CN107314707B - Composite material missile launching canister and preparation method thereof - Google Patents
Composite material missile launching canister and preparation method thereof Download PDFInfo
- Publication number
- CN107314707B CN107314707B CN201710695069.4A CN201710695069A CN107314707B CN 107314707 B CN107314707 B CN 107314707B CN 201710695069 A CN201710695069 A CN 201710695069A CN 107314707 B CN107314707 B CN 107314707B
- Authority
- CN
- China
- Prior art keywords
- barrel
- support
- composite material
- composite
- layer
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention relates to a composite material missile launcher and a preparation method thereof. The barrel body is made of full composite materials, and the characteristics of high strength, good toughness and insufficient rigidity of the glass fiber reinforced material and the characteristics of high strength, good rigidity and insufficient toughness of the carbon fiber reinforced material are utilized to make up for deficiencies of each other, and the weight reduction is obvious, so that the requirements of increasingly complex launching environments are effectively met. According to the preparation method of the launch barrel, the barrel body, the guide rail and the internal installation block are integrally formed, the metal structures at the two ends are bonded by structural adhesive and sealed by the sealant, the sealing effect is good, the process is simple, and the production efficiency is improved.
Description
Technical Field
The invention relates to the technical field of missile launcher, in particular to a composite material missile launcher and a preparation method thereof.
Background
The launcher is an important component of tactical missiles, and can be used for storage, transportation and launching of the missiles. In order to adapt to the characteristics of the paroxysmal character, the rapid decision and the multidimensional character of the modern war, the weapon lightweight is the important importance of scientific research. As a result, composite emitters have become a future development trend. The existing all-metal and metal-lined composite launchers cannot meet the requirement of the lightest weight, the composite launchers are made of glass fiber reinforced plastics, and rockets or missiles are launched while the inner walls of launch barrels are obviously ablated, so that the composite launchers can be generally used once. In wartime, the ammunition is replenished, and meanwhile, the emitter is also required to be replenished, so that the replenishing difficulty is increased. For the army needing quick response to combat, the portable materials are limited, the spare launcher is required to be carried, the portable ammunition amount is reduced, and the development of the light and reusable launcher has important strategic significance and use value.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a composite material missile launcher and a preparation method thereof.
The technical problem to be solved by the invention is how to prepare a new launch canister, so that the prepared launch canister has the characteristics of light weight, high temperature flame scouring resistance, strong bearing capacity, high pressure resistance, good sealing performance, strong electromagnetic shielding capacity, low maintenance cost, reusability and the like.
The purpose of the invention is realized by the following technical scheme:
a composite material missile launcher comprises a composite material barrel body, a guide rail, a locking mechanism mounting block, metal joints at two ends of the barrel body, a hoisting block, a support, support feet, a circumferential reinforcing rib and a plug falling window; the composite material barrel is characterized in that the composite material barrel is made of carbon fiber and glass fiber mixed composite fibers, and the composite material barrel is sequentially provided with a heat-resistant anti-scouring layer, a glass fiber layer, a carbon fiber structure layer, an anti-electromagnetic shielding layer, a glass fiber layer, a barrel upper part and a surface paint layer from inside to outside.
The cylinder, the guide rail and the locking mechanism mounting block are integrally formed; the metal joints at the two ends of the cylinder body are connected with the cylinder body through an adhesive; the plug falling window is connected with the cylinder through an adhesive; the hoisting block, the support and the cylinder body are connected through an adhesive and a circumferential reinforcing rib; the support and the support foot are connected through a bolt.
The barrel fiber material is preferably a prepreg. The prepreg is very convenient to cut and lay, different orientations of fibers can be realized, the resin content is uniformly distributed, and the performance and the quality of a product are effectively ensured while the process efficiency is improved.
The heat-resistant coating is preferably a phosphate-based coating. The phosphate-based coating has the characteristics of excellent heat resistance and corrosion resistance, low price, less pollution and the like, and the phosphate-based coating with lower curing temperature and even capable of being cured at normal temperature is selected, so that the process time can be greatly shortened.
The anti-electromagnetic shielding layer is preferably a copper mesh or a cable conductor. The copper mesh or the cable conductor has good conductivity, can be used for electromagnetic shielding, has low metal activity, and can avoid electrode corrosion between the copper mesh or the cable conductor and carbon fibers.
The hoisting block, the support and the shedding window are selected from carbon fiber prepreg. The shapes of small pieces such as the hoisting block, the support, the falling window and the like are complex, and the prepreg is favorable for molding by utilizing the characteristics of the prepreg.
The support legs and the joints at the two ends of the barrel are made of antirust aluminum alloy, and the joints are connected by threads or flanges according to the connection requirements of the box cover. Because need frequent dismouting between case lid and the barrel, so choose wear-resisting higher metal material for use, adopt rust-resistant aluminum alloy in order to avoid the influence of humid environment such as shipping.
The reinforcing ribs are formed by annularly winding carbon fibers. Utilize hoop strengthening rib fixing support and hoist and mount piece, the atress intensity of this department when guaranteeing barrel hoist and mount transportation simultaneously, this department atress direction is more single, and it is higher to adopt winding shaping efficiency.
A preparation method of a composite material missile launcher specifically comprises the following steps:
(1) Manufacturing a barrel mandrel mould, sequentially laying a heat-resistant anti-scouring layer, a glass fiber layer, a carbon fiber structure layer, an electromagnetic shielding layer and a glass fiber layer on a mandrel by controlling the shape of the mandrel, ensuring that the barrel, a guide rail and a locking mechanism mounting block are integrally formed, connecting a locking mechanism in the barrel through a screw, and embedding a threaded steel sleeve in the locking mechanism mounting block;
(2) After the barrel machine is polished in place, demolding is carried out, and a shedding window is cut after the demolding is finished;
(3) Independently forming the hoisting block and the support, then adhering the hoisting block and the support to the cylinder, and winding and reinforcing carbon fibers at the flanging position of the hoisting block and the support;
(4) Bonding metal joints at two ends and a shedding window;
(5) And screwing the support leg, and decorating and spraying paint to obtain the composite material missile launching canister.
Compared with the prior art, the invention has the positive effects that:
1) Compared with an all-aluminum alloy launch barrel, the launch barrel made of the all-composite material has obvious weight reduction;
2) Through the mixing of the two materials, the characteristics of high strength, good toughness and insufficient rigidity of the glass fiber reinforced material and the characteristics of high strength, good rigidity and insufficient toughness of the carbon fiber reinforced material are utilized to make up for the deficiencies of the glass fiber reinforced material and effectively meet the increasingly complex emission environment requirements;
3) Different cross-sectional shapes can be designed by controlling the structural size of the mandrel;
4) The barrel body, the guide rail and the like are integrally formed, so that secondary curing is reduced, and the process efficiency is effectively improved;
5) The artificial paving is adopted, different wall thicknesses can be designed, the shape of the cylinder body is optimized, and the light weight requirement is met;
6) The joints at the two ends of the support foot are made of metal materials, so that the service life and the maintainability are improved;
7) The hoop winding reinforcing rib can be used for reinforcing the installation of the hoisting block and the support and can also be used as an integral reinforcing part of the cylinder body;
8) Tests prove that the barrel body of the launching barrel has higher strength and can withstand high-temperature scouring in a short time;
9) The metal cylinder covers are matched with the front and the rear metal cylinder covers, and the cylinder shielding layer is added, so that a good electromagnetic shielding effect is achieved;
10 Can be reused after simple maintenance;
11 Verified that the structure provides good air tightness.
The invention is characterized in that:
the barrel body is made of full composite materials, and the characteristics of high strength, good toughness and insufficient rigidity of the glass fiber reinforced material and the characteristics of high strength, good rigidity and insufficient toughness of the carbon fiber reinforced material are utilized to make up for deficiencies of each other, and the weight reduction is obvious, so that the requirements of increasingly complex launching environments are effectively met. According to the preparation method of the launch barrel, the barrel body, the guide rail and the internal installation block are integrally formed, metal structures at two ends are bonded by structural adhesive and sealed by the sealant, the sealing effect is good, the process is simple, and the production efficiency is improved.
Drawings
FIG. 1 is a schematic cross-sectional view of a composite launch canister according to an embodiment of the invention;
FIG. 2 is a schematic end view of a composite launch canister according to an embodiment of the invention;
FIG. 3 is a schematic view of the layers of the composite launch canister body according to an embodiment of the invention;
FIG. 4 is a flow chart of the manufacturing method of the present invention.
Detailed Description
The following provides a specific embodiment of the composite material missile launcher and the preparation method thereof.
Example 1
Referring to the attached drawings 1-4, the embodiment of the invention provides a composite material launch barrel, which comprises a launch barrel body 1, a threaded end cover 2, a hoisting block 3, a support 4, a support foot 5, a shedding window 6 and a circumferential reinforcing rib 7. The total length of the cylinder body is 2480 plus or minus 1mm, and the inner diameter of the cylinder body is phi 180 0 +0.27 mm, and the wall thickness of the cylinder body is 2.5mm. The structural layers of the cylinder 1 are shown in fig. 3, and mainly comprise a heat-resistant anti-scouring layer 8, a glass fiber layer 9, a carbon fiber structural layer 10, an electromagnetic shielding layer 11 and a glass fiber layer 12. The heat-resistant scouring layer 8 is made of phosphate-based coating, the electromagnetic shielding layer 11 is made of AFR-250-0.20 cable wires, the glass fibers 8 and 12 are made of alkali-free prepreg glass cloth, and the carbon fiber layer 10 is made of Dongli T700 unidirectional prepreg and T300 fabric prepreg.
The specific manufacturing process is as follows:
1) Manufacturing a mandrel mould according to the inner cavity structure of the launching tube, and arranging a guide rail groove and a locking mechanism mounting plate position on the mould so that the tube body, the guide rail and the mounting plate are integrally formed;
2) Cleaning the surface of the core mold by using acetone, and uniformly coating sufficient release agent;
3) 3-4 times of phosphate-based coating is sprayed on the mould, the interval of each time is 30 minutes, the mould is placed for 2 hours at room temperature after the coating is finished, and then the core mould is placed into a curing furnace for curing to form a heat-insulating anti-scouring layer;
4) Laying a layer of glass fiber fabric cloth with the angle of +/-45 degrees, and performing vacuum pre-compaction, wherein the vacuumizing force is more than 70KPa, and the time is controlled to be more than 20 minutes;
5) Laying 10 carbon fiber layers, and performing vacuum pre-compaction once every 3-4 layers to ensure that the layers are tightly laid;
6) Wrapping a layer of cable conductor outside the carbon cloth, and then laying a layer of glass cloth with the angle of +/-45 degrees;
7) After the cylinder is laid, the cylinder is fixed on a winding machine for winding an OPP film so as to obtain better surface quality;
8) Putting the mixture into an oven for curing: the temperature rising and falling speed is 1 ℃/min, the temperature is raised to 120 ℃ in the first stage and is kept for 20 minutes, the temperature is raised to 135 ℃ in the second stage and is kept for 20 minutes, the temperature is raised to 150 ℃ in the third stage and is kept for 20 minutes, the temperature is raised to 180 ℃ in the fourth stage and is kept for 4 hours, and finally, the temperature is reduced to 60 ℃ along with the furnace and the furnace is taken out;
9) Machining the bonding parts of the threaded end heads at the two ends and the assembly surfaces of the two supports;
10 De-molding the mold to remove the OPP film;
11 Thorough cleaning of the metal parts and the cylinder with ethyl acetate;
12 Mixing and stirring the Ailanta 2014 adhesive, and gluing the parts on the barrel and the barrel body within 60 minutes of operation time;
13 After bonding is completed, the hoop 90 ° reinforcing rib is wound: winding under 30N tension by using a T700 carbon filament;
14 After the assembly is finished, secondary curing is carried out;
15 Puttying to enhance sealing and secondary assembly of the stand foot at the assembly location;
16 Air tightness test: the front end and the rear end of the launch canister are connected by using M190 multiplied by 2 external threads at the two ends of the launch canister and a flange with internal threads, the front end and the rear end are sealed by adopting an O-shaped gasket, a hole is formed in the flange, the hole at the front end is connected with a barometer, the hole at the rear end is connected with a workshop air source, the pressure is increased to 125KPa, the air source is closed, the launch canister is placed in a thermostatic chamber, the pressure is maintained for 96 hours, and the result shows that the deviation is less than or equal to 0.5KPa;
17 H06-1012H epoxy primer is sprayed on the outside of the cylinder and delivered after detection.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, many modifications and amendments can be made without departing from the spirit of the present invention, and these modifications and amendments should also be considered as within the scope of the present invention.
Claims (7)
1. A composite material missile launcher comprises a composite material barrel body, a guide rail, a locking mechanism mounting block, metal joints at two ends of the barrel body, a hoisting block, a support, support feet, a circumferential reinforcing rib and a plug falling window; the composite material barrel is characterized in that the composite material barrel is made of carbon fiber and glass fiber mixed composite fibers, and the composite material barrel is sequentially provided with a heat-resistant anti-scouring layer, a glass fiber layer, a carbon fiber structure layer, an anti-electromagnetic shielding layer, a glass fiber layer, an upper part of the barrel and a surface paint layer from inside to outside;
the cylinder, the guide rail and the locking mechanism mounting block are integrally formed; the metal joints at the two ends of the cylinder body are connected with the cylinder body through an adhesive; the plug falling window is connected with the cylinder through an adhesive; the hoisting block, the support and the cylinder are connected through an adhesive and an annular reinforcing rib; the support and the support foot are connected through a bolt;
the preparation method of the composite material missile launcher comprises the following specific steps:
(1) Manufacturing a barrel core shaft mold, laying each layer on a core mold by controlling the shape of the core mold, ensuring that the barrel, a guide rail and a locking mechanism mounting block are integrally formed, connecting a locking mechanism with a screw in the barrel, and embedding a threaded steel sleeve in the locking mechanism mounting block;
(2) After the barrel machine is polished in place, demolding is carried out, and a shedding window is cut after the demolding is finished;
(3) Independently forming the hoisting block and the support, then adhering the hoisting block and the support to the cylinder, and winding and reinforcing carbon fibers at the flanging position of the hoisting block and the support;
(4) Bonding metal joints at two ends and a shedding window;
(5) And screwing the support foot, and decorating and spraying paint to obtain the composite material missile launcher.
2. A composite missile launcher as claimed in claim 1, wherein the barrel fibre material is preferably a prepreg.
3. A composite missile launch canister as claimed in claim 1 wherein said heat and erosion resistant layer is preferably a phosphate based coating.
4. A composite missile launcher as claimed in claim 1, wherein the electromagnetic shielding is preferably copper mesh or cable conductor.
5. The composite missile launcher of claim 1, wherein the lifting block, the support and the drop window are carbon fiber prepregs.
6. The composite material missile launcher of claim 1, wherein the base feet and the joints at the two ends of the launcher body are made of rustproof aluminum alloy, and the joints are selected to be connected by threads or flanges according to the connection requirements of the box cover.
7. The composite missile launcher of claim 1, wherein the reinforcing ribs are formed by hoop winding carbon fibers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710695069.4A CN107314707B (en) | 2017-08-15 | 2017-08-15 | Composite material missile launching canister and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710695069.4A CN107314707B (en) | 2017-08-15 | 2017-08-15 | Composite material missile launching canister and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107314707A CN107314707A (en) | 2017-11-03 |
| CN107314707B true CN107314707B (en) | 2023-02-21 |
Family
ID=60176796
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710695069.4A Active CN107314707B (en) | 2017-08-15 | 2017-08-15 | Composite material missile launching canister and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107314707B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107718605A (en) * | 2017-11-16 | 2018-02-23 | 西安方元明科技股份有限公司 | One kind transmitting box body and preparation method thereof, firing box and preparation method thereof |
| CN109059645A (en) * | 2018-08-21 | 2018-12-21 | 浙江鑫宙竹基复合材料科技有限公司 | A kind of launching tube with multi-layer structure and the rocket launcher containing the launching tube |
| CN109323622B (en) * | 2018-11-26 | 2020-07-21 | 中国科学院长春光学精密机械与物理研究所 | Launching tube |
| CN109677562B (en) * | 2018-12-06 | 2024-01-30 | 江苏越科新材料有限公司 | Anchor chain based on composite material and preparation method thereof |
| CN111023894A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Missile launching canister and preparation method thereof |
| CN111186144A (en) * | 2019-12-26 | 2020-05-22 | 天津爱思达新材料科技有限公司 | Ablation-resistant composite material launching tube body structure and forming method thereof |
| CN111409327A (en) * | 2020-03-26 | 2020-07-14 | 北方长龙新材料技术有限公司 | Multi-linked rocket projectile storage and transportation box and manufacturing method thereof |
| CN111912292A (en) * | 2020-07-31 | 2020-11-10 | 西安方元明科技股份有限公司 | Bulletproof and composite structure integrated launch canister and preparation method thereof |
| CN112595172A (en) * | 2021-01-05 | 2021-04-02 | 中国电子科技集团公司第三十三研究所 | Strong electromagnetic pulse protection method for composite material launching canister |
| CN114953514A (en) * | 2021-02-19 | 2022-08-30 | 河北雷萨重型工程机械有限责任公司 | Crane, auxiliary crane boom thereof, boom cylinder of auxiliary crane boom and manufacturing method of boom cylinder |
| CN114851598B (en) * | 2022-03-15 | 2023-08-01 | 东华大学 | Polygonal composite material cylinder body bending-resistant composite forming method with long inner ribs and production line |
| CN115507698B (en) * | 2022-09-30 | 2024-04-12 | 北京星航机电装备有限公司 | Transmitting tube and forming method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103322854A (en) * | 2013-06-27 | 2013-09-25 | 北京航天新风机械设备有限责任公司 | Composite launcher tube and production method thereof |
| CN103395194A (en) * | 2013-08-05 | 2013-11-20 | 河北东恒宇功能材料新技术有限公司 | Manufacture method for composite-material launch canister of high-altitude fire-extinguishing rocket |
| CN106152874A (en) * | 2016-07-12 | 2016-11-23 | 北京航天发射技术研究所 | Sandwich full composite material launching tube |
| CN207095396U (en) * | 2017-08-15 | 2018-03-13 | 精功（绍兴）复合材料有限公司 | A kind of composite launch canister |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9863732B2 (en) * | 2013-08-28 | 2018-01-09 | Proof Research, Inc. | Lightweight composite mortar tube |
-
2017
- 2017-08-15 CN CN201710695069.4A patent/CN107314707B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103322854A (en) * | 2013-06-27 | 2013-09-25 | 北京航天新风机械设备有限责任公司 | Composite launcher tube and production method thereof |
| CN103395194A (en) * | 2013-08-05 | 2013-11-20 | 河北东恒宇功能材料新技术有限公司 | Manufacture method for composite-material launch canister of high-altitude fire-extinguishing rocket |
| CN106152874A (en) * | 2016-07-12 | 2016-11-23 | 北京航天发射技术研究所 | Sandwich full composite material launching tube |
| CN207095396U (en) * | 2017-08-15 | 2018-03-13 | 精功（绍兴）复合材料有限公司 | A kind of composite launch canister |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107314707A (en) | 2017-11-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107314707B (en) | Composite material missile launching canister and preparation method thereof | |
| US7402269B2 (en) | Environmentally stable hybrid fabric system for exterior protection of an aircraft | |
| US20110221093A1 (en) | Method and system for manufacturing wind turbine blades | |
| CN207095396U (en) | A kind of composite launch canister | |
| CN104354436A (en) | Manufacturing method of composite material shell wound by high-temperature-resistant fiber | |
| US20150292677A1 (en) | Method of manufacturing a compressed gas cylinder | |
| US7867589B2 (en) | Hybrid cryogenic tank construction and method of manufacture therefor | |
| RU2652414C2 (en) | Method for manufacturing gas cylinders | |
| CN111186144A (en) | Ablation-resistant composite material launching tube body structure and forming method thereof | |
| US9347610B1 (en) | Techniques for making pressure vessels as unitary structures of composite materials | |
| CA3051735A1 (en) | Composite connectors and methods of manufacturing the same | |
| CN109282139B (en) | Composite material gas cylinder and preparation method thereof | |
| US5054224A (en) | Apparatus and method for a composite polymer rifling disposable gun tube | |
| US10576692B2 (en) | Pre-polymerized thermosetting composite part and methods for making such a part | |
| US10195819B1 (en) | Multilayer ceramic composite and method of production | |
| CN110774611A (en) | Forming method of carbon fiber launching tube | |
| US20180119881A1 (en) | Method for preparing the internal shell of a composite type iv reservoir for storing pressurized fluid | |
| US4934412A (en) | Cooling pipe line for an engine | |
| CN104267479A (en) | Space camera secondary mirror support structure | |
| CN111421858B (en) | Composite material launching box and preparation method thereof | |
| CN110978558B (en) | Preparation method of seal-head-free fiber reinforced resin matrix composite material combustion chamber shell for rocket projectile | |
| US20120006482A1 (en) | Method for improving rubber bonding property between rubber and epoxy-composite | |
| CN104476781A (en) | Preparation method of metal lining ring-shaped composite cylinder | |
| CN115507698B (en) | Transmitting tube and forming method thereof | |
| US10576671B2 (en) | Method of connecting a skirt to a thruster body casing |
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 | ||
| CB02 | Change of applicant information |
Address after: 312000 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Applicant after: Shaoxing Baojing composite material Co.,Ltd. Applicant after: JINGGONG (SHAOXING) COMPOSITE TECHNOLOGY R & D CO.,LTD. Address before: 312030 Building 2, jiuyiqiu, Haitu, Binhai Industrial Zone, Shaoxing City, Zhejiang Province Applicant before: JINGGONG (SHAOXING) COMPOSITE MATERIAL CO.,LTD. Applicant before: JINGGONG (SHAOXING) COMPOSITE TECHNOLOGY R & D CO.,LTD. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 312000 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Patentee after: Shaoxing Baojing composite material Co.,Ltd. Patentee after: Shaoxing Baojing Composite Technology Research and Development Co.,Ltd. Address before: 312000 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Patentee before: Shaoxing Baojing composite material Co.,Ltd. Patentee before: JINGGONG (SHAOXING) COMPOSITE TECHNOLOGY R & D CO.,LTD. |
|
| CP01 | Change in the name or title of a patent holder |