CN116945427A - Carbon fiber missile wing compression molding die - Google Patents
Carbon fiber missile wing compression molding die Download PDFInfo
- Publication number
- CN116945427A CN116945427A CN202311214388.0A CN202311214388A CN116945427A CN 116945427 A CN116945427 A CN 116945427A CN 202311214388 A CN202311214388 A CN 202311214388A CN 116945427 A CN116945427 A CN 116945427A
- Authority
- CN
- China
- Prior art keywords
- die body
- missile wing
- die
- holes
- carbon fiber
- 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.)
- Pending
Links
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 29
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 29
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 29
- 238000000748 compression moulding Methods 0.000 title claims abstract description 22
- 238000005553 drilling Methods 0.000 claims abstract description 25
- 238000003825 pressing Methods 0.000 claims description 16
- 229910000831 Steel Inorganic materials 0.000 claims description 13
- 239000010959 steel Substances 0.000 claims description 13
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 210000001503 joint Anatomy 0.000 abstract 1
- 238000000465 moulding Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 9
- 239000002131 composite material Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000011074 autoclave method Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000009499 grossing Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 239000000725 suspension 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/30—Mounting, exchanging or centering
- B29C33/303—Mounting, exchanging or centering centering mould parts or halves, e.g. during mounting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B47/00—Constructional features of components specially designed for boring or drilling machines; Accessories therefor
- B23B47/28—Drill jigs for workpieces
-
- 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
- B29C33/0055—Moulds or cores; Details thereof or accessories therefor with incorporated overflow cavities
-
- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The application provides a carbon fiber missile wing compression molding die which comprises an upper die body and a lower die body, wherein the upper die body and the lower die body are in butt joint through a plurality of groups of guide posts and guide sleeves, the guide posts are arranged at the top of the lower die body, the guide sleeves are arranged at the bottom of the upper die body, an upper missile wing contour groove is formed in the center of the bottom of the upper die body, and upper gumming grooves are formed in two sides of the upper missile wing contour groove. The forming die disclosed by the application has the beneficial effects that the problem of the manufacturing cost of a single complete set of the drilling die in the prior art is solved, the problem of the smooth whole surface quality of a product and the problem of complex positioning operation are solved, and the forming die has the advantages of simplicity in positioning and good operability, the drilling die is simple in structure, can be mounted on a die body and used together with the die body to save the manufacturing cost, and the like, meets the requirements of a product hole site, meets the position precision of a lining in the product hole, and meets the requirements of the quality and weight of a carbon fiber missile wing.
Description
Technical Field
The application relates to a carbon fiber missile wing compression molding die, and belongs to the field of composite unmanned aerial vehicle molding.
Background
In the prior art, when the product is molded, a molding method of a vacuum bag autoclave is mostly adopted, a die is mostly adopted as a film pasting surface by a male die or a female die, and if the product has a hole site requirement, a set of drilling dies are additionally required to realize the hole site precision requirement and the position requirement of a hole lining. The forming mode can meet the quality requirements of thickness, weight, hole position precision position requirements, surface film pasting surface smoothness and the like of products.
In addition, in practical application, the vacuum bag autoclave method can only ensure the surface quality of a single-side film pasting surface during molding, and if the product is a carbon fiber missile wing, the whole outer surface is required to be smooth, and the cost for separately manufacturing a set of drilling mould to meet the precision requirement is higher, the mould assembly is more complicated, the mould is often positioned by a positioning pin during mould assembly, and the mould and the product extrusion are often difficult to position during mould assembly.
Disclosure of Invention
Aiming at the defects existing in the prior art, the application aims to provide a carbon fiber missile wing compression molding die.
In order to achieve the above object, the present application is realized by the following technical scheme:
the utility model provides a carbon fiber missile wing compression molding die, includes upper die body and lower die body, the upper die body with dock together through a plurality of guide pillar and guide pin bushing between the lower die body, the guide pillar sets up the top of lower die body, the guide pin bushing sets up the bottom of upper die body, upper portion missile wing contour groove has been seted up to upper portion missile wing contour groove in upper die body bottom center department, upper portion missile wing contour groove both sides all are equipped with upper portion gumming groove, lower die body top center department seted up with upper portion missile wing contour groove matched with lower part missile wing contour groove, upper portion missile wing contour groove with pour the missile wing work piece between lower part missile wing contour groove both, lower part missile wing contour groove both sides all are equipped with lower part gumming groove, upper portion missile wing contour groove with be equipped with the missile wing drill jig between the lower part missile wing contour groove.
Further, the upper die body and the lower die body are fixedly connected through a plurality of groups of fixing screws and fixing nuts, the upper die body is provided with screws, the lower die body is provided with nuts, and holes matched with the fixing screws and the fixing nuts are respectively formed in the upper die body and the lower die body.
Further, the missile wing drill jig comprises a pressing plate, two drill jig bottom plates and two positioning blocks, the pressing plate and the drill jig bottom plates are respectively located on two sides of the top of the lower die body, a plurality of through holes matched with fixing screws are formed in the pressing plate, the missile wing workpiece is pressed and held by the pressing plate, the two drill jig bottom plates are symmetrically arranged on the other side of the top of the lower die body, knurled high-head screws and two positioning bolts are arranged on one side of the drill jig bottom plates, the two positioning bolts are symmetrically arranged on two sides of the knurled high-head screws, connecting holes matched with the knurled high-head screws and the positioning bolts are formed in the lower die body, and two bushing holes, two screw holes and two cylindrical pin holes are formed in the other side of the drill jig bottom plates.
Further, two bushing locating pins matched with the bushing holes, two connecting screws matched with the screw holes and two internally threaded cylindrical pins matched with the cylindrical pin holes are symmetrically arranged in the middle of the locating block.
Further, a plurality of jackscrew holes are formed in the upper die body, a die opening groove is formed in the upper die body, and a limit groove matched with the fixing nut is formed in the lower die body.
Further, a plurality of drilling grooves are formed in the lower missile wing contour groove, two bushing holes correspond to the drilling grooves, and steel gaskets are embedded in the drilling grooves.
Further, the upper die body and the lower die body are both provided with eye screws, the upper die body and the lower die body are both provided with target holes, and the upper die body and the lower die body are both provided with thermocouple holes.
The application has the advantages that,
the forming die solves the problems of independent complete manufacturing cost of the drilling die in the prior art, the whole surface quality smoothing of products and the complicated positioning operation, and has the advantages of simple positioning operation, simple structure of the drilling die, capability of being arranged on a die body to be shared with the die body so as to save manufacturing cost, and the like, meets the requirements of hole sites of products, the position accuracy of lining in holes of the products and the quality and weight of carbon fiber missile wings.
The forming die disclosed by the application is applied to the forming process of the composite material product of the unmanned aerial vehicle, the integral surface quality of the composite material missile wing can be ensured by adopting compression molding, the positioning mode of the guide post and the guide sleeve is adopted, so that the positioning and mounting operability is more convenient, the drilling die and the die body are shared, the drilling precision and the positioning precision of the lining in the hole can be realized, and the manufacturing cost is saved.
Compared with other processes, the forming die provided by the application has higher strength and rigidity of a product formed by compression molding of the composite material, and the die is designed according to the composite material missile wing product, so that the requirement of the strength and rigidity of the product is met during the forming process of the product, and the integral surface quality of the product is also met.
The forming die disclosed by the application has the advantages that the drill jig and the die body are shared, the requirement on the aperture precision of a product is met, the parts of the drill jig are reduced in an optimized manner, the working is more efficient and quicker, and the cost is saved.
The upper die body, the lower die body of the forming die are positioned in the form of guide posts and guide sleeves, so that the requirements of die positioning, mounting and dismounting are met.
The forming die is designed to be in a form of a top thread hole and a die opening groove aiming at the problem that the die opening of the compression forming die is difficult, so that the die opening is convenient.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, made with reference to the following drawings,
FIG. 1 is a schematic diagram of a carbon fiber missile wing compression molding die according to the present application;
FIG. 2 is a schematic diagram showing a total structure of a molding die for forming a carbon fiber missile wing according to the present application;
FIG. 3 is a schematic diagram of an upper mold body of a molding mold for forming a carbon fiber missile wing according to the present application;
FIG. 4 is a schematic diagram of an upper mold body of a molding mold for forming a carbon fiber missile wing according to the second embodiment of the present application;
FIG. 5 is a schematic diagram of a lower mold structure of a molding mold for forming a carbon fiber missile wing according to the present application;
FIG. 6 is a schematic diagram showing a connection structure between a lower die body and a drill die bottom plate of a carbon fiber missile wing compression molding die;
FIG. 7 is a schematic diagram showing the connection structure between the lower die body and the drill die bottom plate and the positioning block of the carbon fiber missile wing compression molding die;
FIG. 8 is a schematic view of the structure of the lower mold body, the drill mold bottom plate, the positioning block and the pressing plate of the carbon fiber missile wing compression molding mold;
FIG. 9 is a schematic diagram showing the connection structure between the drill jig bottom plate and the positioning block of the molding die for the carbon fiber missile wing according to the present application;
FIG. 10 is a schematic diagram II of the connection structure between the drill jig bottom plate and the positioning block of the molding die for the carbon fiber missile;
FIG. 11 is a schematic view of a platen structure of a molding die for forming a carbon fiber missile;
fig. 12 is a structural line drawing of a carbon fiber missile wing compression molding die of the present application.
In the figure, 1, an upper die body; 2. a lower die body; 3. a guide post; 4. guide sleeve; 5. an upper spring wing profile groove; 6. an upper gumming groove; 7. a lower spring wing profile groove; 8. a lower gumming groove; 9. a pressing plate; 10. a drill jig bottom plate; 11. a positioning block; 12. knurled high head screws; 13. positioning a bolt; 14. a through hole; 15. a liner hole; 16. screw holes; 17. a cylindrical pin hole; 18. a bushing locating pin; 19. a connecting screw; 20. an internal thread cylindrical pin; 21. a top thread hole; 22. opening a die cavity; 23. a limit groove; 24. drilling a groove; 25. a steel gasket; 26. a suspension ring screw; 27. a target hole; 28. and a thermocouple.
Detailed Description
The application is further described in connection with the following detailed description, in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the application easy to understand.
Referring to fig. 1-12, the application provides a technical scheme of a carbon fiber missile wing compression molding mold, which comprises an upper mold body 1 and a lower mold body 2, wherein the upper mold body 1 and the lower mold body 2 are butted together through a plurality of groups of guide posts 3 and guide sleeves 4, the guide posts 3 and the guide sleeves 4 are all steel standard components and can be purchased in stock, the two guide posts 3 and the guide sleeves 4 are respectively fixed on the lower mold body 2 and the upper mold body 1 by bolts during mold closing, so that the positioning of the upper mold body and the lower mold body is more convenient and better in operability, the guide posts 3 are arranged at the top of the lower mold body 2, the guide sleeves 4 are arranged at the bottom of the upper mold body 1, an upper missile wing contour groove 5 is formed in the center of the bottom of the upper mold body 1, lower missile wing contour groove 6 is formed on two sides of the upper missile wing contour groove 5, a lower missile wing contour groove 7 matched with the upper missile wing contour groove 5 is formed in the center of the upper mold body 2, and a lower missile wing contour groove 7 is formed between the two sides of the lower die body 2 and the upper contour groove 7, and the lower contour groove 7 is formed by adopting a clearance groove between the two sides of the upper flange contour groove 7 and the lower contour groove 7; by designing the upper gumming groove 6 and the lower gumming groove 8, redundant resin flows out along the grooves when the upper die body 1 and the lower die body 2 are assembled and molded.
1-2, the upper die body 1 and the lower die body 2 are fixedly connected with each other through a plurality of groups of fixing screws and fixing nuts, the upper die body 1 is provided with screws, the lower die body 2 is provided with nuts, and holes matched with the fixing screws and the fixing nuts are respectively formed in the upper die body 1 and the lower die body 2; after the upper die body 1 and the lower die body 2 are positioned, clamping and die closing are performed by using a fixing screw, a fixing nut and a gasket.
Referring to fig. 6-11, the missile wing drill jig comprises a pressing plate 9, two drill jig bottom plates 10 and two positioning blocks 11, wherein the pressing plate 9 and the drill jig bottom plates 10 are respectively positioned at two sides of the top of the lower die body 2, a plurality of through holes 14 matched with the fixing screws are formed in the pressing plate 9, the pressing plate 9 presses and holds the missile wing workpiece, the pressing plate 9 adopts Q235 steel and is matched with the screws, nuts and gaskets to fix the missile wing workpiece, so that the missile wing workpiece is attached to the die surface during drilling, the die surface is more stable, the two drill jig bottom plates 10 are symmetrically arranged at the other side of the top of the lower die body 2, one side of the drill jig bottom plates 10 is provided with knurled high head screws 12 and two positioning bolts 13, the drill jig bottom plates 10 are made of Q235 steel, after being positioned by the positioning bolts 13, bottom holes of a product are clamped by the high head screws 12, the two positioning bolts 13 are symmetrically arranged on two sides of the knurled high head screw 12, the lower die body 2 is provided with connecting holes matched with the knurled high head screw 12 and the positioning bolts 13, the other side of the drill jig bottom plate 10 is provided with two bushing holes 15, two screw holes 16 and two cylindrical pin holes 17, the middle part of the positioning block 11 is symmetrically provided with two bushing positioning pins 18 matched with the bushing holes 15, two connecting screws 19 matched with the screw holes 16 and two internal thread cylindrical pins 20 matched with the cylindrical pin holes 17, the positioning block 11 and the bushing positioning pins 18 are all made of Q235 steel, the positioning block 11 is positioned and installed on the drill jig bottom plate 10 by utilizing the internal thread cylindrical pins 20 and the connecting screws 19, the bushing positioning pins 18 are matched with the bushing positioning pins 18 after the product is adhered to meet the bushing positioning tolerance, the steel gasket 25 is damaged due to the fact that the drilling is performed, the lining is bonded after being replaced in time when the lining is bonded in the hole.
Referring to fig. 3-5, the upper mold body 1 is provided with a plurality of top thread holes 21, the upper mold body is designed with the top thread holes 21, in practical application, the upper mold body 1 is provided with a mold opening groove 22 in cooperation with mold opening, the upper mold body 1 is provided with the mold opening groove 22, mold opening is facilitated by arranging the mold opening groove 22 on the upper mold body 1, the lower mold body 2 is provided with a limit groove 23 matched with the fixing nut, and the lower mold body 2 is provided with the limit groove 23 for limiting rotation of the fixing nut, thereby facilitating mold closing.
In a fifth embodiment, referring to fig. 5, a plurality of drilling grooves 24 are formed in the lower missile wing contour groove 7, two bushing holes 15 correspond to the drilling grooves 24, and steel gaskets 25 are embedded in the drilling grooves 24; in practice, to prevent damage to the die pad profile during drilling of the drill jig, a replaceable steel spacer 25 is inserted into the drill slot 24 for protection.
1-2, the upper die body 1 and the lower die body 2 are both provided with eye screws 26, the mold transportation is facilitated by installing the eye screws 26 on the upper die body and the lower die body, the upper die body 1 and the lower die body 2 are both provided with target holes 27, the target holes 27 serve as reference holes for mold positioning, the upper die body 1 and the lower die body 2 are both provided with thermocouple holes 28, and the thermocouple holes 28 are used for temperature detection.
When in use:
and (3) product forming: during forming, a compression molding process is adopted, a steel gasket 25 is placed on a drilling groove 24 on the lower die body 2 in advance before layering, a missile wing product is paved on the film pasting surface of the lower die body 2, the upper die body 1 is positioned and installed by utilizing a guide post 3 and a guide sleeve 4 after layering, and the steel gasket is clamped and fixed by using a fixing screw, a fixing nut and a gasket standard part, and is formed in an autoclave.
And (3) mold opening: the product is demolded by means of the top wire hole 21 and the die opening groove 22.
Drilling: after the product is placed on the lower die body 2 and pressed to be in a bonding state with a film pasting surface by using the pressing plate 9, the positioning bolt 13 is used for positioning, the knurled high head screw 12 is used for clamping, the drill jig bottom plate 10 is installed, the product bottom hole drilling action is carried out, after the drilling is carried out, the steel gasket 25 is taken out, the product bushing is bonded in the product bottom hole, the drill jig bottom plate 10 is positioned by using the internal thread cylindrical pin 20, the connecting screw 19 is used for clamping to install the positioning block 11, and then the bushing positioning pin 18 is installed to position the bushing bonded by the product.
And (3) blanking: and taking down the product, and ending the flow.
Although the present disclosure describes embodiments, not every embodiment is described in terms of a single embodiment, and such description is for clarity only, and one skilled in the art will recognize that the embodiments described in the disclosure as a whole may be combined appropriately to form other embodiments that will be apparent to those skilled in the art.
Claims (7)
1. The utility model provides a carbon fiber missile wing compression molding die, its characterized in that, includes last die body (1) and lower die body (2), go up die body (1) with dock together with guide pin bushing (4) through a plurality of guide pillar (3) between lower die body (2), guide pillar (3) set up the top of lower die body (2), guide pin bushing (4) set up the bottom of last die body (1), upper portion missile wing contour groove (5) have been seted up in last die body (1) bottom center department, upper portion missile wing contour groove (5) both sides all are equipped with upper portion basin (6), lower die body (2) top center department seted up with upper portion missile wing contour groove (5) matched with lower part missile wing contour groove (7), upper portion missile wing contour groove (5) with cast the missile wing work piece between lower part missile wing contour groove (7) both, lower part missile wing contour groove (7) both sides all are equipped with lower part missile wing contour groove (8), upper portion missile wing contour groove (5) are equipped with between the nose die.
2. The carbon fiber missile wing compression molding die according to claim 1, wherein the upper die body (1) and the lower die body (2) are fixedly connected with the fixing nuts through a plurality of groups of fixing screws, the upper die body (1) is provided with the screws, the lower die body (2) is provided with the nuts, and holes matched with the fixing screws and the fixing nuts are respectively formed in the upper die body (1) and the lower die body (2).
3. The carbon fiber missile wing compression molding die according to claim 2, wherein the missile wing drill die comprises a pressing plate (9), two drill die bottom plates (10) and two positioning blocks (11), the pressing plate (9) and the drill die bottom plates (10) are respectively located at two sides of the top of the lower die body (2), a plurality of through holes (14) matched with fixing screws are formed in the pressing plate (9), the missile wing workpiece is pressed and held by the pressing plate (9), the two drill die bottom plates (10) are symmetrically arranged at the other side of the top of the lower die body (2), knurled high head screws (12) and two positioning bolts (13) are arranged at one side of the drill die bottom plates (10), the two positioning bolts (13) are symmetrically arranged at two sides of the knurled high head screws (12), connecting holes matched with the knurled high head screws (12) and the positioning bolts (13) are formed in the lower die body (2), and two cylindrical pin holes (16) are formed in the other side of the drill die bottom plates (10), and two cylindrical pin holes (17) are formed in the other side of the drill die bottom plates.
4. A carbon fiber missile wing compression molding die according to claim 3, characterized in that the middle part of the positioning block (11) is symmetrically provided with two bushing positioning pins (18) matched with the bushing holes (15), two connecting screws (19) matched with the screw holes (16) and two internally threaded cylindrical pins (20) matched with the cylindrical pin holes (17).
5. The carbon fiber missile wing compression molding die according to claim 4, wherein the upper die body (1) is provided with a plurality of jackscrew holes (21), the upper die body (1) is provided with a die opening groove (22), and the lower die body (2) is provided with a limit groove (23) matched with the fixing nut.
6. The carbon fiber missile wing compression molding die according to claim 5, wherein a plurality of drilling grooves (24) are formed in the lower missile wing contour groove (7), two bushing holes (15) correspond to the drilling grooves (24), and steel gaskets (25) are embedded in the drilling grooves (24).
7. The carbon fiber missile wing compression molding die according to claim 6, wherein the upper die body (1) and the lower die body (2) are provided with eye screws (26), the upper die body (1) and the lower die body (2) are provided with target holes (27), and the upper die body (1) and the lower die body (2) are provided with thermocouples (28).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311214388.0A CN116945427A (en) | 2023-09-20 | 2023-09-20 | Carbon fiber missile wing compression molding die |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311214388.0A CN116945427A (en) | 2023-09-20 | 2023-09-20 | Carbon fiber missile wing compression molding die |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116945427A true CN116945427A (en) | 2023-10-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311214388.0A Pending CN116945427A (en) | 2023-09-20 | 2023-09-20 | Carbon fiber missile wing compression molding die |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116945427A (en) |
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2023
- 2023-09-20 CN CN202311214388.0A patent/CN116945427A/en active Pending
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