, a third fiber belt, 29, a grid structure, 30, grid ribs, 31 and grid nodes.
Detailed Description
The invention is further described below with reference to the drawings and examples.
As shown in fig. 1,2 and 8, according to the invention, rectangular grids 3 with different sizes are manufactured according to different structural members and different geometric dimensions, and the ratio of the side length of the rectangular grid 3 to the diameter of the circular section of the whole grid structure or the side length of the short side of the rectangular section is 1/8-1/500; forming a gap after the first fiber belt 26, the second fiber belt 27 and the third fiber belt 28 which are parallel to each other at the grid node 31 are vertically laid, and carrying out fiber layer missing between the two nodes, and adopting the flat-filling fiber belt 25 to fill in the gap, so that the thickness of the fibers at the grid node 31 is as high as that of the fibers at the non-node; the ratio of the height of the grid ribs 30 to the short side length of the rectangular grid is 1/5-1/20, which is calculated and determined according to the structural rigidity and strength; the central axis direction c-c of the plane of the grid 3 forms 45 degrees or 0 degrees with the central axis direction a-a of different structural members, the skin 24 is laid on one side surface or two side surfaces of the integrated carbon fiber composite material grid, and the thickness of the skin layer is not more than 1/5 of the thickness of the grid ribs.
The taper ratio of two end faces of the cross section of the grid rib 30 of the rectangular grid 3 with different sizes is 1:10-1:20.
The rectangular grid 3 is a square grid or a rectangular grid.
1. The preparation method of the integrated carbon fiber composite material grid structure adopts a grooved mold forming method (shown in figures 3,4 and 7):
1) According to different structural members and different geometric dimensions, rectangular grids 3 with different sizes are designed;
2) Manufacturing a die 15 with a rectangular or cylindrical cross section, wherein a groove 4 is formed in the die 15, the opening of the groove 4 is wide, the lower bottom of the groove is narrow, and the taper of the cross section of the groove is 1: between 10 and 1:20, the groove bottom is transited by a round angle, a release agent is sprayed in the groove 4 of the die 15, the two ends of the rotating shaft 1 of the die 15 are respectively provided with a bearing 2, and the coupling 5 of the rotating shaft 1 forms a rotating system through a motor 6; the carbon fiber belt 7 is wound in the groove along one direction of the groove 4, the carbon fiber belt 7 is wound after being tensioned by a cloth tape device 8 by prestress, the carbon fiber belt 7 is wound on a disc rack 10 rotating along a disc rack rotating shaft 14 in a whole roll, the laying direction of the carbon fiber belt 7 is adjusted by the cloth tape device 8, and the cloth tape device 8 rotates along a cloth tape device rotating shaft 13; the carbon fiber belt 7 is mounted on an auxiliary belt trolley 9 which can move left and right on a screw rod 11; when the mould 15 rotates, the auxiliary belt trolley 9 moves along the screw rod 11 at the same time, so that the grooves 4 are always aligned with the carbon fiber belts 7 in a straight line, after the 1 st layer of carbon fiber belts 7 are wound in one direction groove 4, the 1 st layer of carbon fiber belts are completely laid after the flat-filling fiber belts 25 are laid in the other direction groove 4, after the 2 nd layer of carbon fiber belts 7 are wound in the opposite direction groove 4, the flat-filling fiber belts 25 are completely laid in the opposite direction groove 4, the next layer of carbon fiber belts 7 are sequentially laid in each groove in a back-and-forth winding mode until the set thickness is reached, and the required grid structure 29 can be obtained after solidification molding.
The mold 15 is manufactured using a plurality of arc-shaped molds 12, and is finally assembled into a unitary mold.
2. Another method for preparing the integrated carbon fiber composite grid structure adopts a slotless mold forming method (as shown in fig. 5):
1) According to different structural members and different geometric dimensions, rectangular grids 3 with different sizes are designed;
2) A skin with set thickness is manufactured on a mould, a carbon fiber belt 7 is laid at a set grid position by adopting an automatic auxiliary belt machine 17 at the outer side of the manufactured skin 24, and the whole body is solidified and formed after the set thickness is reached; the carbon fiber belt 7 is laid on the skin 24 by a belt application locomotive 20 arranged on a circular frame 21 with a pressing force and a pretension force; the tape application locomotive 20 moves in a 360-degree range along the annular frame 21 through the wheels 19, the carbon fiber tape 7 is laid on the skin 24 through the cloth tape device 17, the pressing wheel 23 and the tensioner 22 on the tape application locomotive 20, and is pressed, and the carbon fiber tape 7 is cut off at a set place; the tape application locomotive 20 can autorotate along the limiting shaft 18, so that the carbon fiber tape 7 is laid on the skin 24 along any angle, when the skin 24 moves along the central shaft axially, the tape application locomotive 20 moves along the annular frame 21 at the same time, and the tape application locomotive is stopped after the tape application locomotive moves back and forth until the tape is laid to a set thickness, and the required grid structural member can be obtained after solidification; the tape application locomotive 20 is limited to run on a fixed track on a circular frame 21 through a limiting shaft 18, and the circular frame 21 is fixed on the stand 16; the carbon fiber strip 7 can be cut on the auxiliary strip machine 17 according to the required length, when the 1 st layer is paved, the 1 st layer of the grid rib 30 in one direction is paved as the continuous carbon fiber strip 7, the 1 st layer of the grid rib 30 in the other direction is paved as the flat fiber strip 25, after the 1 st layer of all the grid ribs 30 is paved, the 2 nd layer of the grid rib 30 is paved, at the moment, the 1 st layer is paved as the 2 nd layer of the grid rib 30 in the direction of the continuous carbon fiber strip 7, the 2 nd layer of the grid rib 30 of the 1 st layer is paved as the flat fiber strip 25, the continuous carbon fiber strip 7 is paved, and the 3 rd layer is paved in sequence until the set grid rib 30 is high.
The carbon fiber tape 7 is a prepreg carbon fiber tape wound into a disc shape with a predetermined width.
The grids shown in fig. 6 and 7 are specific structures, as the embodiment, the grid of the mold is obliquely placed at an angle of 45 degrees with the axial center line of the mold, the width of the bottom surface of the grid is 56.71mm, the width of the upper surface of the grid is 54.27mm, the grid is centrally placed, the inclination angles of two side surfaces of ribs are 4.98 degrees, the groove depth is 14mm, the groove bottom is subjected to fillet treatment, the whole grid is a circular section, and the outer diameter is 500mm.
Claims (7)
1. The utility model provides an integrated carbon fiber composite grid structure which characterized in that: according to different structural members and different geometric dimensions, rectangular grids (3) with different dimensions are manufactured, and the ratio of the side length of each rectangular grid (3) to the diameter of the circular section of the whole grid structure or the side length of the short side of each rectangular section is 1/8-1/500; forming a gap after the first fiber belt (26) at the grid node (31) and the second fiber belt (27) and the third fiber belt (28) which are parallel to each other are vertically laid, and carrying out fiber layer missing between the two nodes, and adopting a flat fiber belt (25) to make the fiber thickness at the grid node (31) as high as the fiber thickness at the non-node; the ratio of the height of the grid ribs (30) to the short side length of the rectangular grid is 1/5-1/20, which is calculated and determined according to the structural rigidity and the strength; the central axis direction c-c of the plane of the grid (3) forms 45 degrees or 0 degrees with the central axis direction a-a of different structural members, a skin (24) is laid on one side surface or two side surfaces of the integrated carbon fiber composite material grid, and the thickness of the skin layer is not more than 1/5 of the thickness of the grid rib.
2. The integrated carbon fiber composite lattice structure of claim 1, wherein: the cross section taper ratio of the grid ribs (30) of the rectangular grids (3) with different sizes is 1:10-1:20.
3. The integrated carbon fiber composite lattice structure according to claim 1 or 2, wherein: the rectangular grid (3) is a square grid or a rectangular grid.
4. The method for preparing the integrated carbon fiber composite grid structure as claimed in claim 1 or 2, wherein a grooved mold forming method is adopted:
1) According to different structural members and different geometric dimensions, designing rectangular grids (3) with different dimensions;
2) Manufacturing a die (15) with a rectangular or cylindrical cross section, wherein a groove (4) is formed in the die (15), the opening of the groove (4) is wide, the bottom of the groove is narrow, and the taper of the cross section of the groove is 1: between 10 and 1:20, the groove bottom is transited by a round angle, a release agent is sprayed in the groove (4) of the die (15), the two ends of the rotating shaft (1) of the die (15) are respectively provided with a bearing (2), and the coupler (5) of the rotating shaft (1) forms a rotating system through a motor (6); the carbon fiber belt (7) is wound in the groove along one direction of the groove (4), the carbon fiber belt (7) is wound after being tensioned by a cloth tape device (8) by prestress, the carbon fiber belt (7) is wound on a disc rack (10) rotating along a disc rack rotating shaft (14) in a whole roll, the laying direction of the carbon fiber belt (7) is adjusted by the cloth tape device (8), and the cloth tape device (8) rotates along a cloth tape device rotating shaft (13); the carbon fiber belt (7) is arranged on an auxiliary belt trolley (9) which can move left and right on the screw rod (11); when the die (15) rotates, the auxiliary belt trolley (9) moves along the screw rod (11) simultaneously, so that the grooves (4) are always aligned with the carbon fiber belts (7) in a straight line, after the 1 st layer of carbon fiber belts (7) are wound in one direction groove (4), the complete 1 st layer of carbon fiber belts are paved after the flat fiber belts (25) are paved in the other direction groove (4), after the 2 nd layer of carbon fiber belts (7) are paved in the opposite direction groove (4) in the next layer, the complete 2 nd layer of carbon fiber belts are paved after the flat fiber belts (25) are paved in the opposite direction groove (4), the carbon fiber belts (7) are sequentially paved in each groove in a back-and-forth winding mode until the set thickness is reached, and the required grid structure (29) can be obtained after solidification and molding.
5. The method of manufacturing according to claim 4, wherein: the die (15) is manufactured by adopting a plurality of arc-shaped dies (12), and finally is combined into a whole die.
6. The method for preparing the integrated carbon fiber composite grid structure as claimed in claim 1 or 2, wherein a slotless mold forming method is adopted:
1) According to different structural members and different geometric dimensions, designing rectangular grids (3) with different dimensions;
2) A skin with set thickness is manufactured on a die, a carbon fiber belt (7) is laid at a set grid position by adopting an auxiliary belt machine (17) at the outer side of the manufactured skin (24), and the whole body is solidified and formed after the set thickness is reached; the carbon fiber belt (7) is laid on the skin (24) by a belt application locomotive (20) arranged on the annular frame (21) with pressing force and pretension force; the tape application locomotive (20) moves in a 360-degree range along the annular frame (21) through the wheels (19), the carbon fiber tape (7) is laid on the skin (24) through the auxiliary tape machine (17), the pressing wheel (23) and the tensioner (22) on the tape application locomotive (20), and is pressed, and the carbon fiber tape (7) is cut off at a set place; the tape application locomotive (20) can automatically rotate along the limiting shaft (18) to enable the carbon fiber tape (7) to be laid on the skin (24) along any angle, when the skin (24) moves along the central shaft axially, the tape application locomotive (20) moves along the annular frame (21) at the same time, and moves back and forth until the tape is laid to a set thickness, the tape laying is stopped, and the required grid structural member can be obtained after solidification; the tape application locomotive (20) is limited to run on a fixed track on a circular frame (21) through a limiting shaft (18), and the circular frame (21) is fixed on the machine base (16); the carbon fiber strip (7) is cut on the auxiliary strip machine (17) according to the required length, when the 1 st layer is paved, the 1 st layer of the grid rib (30) in one direction is paved to be the continuous carbon fiber strip (7), the 1 st layer of the grid rib (30) in the other direction is paved to be the flat fiber strip (25), after the 1 st layer of all the grid ribs (30) is paved, the 2 nd layer of the grid rib (30) is paved, at the moment, the 1 st layer is paved to be the flat fiber strip (25) for the 2 nd layer of the grid rib (30) in the direction of the continuous carbon fiber strip (7), the 2 nd layer of the grid rib (30) for the flat fiber strip (25) is paved to be the continuous carbon fiber strip (7) for the 2 nd layer of the grid rib (30) for the flat fiber strip (25), and the 3 rd layer is paved in sequence until the set grid rib (30) is high.
7. The method of manufacturing according to claim 6, wherein: the fiber belts are prepreg carbon fiber belts which are rolled into discs with customized widths.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911296602.5A CN111098515B (en) | 2019-12-16 | 2019-12-16 | Integrated carbon fiber composite grid structure and manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911296602.5A CN111098515B (en) | 2019-12-16 | 2019-12-16 | Integrated carbon fiber composite grid structure and manufacturing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111098515A CN111098515A (en) | 2020-05-05 |
| CN111098515B true CN111098515B (en) | 2024-05-31 |
Family
ID=70423622
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911296602.5A Active CN111098515B (en) | 2019-12-16 | 2019-12-16 | Integrated carbon fiber composite grid structure and manufacturing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111098515B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113002008B (en) * | 2021-04-30 | 2022-02-22 | 浙江大学 | Composite material grid structure without carbon fiber accumulation at grid intersection and manufacturing method |
| CN114290706A (en) * | 2021-12-08 | 2022-04-08 | 上海瓴荣材料科技有限公司 | Layering method for aerospace composite material grid structure |
| CN116533413A (en) * | 2023-05-10 | 2023-08-04 | 扬州利宏碳纤维材料有限公司 | Carbon fiber composite material solidification equipment |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102152502A (en) * | 2010-12-07 | 2011-08-17 | 沈阳航空航天大学 | Preparation method of high-intensity composite material grid structure |
| CN103935053A (en) * | 2014-04-08 | 2014-07-23 | 东南大学 | Forming mold and forming method of fiber reinforced composite material grid rib |
| CN110561782A (en) * | 2019-08-26 | 2019-12-13 | 长春长光宇航复合材料有限公司 | Composite material secondary curing molding method based on internal grid rib structure and application |
| CN211843281U (en) * | 2019-12-16 | 2020-11-03 | 浙江大学 | Integrated carbon fiber composite material grid structure |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2936488B1 (en) * | 2008-09-30 | 2011-04-15 | Airbus France | AIRCRAFT FUSELAGE TRUNK IN COMPOSITE MATERIAL WITH INTERNAL CONSTANT PROFILE |
| WO2011143666A2 (en) * | 2010-05-14 | 2011-11-17 | Sigma-Tek, Llc | Covered composite lattice support structures and methods associated therewith |
| US8765042B2 (en) * | 2010-06-11 | 2014-07-01 | Airbus Operations Gmbh | Fuselage section of an aircraft and method for the production of the fuselage section |
-
2019
- 2019-12-16 CN CN201911296602.5A patent/CN111098515B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102152502A (en) * | 2010-12-07 | 2011-08-17 | 沈阳航空航天大学 | Preparation method of high-intensity composite material grid structure |
| CN103935053A (en) * | 2014-04-08 | 2014-07-23 | 东南大学 | Forming mold and forming method of fiber reinforced composite material grid rib |
| CN110561782A (en) * | 2019-08-26 | 2019-12-13 | 长春长光宇航复合材料有限公司 | Composite material secondary curing molding method based on internal grid rib structure and application |
| CN211843281U (en) * | 2019-12-16 | 2020-11-03 | 浙江大学 | Integrated carbon fiber composite material grid structure |
Non-Patent Citations (1)
| Title |
|---|
| 带蒙皮复合材料圆柱网格结构的轴压稳定性分析;廖英强;刘勇琼;;材料工程;20110720(07);第1-5页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111098515A (en) | 2020-05-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111098515B (en) | Integrated carbon fiber composite grid structure and manufacturing method | |
| EP1798428B1 (en) | Braided composite part | |
| US4574029A (en) | Apparatus for forming concave tape wrapped composite structures | |
| US3490983A (en) | Fiber reinforced structures and methods of making the same | |
| EP2314445B1 (en) | A method for manufacturing a composite body and a composite body manufacturing arrangement | |
| US4401495A (en) | Method of winding composite panels | |
| WO2013083500A1 (en) | Wheel comprising a wheel spider, and suitable production method | |
| DE102012210043A1 (en) | Method and device for producing a lightweight structure and lightweight structure | |
| JP2004507379A (en) | Crushable structural member with deformed special shape and method of making the structural member | |
| EP2684680B1 (en) | Method and device for the manufacture of pre-forms made of fibre-reinforced plastic | |
| US4463044A (en) | Composite panel of varied thickness | |
| GB2520079A (en) | Wind turbine blades | |
| DE102015224388B4 (en) | Fibre-reinforced plastic element for vehicles, method of manufacturing the same and vehicle | |
| CN115008783B (en) | Fiber composite component, apparatus and method of manufacturing a fiber composite component | |
| CN211843281U (en) | Integrated carbon fiber composite material grid structure | |
| CN108081636A (en) | The production method of composite material spring | |
| CN106426976B (en) | The manufacturing method of compound material flexible hinge | |
| DE102010053635B4 (en) | Process for producing a fiber composite product | |
| US3687795A (en) | Tubular laminate | |
| DE102013007609A1 (en) | Process for producing a fiber-reinforced plastic component | |
| WO2019173745A1 (en) | Systems and methods for forming a winding structure | |
| EP2990187B1 (en) | Method and apparatus for forming a composite material blank | |
| DE3814344C2 (en) | ||
| EP3360671B1 (en) | Rotatable pre-mould for a preform | |
| CN115008133B (en) | Composite material tension-compression bar and manufacturing method thereof |
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 |