CN112706426A - Forming tool for carbon fiber composite undercarriage support - Google Patents
Forming tool for carbon fiber composite undercarriage support Download PDFInfo
- Publication number
- CN112706426A CN112706426A CN202110117745.6A CN202110117745A CN112706426A CN 112706426 A CN112706426 A CN 112706426A CN 202110117745 A CN202110117745 A CN 202110117745A CN 112706426 A CN112706426 A CN 112706426A
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- CN
- China
- Prior art keywords
- tank body
- forming tool
- carbon fiber
- landing gear
- fiber composite
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- 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.)
- Pending
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- 239000002131 composite material Substances 0.000 title claims abstract description 33
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 22
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 22
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 22
- 238000010438 heat treatment Methods 0.000 claims abstract description 21
- 238000004321 preservation Methods 0.000 claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 10
- 239000012774 insulation material Substances 0.000 claims description 18
- 239000002184 metal Substances 0.000 claims description 4
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 2
- 238000007493 shaping process Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 3
- 239000011347 resin Substances 0.000 description 10
- 229920005989 resin Polymers 0.000 description 10
- 239000011810 insulating material Substances 0.000 description 6
- 238000000465 moulding Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012546 transfer Methods 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
- B29C70/342—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 isostatic pressure
-
- 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
- B29C33/02—Moulds or cores; Details thereof or accessories therefor with incorporated heating or cooling means
-
- 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
- B29C33/34—Moulds or cores; Details thereof or accessories therefor movable, e.g. to or from the moulding station
-
- 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
- B29C33/02—Moulds or cores; Details thereof or accessories therefor with incorporated heating or cooling means
- B29C2033/023—Thermal insulation of moulds or mould parts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a forming tool for a carbon fiber composite landing gear strut, which comprises an upper tank body, a lower tank body, a telescopic rod, a base, an articulated piece, a mold frame and a core mold, wherein the upper tank body is provided with a plurality of upper tank bodies; the upper tank body and the lower tank body are connected with an articulated piece, the upper tank body and the lower tank body are respectively provided with a die carrier and a core die in a corresponding mode, the upper end of a telescopic rod is connected to the inside of the upper tank body, the lower end of the telescopic rod extends to the inner side of the lower tank body, a fan and an air inlet device are arranged on the surface of a base, the fan is located on one side of the air inlet device, a heating assembly is laid on the periphery of the die carrier, a cooling assembly is fixedly installed below the heating assembly, a heat preservation frame is movably arranged above the heating assembly, and. Has the advantages that: the method is not easy to demould and convenient to popularize, further solves the problems of laying, pressurizing, curing and demoulding of the composite material support of the landing gear, and realizes the forming and manufacturing of the composite material product with the double-curvature variable cross section, multiple layers and large-thickness special structure.
Description
Technical Field
The invention belongs to the technical field of carbon fiber equipment, and particularly relates to a forming tool for a carbon fiber composite landing gear support.
Background
Carbon fiber composite materials have been widely used in military technical fields such as aerospace and weaponry because of their characteristics of light weight, high strength, high modulus, corrosion resistance, etc., and most of the conventional high-performance composite materials adopt autoclave molding technology in order to meet the strength requirement and porosity requirement. The autoclave molding has the advantages of capability of manufacturing various complex components, excellent part quality, high molding precision and uniform thickness of a finished part.
However, the main landing gear strut structure is designed by a double-curvature variable cross section which is bent laterally and wide in transverse direction and narrow in transverse direction, and the main landing gear strut is formed by laying carbon fiber prepreg, and more than 50 layers are laid at the thickest part, and the conventional composite material forming tool can be used for products with small structural curvature, few layers and small forming pressure, but cannot meet the requirements of the structure with complex shape, more layers and large curing pressure.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides a forming tool for a carbon fiber composite landing gear support, which is not easy to demould and convenient to popularize, further solves the problems of stacking, pressurizing curing and demoulding of the landing gear composite support, and realizes the forming and manufacturing of a composite product with a special structure, namely a double-curvature variable cross section, multiple layers and large thickness.
(II) technical scheme
In order to realize the advantages of good sealing performance, convenience and rapidness, the invention adopts the following specific technical scheme:
a forming tool for a carbon fiber composite landing gear strut comprises an upper tank body, a lower tank body, a telescopic rod, a base, an articulated piece, a mold frame and a core mold; an articulated piece is connected between the upper tank body and the lower tank body, a mold frame and a core mold are respectively and correspondingly arranged on the upper tank body and the lower tank body, the upper end of the telescopic rod is connected inside the upper tank body, the lower end of the telescopic rod extends to the inner side of the lower tank body, a fan and an air inlet device are arranged on the surface of the base, the fan is positioned on one side of the air inlet device, and the mold frame is provided with a heating assembly, a cooling assembly, a heat preservation frame and a lighting device; the heating assembly is laid on the periphery of the die carrier, the cooling assembly is fixedly arranged below the heating assembly, the heat preservation frame is movably arranged above the heating assembly, and the lighting device is arranged at the bottom of the die carrier.
Furthermore, a die cavity is arranged in the core die, and bearing seats are movably arranged at two ends of the die cavity.
Furthermore, the die carrier and the core die can be made of silicon rubber.
Further, the heat preservation frame is made of one of an organic heat insulation material, an inorganic heat insulation material, a metal heat insulation material, a loose heat insulation material, a plate-shaped heat insulation material and an integral heat insulation material.
Furthermore, the telescopic rods are hydraulic telescopic rods, and the number of the telescopic rods is at least one group.
Furthermore, still fixedly on the upper die body be provided with a plurality of lugs, and a plurality of lugs evenly distributed are on two sides of upper die body.
Furthermore, the bottom of the base is provided with a plurality of groups of fixing piles, and movable guide wheels can be installed on the peripheries of the fixing piles.
(III) advantageous effects
Compared with the prior art, the invention provides a carbon fiber composite landing gear support post forming tool, which has the following beneficial effects:
1. the invention has reasonable structural design, is not easy to demould and convenient to popularize, further solves the problems of the laying, the pressure curing and the demould of the landing gear composite material strut, and realizes the molding and manufacturing of the composite material product with the special structure of double curvature variable cross section, multiple layers and large thickness.
2. The telescopic rods are hydraulic telescopic rods, and the number of the telescopic rods is at least one group. Thereby realizing the opening and closing of the upper tank body and the lower tank body.
3. The heat preservation effect of the whole mechanism is enhanced by arranging the heat preservation frame to be one of an organic heat insulation material, an inorganic heat insulation material, a metal heat insulation material, a loose heat insulation material, a plate-shaped heat insulation material and an integral heat insulation material.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a carbon fiber composite landing gear strut forming tool according to an embodiment of the invention;
FIG. 2 is a rear view of FIG. 1;
fig. 3 is a schematic structural diagram of a mold frame 6 of a carbon fiber composite landing gear strut forming tool according to an embodiment of the invention;
fig. 4 is a top view of a mold frame 6 of a carbon fiber composite landing gear strut forming tool according to an embodiment of the invention;
fig. 5 is a schematic structural diagram of a core mold 7 of a tool for forming a landing gear strut made of carbon fiber composite according to an embodiment of the invention.
In the figure:
the device comprises an upper tank body 1, a lower tank body 2, an expansion rod 3, a base 4, a hinge piece 5, a mold frame 6, a core mold 7, a fan 41, an air inlet device 42, a heating component 61, a cooling component 62, a heat preservation frame 63, a lighting device 64, a mold cavity 71 and a bearing seat 72
Detailed Description
For further explanation of the various embodiments, the drawings which form a part of the disclosure and which are incorporated in and constitute a part of this specification, illustrate embodiments and, together with the description, serve to explain the principles of operation of the embodiments, and to enable others of ordinary skill in the art to understand the various embodiments and advantages of the invention, and, by reference to these figures, reference is made to the accompanying drawings, which are not to scale and wherein like reference numerals generally refer to like elements.
According to the embodiment of the invention, a forming tool for a carbon fiber composite landing gear strut is provided.
Referring to the drawings and the detailed description, the invention is further described, and as shown in fig. 1 to 5, a forming tool for a carbon fiber composite landing gear strut according to an embodiment of the invention comprises an upper tank body 1, a lower tank body 2, a telescopic rod 3, a base 4, a hinge part 5, a mold frame 6 and a core mold 7; an articulated piece 5 is connected between the upper tank body 1 and the lower tank body 2, a mold frame 6 and a core mold 7 are respectively and correspondingly arranged on the upper tank body 1 and the lower tank body 2, the upper end of the telescopic rod 3 is connected inside the upper tank body 1, the lower end of the telescopic rod 3 extends to the inner side of the lower tank body 2, a fan 41 and an air inlet device 42 are arranged on the surface of the base 4, the fan 41 is positioned on one side of the air inlet device 42, and the mold frame 6 is provided with a heating component 61, a cooling component 62, a heat preservation frame 63 and a lighting device 64; the heating assembly 61 is laid on the periphery of the mold frame 6, the cooling assembly 62 is fixedly arranged below the heating assembly 61, the heat preservation frame 63 is movably arranged above the heating assembly 61, and the lighting device 64 is arranged at the bottom of the mold frame 6.
The invention has reasonable structural design, is not easy to demould and convenient to popularize, further solves the problems of the laying, the pressure curing and the demould of the landing gear composite material strut, and realizes the molding and manufacturing of the composite material product with the special structure of double curvature variable cross section, multiple layers and large thickness.
In one embodiment, a cavity 71 is provided inside the core mold 7, and bearing seats 72 are movably installed at both ends of the cavity 71.
In one embodiment, the material of the mold frame 6 and the core mold 7 may be silicon rubber. The rear end of the die cavity 7 is completely sealed, and the sealing effect of the rear end of the die cavity 7 is better.
In one embodiment, the heat-insulating frame 63 is one of an organic heat-insulating material, an inorganic heat-insulating material, a metal-based heat-insulating material, a loose heat-insulating material, a plate-like heat-insulating material, and an integral heat-insulating material.
In one embodiment, the telescopic rods 3 are hydraulic telescopic rods, and the number of the telescopic rods is at least one group. Thereby realizing the opening and closing of the upper tank body and the lower tank body.
In one embodiment, a plurality of lifting lugs are further fixedly arranged on the upper die body 1, and the plurality of lifting lugs are uniformly distributed on two side surfaces of the upper die body 1. Thereby facilitating the movement of the whole device and carrying through a crane or a crane.
In one embodiment, the bottom of the base 4 is provided with a plurality of groups of fixing piles, and the periphery of the fixing piles can be provided with movable guide wheels. Thereby facilitating movement of the entire device.
In the processing process of the invention, the prepreg lamination is placed in a hot-pressing tank, and the lamination is pressurized by using the internal air pressure. Because the air pressure exists in all directions, the air pressure can be used for pressurizing parts with uneven surfaces. The pressure and temperature can be controlled to a predetermined variation curve, which is generally called a curing period. The purpose of the pressure during curing is to densify the material, remove the voids between the layers, and squeeze excess resin out of the fibers, taking out air bubbles. In general, when prepreg laminates are cured by heating, the viscosity of the resin initially decreases due to an increase in temperature due to an exothermic reaction, and at this time, the autoclave pressure can squeeze out excess resin to completely join the layers. Thereafter, the resin gradually reacts and the viscosity increases, so that the resin does not flow any more, and therefore the timing of pressurization must be performed when the resin viscosity is low. In terms of temperature, the resin is an exothermic reaction as previously described, and must be heated initially to promote the reaction, and the external temperature must not be too high to avoid the internal temperature being too high due to heat build-up, resulting in material being removed. The curing temperature must therefore take into account both the heat of reaction of the resin and the thickness of the laminate which affects the heat transfer, and different materials and part thicknesses will result in different curing cycles at the beginning of the curing cycle, usually requiring a vacuum to be applied to the laminate to remove air from the voids between the layers, and the effect of the vacuum will fail when the viscosity of the resin begins to flow, since the passage of air is blocked by the resin flow and can no longer be evacuated via the vacuum, so that the vacuum can be applied and terminated.
The working principle is as follows: the upper tank body 1 and the lower tank body 2 are respectively and correspondingly provided with a mold frame 6 and a core mold 7 through connecting an articulated piece 5 between the tank body 1 and the lower tank body 2, the upper end of an expansion rod 3 is connected inside the upper tank body 1, the lower end of the expansion rod 3 extends to the inner side of the lower tank body 2, the surface of the base 4 is provided with a fan 41 and an air inlet device 42, the fan 41 is positioned on one side of the air inlet device 42, and the mold frame 6 is provided with a heating component 61, a cooling component 62, a heat preservation frame 63 and a lighting device 64; the heating assembly 61 is laid on the periphery of the mold frame 6, the cooling assembly 62 is fixedly arranged below the heating assembly 61, the heat preservation frame 63 is movably arranged above the heating assembly 61, and the lighting device 64 is arranged at the bottom of the mold frame 6. The method is not easy to demould and convenient to popularize, further solves the problems of laying, pressurizing, curing and demoulding of the composite material support of the landing gear, and realizes the forming and manufacturing of the composite material product with the double-curvature variable cross section, multiple layers and large-thickness special structure.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "disposed," "connected," "secured," "screwed" and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; the terms may be directly connected or indirectly connected through an intermediate, and may be communication between two elements or interaction relationship between two elements, unless otherwise specifically limited, and the specific meaning of the terms in the present invention will be understood by those skilled in the art according to specific situations.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (7)
1. The utility model provides a shaping frock of carbon-fibre composite undercarriage pillar which characterized in that: the device comprises an upper tank body (1), a lower tank body (2), an expansion rod (3), a base (4), an articulated piece (5), a mold frame (6) and a core mold (7); an articulated piece (5) is connected between the upper tank body (1) and the lower tank body (2), a mold base (6) and a core mold (7) are respectively and correspondingly arranged on the upper tank body (1) and the lower tank body (2), the upper end of the telescopic rod (3) is connected inside the upper tank body (1), the lower end of the telescopic rod (3) extends to the inner side of the lower tank body (2), a fan (41) and an air inlet device (42) are arranged on the surface of the base (4), the fan (41) is positioned on one side of the air inlet device (42), and the mold base (6) is provided with a heating assembly (61), a cooling assembly (62), a heat preservation frame (63) and a lighting device (64); the heating assembly (61) is laid on the periphery of the die carrier (6), the cooling assembly (62) is fixedly arranged below the heating assembly (61), the heat preservation frame (63) is movably arranged above the heating assembly (61), and the illuminating device (64) is arranged at the bottom of the die carrier (6).
2. The forming tool for the landing gear strut made of the carbon fiber composite material as claimed in claim 1, wherein the forming tool comprises: a die cavity (71) is arranged in the core die (7), and bearing seats (72) are movably mounted at two ends of the die cavity (71).
3. The forming tool for the landing gear strut made of the carbon fiber composite material as claimed in claim 1, wherein the forming tool comprises: the die frame (6) and the core die (7) can be made of silicon rubber.
4. The forming tool for the landing gear strut made of the carbon fiber composite material as claimed in claim 1, wherein the forming tool comprises: the heat preservation frame (63) is made of one of an organic heat insulation material, an inorganic heat insulation material, a metal heat insulation material, a loose heat insulation material, a plate-shaped heat insulation material and an integral heat insulation material.
5. The forming tool for the landing gear strut made of the carbon fiber composite material as claimed in claim 1, wherein the forming tool comprises: the telescopic rods (3) are hydraulic telescopic rods, and the number of the telescopic rods is at least one group.
6. The forming tool for the landing gear strut made of the carbon fiber composite material as claimed in claim 1, wherein the forming tool comprises: the upper die body (1) is fixedly provided with a plurality of lifting lugs, and the plurality of lifting lugs are uniformly distributed on two side faces of the upper die body (1).
7. The forming tool for the landing gear strut made of the carbon fiber composite material as claimed in claim 1, wherein the forming tool comprises: the bottom of the base (4) is provided with a plurality of groups of fixing piles, and movable guide wheels can be installed on the peripheries of the fixing piles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110117745.6A CN112706426A (en) | 2021-01-28 | 2021-01-28 | Forming tool for carbon fiber composite undercarriage support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110117745.6A CN112706426A (en) | 2021-01-28 | 2021-01-28 | Forming tool for carbon fiber composite undercarriage support |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112706426A true CN112706426A (en) | 2021-04-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110117745.6A Pending CN112706426A (en) | 2021-01-28 | 2021-01-28 | Forming tool for carbon fiber composite undercarriage support |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112706426A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228193A (en) * | 2021-12-17 | 2022-03-25 | 江西洪都航空工业集团有限责任公司 | Forming die for preparing variable-thickness closed-angle slender I-shaped composite material part |
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| CN202727169U (en) * | 2012-06-08 | 2013-02-13 | 滁州精益模具设备制造有限公司 | Upper die opening device of door body foaming die |
| CN206128623U (en) * | 2016-10-20 | 2017-04-26 | 山东博远重工有限公司 | Template revenue and expenditure device with heat dissipation function |
| CN207882040U (en) * | 2018-03-12 | 2018-09-18 | 泾县恒运机械铸造有限公司 | A kind of precoated sand sampling machine of easy mold release |
| CN108582815A (en) * | 2018-05-09 | 2018-09-28 | 江苏亨睿碳纤维科技有限公司 | Mold carries the carbon fibre composite autoclave molding method of heating system |
| CN109910328A (en) * | 2019-03-21 | 2019-06-21 | 四川省新万兴碳纤维复合材料有限公司 | A kind of forming frock and its moulding process of carbon fibre composite undercarriage leg |
| CN210700396U (en) * | 2019-07-09 | 2020-06-09 | 武汉威仕包装材料有限公司 | Horizontal sanding dispersion machine |
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2021
- 2021-01-28 CN CN202110117745.6A patent/CN112706426A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202727169U (en) * | 2012-06-08 | 2013-02-13 | 滁州精益模具设备制造有限公司 | Upper die opening device of door body foaming die |
| CN206128623U (en) * | 2016-10-20 | 2017-04-26 | 山东博远重工有限公司 | Template revenue and expenditure device with heat dissipation function |
| CN207882040U (en) * | 2018-03-12 | 2018-09-18 | 泾县恒运机械铸造有限公司 | A kind of precoated sand sampling machine of easy mold release |
| CN108582815A (en) * | 2018-05-09 | 2018-09-28 | 江苏亨睿碳纤维科技有限公司 | Mold carries the carbon fibre composite autoclave molding method of heating system |
| CN109910328A (en) * | 2019-03-21 | 2019-06-21 | 四川省新万兴碳纤维复合材料有限公司 | A kind of forming frock and its moulding process of carbon fibre composite undercarriage leg |
| CN210700396U (en) * | 2019-07-09 | 2020-06-09 | 武汉威仕包装材料有限公司 | Horizontal sanding dispersion machine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114228193A (en) * | 2021-12-17 | 2022-03-25 | 江西洪都航空工业集团有限责任公司 | Forming die for preparing variable-thickness closed-angle slender I-shaped composite material part |
| CN114228193B (en) * | 2021-12-17 | 2023-12-05 | 江西洪都航空工业集团有限责任公司 | Forming die for preparing variable-thickness closed-angle slender I-shaped composite material workpiece |
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Application publication date: 20210427 |