CN111976228A - Composite material space truss structure and preparation method based on curing forming die - Google Patents
Composite material space truss structure and preparation method based on curing forming die Download PDFInfo
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- CN111976228A CN111976228A CN202010787182.7A CN202010787182A CN111976228A CN 111976228 A CN111976228 A CN 111976228A CN 202010787182 A CN202010787182 A CN 202010787182A CN 111976228 A CN111976228 A CN 111976228A
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- 239000002131 composite material Substances 0.000 title claims abstract description 27
- 238000002360 preparation method Methods 0.000 title claims abstract description 9
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 32
- 239000004917 carbon fiber Substances 0.000 claims abstract description 32
- 238000004804 winding Methods 0.000 claims abstract description 25
- 239000003921 oil Substances 0.000 claims description 25
- 238000010438 heat treatment Methods 0.000 claims description 24
- 239000000047 product Substances 0.000 claims description 21
- 239000010720 hydraulic oil Substances 0.000 claims description 15
- 239000003292 glue Substances 0.000 claims description 8
- 238000005520 cutting process Methods 0.000 claims description 6
- 230000002457 bidirectional effect Effects 0.000 claims description 4
- 238000007598 dipping method Methods 0.000 claims description 4
- 238000007790 scraping Methods 0.000 claims description 4
- 239000011265 semifinished product Substances 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 238000009940 knitting Methods 0.000 claims description 2
- 239000002184 metal Substances 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000000835 fiber Substances 0.000 description 10
- 238000009941 weaving Methods 0.000 description 8
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 7
- 238000000465 moulding Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 238000007711 solidification Methods 0.000 description 4
- 230000008023 solidification Effects 0.000 description 4
- 238000009825 accumulation Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005452 bending Methods 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
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/78—Moulding material on one side only of the preformed part
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a non-planar shape
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2250/00—Layers arrangement
- B32B2250/20—All layers being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a composite material space truss structure and a preparation method based on a curing forming die, relates to the technical field of space stations, and solves the technical problems that in the prior art, a plurality of round tubes of the space station truss structure are in a multi-round tube form, are formed by winding with equal tension, are single in structural form, are limited by the specification of a winding machine in structural length and size, are usually connected by short pipes and short rods through metal adapters, increase the damage risk of composite material bonding and opening, and reduce effective load. The technical characteristics of the square pipe comprise a three-layer structure square pipe, wherein the inner layer and the outer layer are made of 12K carbon fibers, and the middle layer is made of 50K large-tow carbon fibers. The truss structure has the beneficial effects of avoiding the trouble in splicing and assembling short pipes and short rods, reducing the risk and weight of connecting ends, further improving the effective load and improving the truss foundation for a large-scale space structure.
Description
Technical Field
The invention relates to the technical field of space stations, in particular to a composite material space truss structure and a preparation method based on a curing forming mold.
Background
The truss structure is used as a base structure of the space phase station, transmits and bears load, and provides an installation base for effective loads of various components and parts and the like. At present, the many tubular forms of space station truss structure, through the equal tension winding shaping, structural style is single, and structure length size receives the specification restriction of coiler, often realizes that the nozzle stub is continuous to connect through metal adapter, increases combined material bonding trompil and destroys the risk, reduces payload.
Disclosure of Invention
The invention provides a composite material space truss structure and a preparation method thereof, and aims to solve the technical problems that in the prior art, a truss structure of a space station is in a multi-round-tube form, is formed by equal-tension winding, is single in structural form, is limited by the specification of a winding machine in structural length and size, is usually connected by short pipes and short rods through metal adapters, increases the risk of damage of composite material bonding and opening, and reduces effective load.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a composite space truss structure comprising:
the wall thickness is three-layer structure square pipe, wherein, the inner layer and the outer layer adopt 12K carbon fiber, and the middle layer adopts 50K large tow carbon fiber.
Furthermore, the weaving direction of the 12K carbon fibers of the inner layer forms an angle of +/-45 degrees with the central axis of the square pipe, the 50K large tow carbon fibers of the middle layer form an angle of 0 degree with the central axis of the square pipe, and the winding direction of the 12K carbon fibers of the outer layer forms an angle of 90 degrees with the central axis of the square pipe.
The preparation method of the composite material space truss structure comprises the following steps:
s1, weaving 12K carbon fibers on a high-precision core mold by a three-dimensional weaving machine, guiding the core mold into a first preforming mold through a reciprocating tractor, and forming the inner layer with thick wall;
the S2 and 50K carbon fibers sequentially pass through a glue dipping tank, a glue scraping tank and a guide frame by a creel, and enter a preforming mold II together with the 12K carbon fibers in the S1 to form the thickness of the middle layer;
s3, winding the 12K carbon fiber on the outer layer of the S2 product by a bidirectional winding machine to form the outermost layer with thick wall;
s4, dragging the product to a split type telescopic curing forming die by a reciprocating tractor to be heated and cured to form a composite material space truss structure;
and S5, cutting by a cutting machine according to a fixed length, transferring into a semi-finished product area, and performing circular production.
Further, scalable solidification moulding mould of split type includes:
the hydraulic stretching device fixing frame is arranged above the ground through a fixing support;
the hydraulic stretching devices are fixedly arranged on the periphery of the hydraulic stretching device fixing frame;
the oil way heating template is fixedly arranged at the movable end of the hydraulic stretching device;
the split outer core mold is fixedly connected with the oil way heating template;
the inner core die is arranged inside the split outer core die and is fixed by the core die fixing device;
the hydraulic stretching device drives the oil way heating template and the split outer core mold to move inwards, so that a product between the split outer core mold and the split inner core mold is heated and fixed to form a composite material space truss structure.
Furthermore, the hydraulic stretching device is a hydraulic oil cylinder.
Furthermore, the fixed frame is a hollow rectangular frame structure, and the cylinder body of the hydraulic oil cylinder is fixed on four side surfaces of the rectangular frame.
Furthermore, a plurality of oil way processing holes are formed in the oil way heating template, and the oil way heating template is arranged inside the rectangular frame body and fixedly connected with the end part of the piston rod of the hydraulic oil cylinder.
Furthermore, the cross section of the split outer core mold is a plate with a trapezoidal structure, the short sides of the four split outer core molds face inwards, and the split outer core mold is fixedly connected with the oil way heating template.
Furthermore, the inner core mold is a solid rectangular bar, and the four split outer core molds are driven by the hydraulic oil cylinder to open and close the inner core mold, so that the temperature rise, pressurization and solidification of the product are completed.
The invention has the following beneficial effects:
the composite material space truss structure and the preparation method based on the curing and forming die are combined with three forming processes of weaving (first step), pultrusion (second step) and winding (third step), so that the limitation of the size of the space truss structure by the specification of a winding machine can be broken through, the complex splicing and assembling of short pipe and short rod can be avoided, the risk and the weight of a connecting end can be reduced, the effective load can be further improved, and the truss foundation can be improved for a large space structure; through setting up the scalable solidification forming die of split type, can solve: for a pipe with a square or rectangular cross section, the tension of a winding machine is not controllable, particularly, the fiber is difficult to cling to pultruded fiber after being wound by a fillet, so that the winding cross section is larger than the cross section of a cavity of a curing molding die, and the technical problem of rubbing and accumulation can also occur when the fiber enters the curing molding die.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
FIG. 1 is a schematic structural view of a composite space truss structure of the present invention;
FIG. 2 is a cross-sectional structural schematic view of a composite space truss structure of the present invention;
FIG. 3 is a schematic view of a method of making a composite space truss structure of the present invention;
fig. 4 is a schematic structural view of a split retractable curing mold according to the present invention.
The reference numerals in the figures denote:
1. a three-dimensional knitting machine; 2. a bidirectional winding machine; 3. a reciprocating tractor; 4. a split type telescopic curing forming die; 401. a hydraulic stretching device; 402. the hydraulic stretching device fixes the frame; 403. heating the template by an oil way; 404. a split outer core mold; 405. an inner core mold; 406. fixing and supporting; 407. a composite space truss structure; 4071. an inner layer; 4072. an intermediate layer; 4073. an outer layer; 5. a high-precision core mold; 6. performing a first mold; 7. performing a second mold; 8. a cutter; 9. a core mold fixing device; 10. a glue scraping groove; 11. a glue dipping tank; 12. a creel.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 and 2, the composite space truss structure includes:
the wall thickness is a square pipe with a three-layer structure, wherein 12K carbon fibers are adopted as the inner layer 4071 and the outer layer 4073, and 50K large tow carbon fibers are adopted as the middle layer 4072.
The angle between the 12K carbon fiber weaving angle of the inner layer 4071 and the central axis of the square pipe is +/-45 degrees, the angle between the 50K large tow carbon fiber of the middle layer 4072 and the central axis of the square pipe is 0 degree, and the angle between the 12K carbon fiber winding angle of the outer layer 4073 and the central axis of the square pipe is 90 degrees.
The working principle is as follows: firstly, the truss structure mainly bears axial tension and compression, namely the angle between the 50K large tow carbon fiber of the middle layer 4072 and the central axis of the square pipe is 0 degree, so that the main bearing effect is achieved, and the inner layer 4071 and the outer layer 4073 fibers play a role in protecting the middle layer 4072; secondly, from the lay-up perspective, the lay-up direction of the composite material is: 0 °, 90 ° and ± 45 ° are quasi-isotropic plies, so that the truss structure is reinforced in all directions. In terms of process, the fibers of the middle layer 4072 are formed in an axial movement mode and form 0 degree with the central axis by aligning, and the fibers of the outer layer 4073 form 90 degrees with the central axis by combining the winding process of the outer layer 4073, so that the bending resistance of the truss is improved; considering that the inner layer 4071 is also subjected to traction force, the weaving angle is not too large, and in order to take the strength in the +/-45-degree direction into consideration, the fibers of the inner layer 4071 are woven to +/-45 degrees;
three kinds of forming technology of inner layer 4071, pultrusion intermediate level 4072 and outer 4073 of winding are woven in the combination, make combined material space truss structure, can break through the restriction that space truss structure size received the coiler specification, have and avoid the nozzle stub short-rod concatenation to assemble loaded down with trivial details, reduce the risk and the weight of connecting the end, further improve payload, improve the effect on truss basis for large-scale space structure.
The preparation method of the composite material space truss structure comprises the following steps:
firstly, weaving 12K carbon fibers on a high-precision core mold 5 by a three-dimensional weaving machine 1, guiding the carbon fibers into a first preforming mold 6 through a reciprocating tractor 3, and forming an inner layer 4071 with a thick wall;
secondly, the 50K carbon fibers sequentially pass through a glue dipping groove 11, a glue scraping groove 10 and a guide frame from a creel 12, and enter a pre-forming mold II 7 together with the 12K carbon fibers in the first step to form a middle layer 4072 with the wall thickness;
thirdly, winding 12K carbon fibers on the outer layer of the product obtained in the second step by using a bidirectional winding machine 2, and forming the outer layer to be 4073 thick;
fourthly, the reciprocating tractor 3 draws the product into a split type telescopic curing forming die 4 to be heated and cured to form a composite material space truss structure 407;
and fifthly, cutting by a cutting machine 8 according to a fixed length, transferring to a semi-finished product area, and performing circular production.
Scalable solidification moulding mould 4 of split type includes:
a hydraulic stretching device fixing frame 402, the hydraulic stretching device fixing frame 402 is installed above the ground through a fixing support 406;
the hydraulic stretching devices 401 are fixedly arranged on the periphery of a hydraulic stretching device fixing frame 402;
the oil path heating template 403 is fixedly arranged at the movable end of the hydraulic stretching device 401;
a split outer mandrel 404, wherein the split outer mandrel 404 is fixedly connected with the oil path heating template 403;
an inner core mold 405, the inner core mold 405 being disposed inside the split outer core mold 404 and fixed by the core mold fixing device 9;
the hydraulic stretching device 401 drives the oil path heating template 403 and the split outer core mold 404 to move inwards, so that the product between the split outer core mold 404 and the split inner core mold 405 is heated and fixed to form a composite space truss structure 407.
The hydraulic stretching device 401 is a hydraulic cylinder.
In order to support the truss with a rectangular structure, the fixed frame 402 is a hollow rectangular frame structure, and the cylinder bodies of the hydraulic cylinders are respectively fixed on four side surfaces of the rectangular frame.
The oil path heating template 403 is provided with a plurality of oil path processing holes, and the oil path heating template 403 is arranged inside the rectangular frame body and is fixedly connected with the end part of the piston rod of the hydraulic oil cylinder.
The cross section of the split outer mandrel 404 is a plate with a trapezoidal structure, the short sides of the four split outer mandrels 404 face inward, and the split outer mandrel 404 is fixedly connected with the oil passage heating die plate 403. The oil path heating die plate 403 and the split outer core die 404 are long plates, and in order to enable the outer core die 404 to apply force to the product uniformly, a plurality of hydraulic oil cylinders are arranged, so that the purpose of applying force to the product uniformly is achieved, and the quality of the product is ensured.
The inner core mold 405 is a solid rectangular strip, and the four split outer core molds 404 are driven by a hydraulic oil cylinder to open and close the inner core mold 405, so that the temperature rise and pressure curing of the product between the split outer core mold 404 and the inner core mold 405 is completed.
The working principle is as follows: production equipment of the composite material space truss structure is purchased from the outside, but the forming dies of the existing pulling and winding production line are all of fixed cross sections, and only circular tube winding can be basically realized due to the constant winding tension. For a pipe with a square or rectangular section, the tension of a winding machine is not controllable, particularly, the fiber is difficult to cling to pultruded fiber after being wound by a fillet, so that the winding section is larger than the section of a cavity of a curing molding die, and rubbing and accumulation can also occur when the fiber enters the curing molding die;
in order to solve the problems, a split type telescopic curing forming die 4 is arranged, a hydraulic oil cylinder drives a split outer core die 404 to contract and stretch, and an oil way heating die plate 403 is used for heating a product to cure the product;
when the product passes through the first three steps and before entering the split type telescopic curing forming die 4, the hydraulic oil cylinder is in an extended state (namely, the piston of the hydraulic oil cylinder is contracted to separate the four split outer core dies 404); when the product completely enters the split type telescopic curing and forming die 4, the hydraulic oil cylinder is in a contraction state (namely, the piston of the hydraulic oil cylinder drives the four split outer core dies 404 to move forwards, so that the four split outer core dies 404 are in a joint state), and the split outer core dies 404 heat, pressurize and cure the product; the four split outer core molds 404 are driven by the hydraulic oil cylinder to retract, the product is pulled out by the reciprocating tractor 3, and the processes are circularly and continuously produced.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (9)
1. A composite space truss structure, comprising:
the square pipe with the wall thickness of a three-layer structure is characterized in that the inner layer (4071) and the outer layer (4073) adopt 12K carbon fibers, and the middle layer (4072) adopts 50K large tow carbon fibers.
2. The composite space truss structure of claim 1 wherein the 12K carbon fibers of the inner layer (4071) are woven at an angle of ± 45 ° to the central axis of the square tubing, the 50K large tow carbon fibers of the middle layer (4072) are woven at an angle of 0 ° to the central axis of the square tubing, and the 12K carbon fibers of the outer layer (4073) are wound at an angle of 90 ° to the central axis of the square tubing.
3. A preparation method of a composite material space truss structure is characterized by comprising the following steps:
firstly, a three-dimensional knitting machine (1) weaves 12K carbon fibers on a high-precision core mold (5), and the carbon fibers are guided into a first preforming mold (6) through a reciprocating tractor (3) to form an inner layer (4071) with thick wall;
secondly, the 50K carbon fibers sequentially pass through a glue dipping tank (11), a glue scraping tank (10) and a guide frame from a creel (12), and enter a pre-forming mold II (7) together with the 12K carbon fibers in the first step, and the thickness of a forming intermediate layer (1072) is thick;
thirdly, winding 12K carbon fibers on the outer layer of the product obtained in the second step by using a bidirectional winding machine (2), and forming the outermost layer (4073) with the wall thickness;
fourthly, the reciprocating tractor (3) pulls the product into a split type telescopic curing forming die (4) for heating and curing to form a composite material space truss structure (407);
and fifthly, cutting by a cutting machine (8) according to a fixed length, transferring to a semi-finished product area, and circularly producing.
4. A split telescopic curing mould (4) according to claim 3, comprising:
a hydraulic stretching device fixed frame (402), the hydraulic stretching device fixed frame (402) is installed above the ground through a fixed support (406);
the hydraulic stretching devices (401), a plurality of hydraulic stretching devices (401) are fixedly arranged around a hydraulic stretching device fixing frame (402);
the oil path heating template (403), the oil path heating template (403) is fixedly arranged at the movable end of the hydraulic stretching device (401);
the split outer core mold (404), the split outer core mold (404) is fixedly connected with the oil way heating template (403);
an inner core mold (405), the inner core mold (405) being disposed inside the split outer core mold (404) and fixed by a core mold fixing means (9);
the hydraulic stretching device (401) drives the oil way heating template (403) and the split outer core mold (404) to move inwards, so that a product between the split outer core mold (404) and the inner core mold (405) is heated and fixed to form a composite material space truss structure (407).
5. The split expandable curing mold (4) according to claim 4, wherein the hydraulic stretching device (401) is a hydraulic cylinder.
6. The split type retractable curing mold (4) as claimed in claim 5, wherein the fixed frame (402) is a hollow rectangular frame structure, and the cylinder body of the hydraulic oil cylinder is fixed on four sides of the rectangular frame.
7. The split type telescopic curing and forming die (4) as claimed in claim 6, wherein a plurality of oil way processing holes are formed in the oil way heating die plate (403), and the oil way heating die plate (403) is arranged inside the rectangular frame body and fixedly connected with the end part of a piston rod of the hydraulic oil cylinder.
8. The split retractable curing mold (4) according to claim 5, wherein the cross section of the split outer core mold (404) is a plate with a trapezoidal structure, the short sides of the four split outer core molds (404) face inward, and the split outer core molds (404) are fixedly connected with the oil passage heating mold plate (403).
9. The split type retractable curing mold (4) as claimed in claim 5, wherein the inner core mold (405) is a solid rectangular bar, and the four split outer core molds (404) are driven by a hydraulic cylinder to open and close the inner core mold (405) to complete the temperature-rising and pressure-applying curing of the product.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010787182.7A CN111976228A (en) | 2020-08-07 | 2020-08-07 | Composite material space truss structure and preparation method based on curing forming die |
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| CN202010787182.7A CN111976228A (en) | 2020-08-07 | 2020-08-07 | Composite material space truss structure and preparation method based on curing forming die |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113954386A (en) * | 2021-10-14 | 2022-01-21 | 亨弗劳恩(江苏)复合材料研发有限公司 | Composite material part and preparation device and method thereof |
| CN114889155A (en) * | 2022-03-15 | 2022-08-12 | 云路复合材料(上海)有限公司 | Bending-torsion-resistant composite material beam local reinforcing composite forming method and production line |
| CN115742295A (en) * | 2022-10-28 | 2023-03-07 | 南京航空航天大学 | Aerospace truss additive manufacturing device |
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| CN113954386A (en) * | 2021-10-14 | 2022-01-21 | 亨弗劳恩(江苏)复合材料研发有限公司 | Composite material part and preparation device and method thereof |
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