CN113119490A - Integrally-formed composite cabin capable of performing electromagnetic shielding and forming process thereof - Google Patents
Integrally-formed composite cabin capable of performing electromagnetic shielding and forming process thereof Download PDFInfo
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- CN113119490A CN113119490A CN202110307626.7A CN202110307626A CN113119490A CN 113119490 A CN113119490 A CN 113119490A CN 202110307626 A CN202110307626 A CN 202110307626A CN 113119490 A CN113119490 A CN 113119490A
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- 239000002131 composite material Substances 0.000 title claims abstract description 52
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- 238000003825 pressing Methods 0.000 claims description 22
- 239000000463 material Substances 0.000 claims description 16
- 239000002346 layers by function Substances 0.000 claims description 15
- 229920005989 resin Polymers 0.000 claims description 9
- 239000011347 resin Substances 0.000 claims description 9
- 239000002994 raw material Substances 0.000 claims description 8
- 238000000465 moulding Methods 0.000 claims description 7
- 239000011159 matrix material Substances 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 238000012545 processing Methods 0.000 claims description 6
- 239000012779 reinforcing material Substances 0.000 claims description 6
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- XQUPVDVFXZDTLT-UHFFFAOYSA-N 1-[4-[[4-(2,5-dioxopyrrol-1-yl)phenyl]methyl]phenyl]pyrrole-2,5-dione Chemical compound O=C1C=CC(=O)N1C(C=C1)=CC=C1CC1=CC=C(N2C(C=CC2=O)=O)C=C1 XQUPVDVFXZDTLT-UHFFFAOYSA-N 0.000 claims description 3
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 229920006231 aramid fiber Polymers 0.000 claims description 3
- 230000001680 brushing effect Effects 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 238000004140 cleaning Methods 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 229920003192 poly(bis maleimide) Polymers 0.000 claims description 3
- 229920000647 polyepoxide Polymers 0.000 claims description 3
- 229920001225 polyester resin Polymers 0.000 claims description 3
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- 239000010453 quartz Substances 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
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- 238000004804 winding Methods 0.000 description 1
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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
- B29C70/04—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
- B29C70/345—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 matched moulds
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- 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
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The invention provides an integrally formed composite cabin capable of carrying out electromagnetic shielding and a forming process thereof. The capsule body is prepared by adopting a prepreg laying process, has the advantages of high strength, electromagnetic shielding, light weight, low cost and the like, the production period of a single piece is 24 hours, and the formed integrated capsule body has good dimensional precision and does not need to be processed for 2 times.
Description
Technical Field
The invention relates to an integrally formed composite cabin capable of performing electromagnetic shielding and a forming process thereof, belonging to the technical field of composite cabins.
Background
The composite cabin is commonly used for manufacturing military missile shells, and the development and development of the composite cabin and the wings have been explored and applied for more than 10 years, so that great progress and development are achieved. Compared with the traditional mechanical assembly of the cabin body and the wing panel, the integrated molding of the cabin body and the wing panel reduces the assembly period and improves the production efficiency, and the design scheme of the integrated molding of the cabin body and the wing panel becomes a hot spot of the discussion at home and abroad in recent years.
Disclosure of Invention
The invention provides an integrally formed composite material cabin capable of performing electromagnetic shielding and a forming process thereof, aiming at solving the technical problems that the cabin can not be subjected to electromagnetic shielding, the metal processing difficulty of a thin-wall structure is high, and the period is long.
The invention provides an integrally formed composite material cabin capable of performing electromagnetic shielding, which comprises a plurality of fins and a barrel body, wherein the fins and the barrel body are integrally formed, the barrel body comprises a composite material structure layer, an electromagnetic shielding function layer and a composite material structure layer inner layer, the composite material structure layer is internally wrapped with the electromagnetic shielding function layer, and the composite material structure layer inner layer is wrapped in the electromagnetic shielding function layer.
Preferably, the thickness of the composite structure layer is 1mm-4 mm.
Preferably, the thickness of the electromagnetic shielding function layer is 0.2mm-1 mm.
Preferably, the fin is 2mm-6mm thick and has a plate structure.
Preferably, the raw materials of the composite material structure layer and the wing panel are prepregs made of reinforcing materials and matrix materials.
Preferably, the reinforcing material is one of carbon fiber, glass fiber, aramid fiber and quartz fiber.
Preferably, the matrix resin is one of epoxy resin, bismaleimide resin, polyester resin and cyanate resin.
Preferably, the electromagnetic shielding function layer is a woven metal mesh.
The forming process of the integrally formed composite cabin body capable of performing electromagnetic shielding specifically comprises the following steps:
(1) preparing an integrated molding die of the cabin body; cleaning the surface of the mold, and uniformly brushing a release agent on the surface after preheating the mold;
(2) preparing a composite material structure layer, a fin raw material and an electromagnetic shielding function layer raw material;
(3) paving an inner layer of a composite material structural layer and an electromagnetic shielding functional layer on the outer wall of a core mold of the preheated mold;
(4) laying composite material structure layers and fins on the surfaces of the upper part and the lower part of an external pressing die of the preheated die;
(5) after the paving is finished, assembling the core mould and the external pressing mould, connecting the core mould and the external pressing mould by using bolts and pin holes, and uniformly pressing the upper surface and the lower surface of the external pressing mould until the surfaces of the upper mould and the lower mould are completely attached, wherein the gap is less than or equal to 0.1 mm;
(6) after the die is closed in place, heating and curing the die, after curing, removing the external pressing die and the core die in sequence after the die is naturally cooled, and taking out the product;
(7) and processing the product according to a drawing to a set size to finish the preparation of the composite cabin body capable of carrying out electromagnetic shielding.
Preferably, the cabin body integrated forming mold is a stainless steel mold, and comprises an external pressing mold and a core mold, wherein the external pressing mold comprises an upper part and a lower part which are in a split structure.
The integrally formed composite cabin capable of performing electromagnetic shielding and the forming process thereof have the beneficial effects that:
1. the wing and the barrel are integrally formed, and the cabin body with the composite material structure and the electromagnetic shielding function is only 1mm-4mm thick, 0.2mm-1mm thick and belongs to a thin-wall structure; the whole thickness of the wing panel is 2mm-6mm plate type structure.
2. The composite material structure cabin body with the integrally formed fins and the integrally formed barrel and the electromagnetic shielding function is prepared by adopting a prepreg laying process, and has the advantages of high strength, electromagnetic shielding, light weight, low cost and the like.
3. According to the composite material structure cabin body with the fin and the barrel integrally formed and the electromagnetic shielding function, the production period of a single piece is 24 hours, the formed integrated cabin body has good dimensional precision, 2 times of processing is not needed, and the problems of high metal processing difficulty, long period and the like of a thin-wall structure are solved.
4. The wing and the barrel are integrally formed, and the cabin body with the electromagnetic shielding function and the composite material structure is integrally formed, so that the rigidity and the strength of a joint are improved, and the mechanical connection of the wing and the cabin body in the assembling process is reduced, thereby improving the production efficiency, reducing the weight and reducing the cost.
5. The wing and the barrel of the composite material cabin body are integrally formed and have the electromagnetic shielding function, and can be used for a long time under the temperature condition of-40 ℃ to +60 ℃. The cabin body can bear the designed axial uniformly distributed load and bending load; the wing panel method can bear the designed load without damage, and the integrated cabin body has no hierarchical damage after the test.
6. The electromagnetic shielding test frequency band of the integrated cabin is tested in a formulated fixed frequency band according to the electromagnetic shielding material shielding effectiveness test method, the shielding effect is good, and the product can meet the requirements.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic structural diagram of an integrally formed composite cabin capable of electromagnetic shielding according to the present invention;
FIG. 2 is a left side view of FIG. 1;
FIG. 3 is a schematic view of a mold structure;
FIG. 4 is a schematic view of the structural layers of the cabin;
the composite material structure comprises 1-fin, 2-barrel, 3-additional pressing die, 4-core die, 5-composite material structure layer, 6-electromagnetic shielding function layer and 7-composite material structure layer inner layer.
Detailed Description
The following detailed description of embodiments of the invention is provided in conjunction with the appended drawings:
the first embodiment is as follows: the present embodiment is explained with reference to fig. 1 to 4. This embodiment the integrated into one piece combined material cabin that can carry out electromagnetic shield, including a plurality of fins 1 and barrel 2, a plurality of fins 1 and barrel 2 integrated into one piece, barrel 2 includes combined material structural layer 5, electromagnetic shield functional layer 6 and combined material structural layer inlayer 7, combined material structural layer 5 endocyst has electromagnetic shield functional layer 6, electromagnetic shield functional layer 6 endocyst has combined material structural layer inlayer 7.
The thickness of the composite material structural layer 5 is 1mm-4 mm. The thickness of the electromagnetic shielding functional layer 6 is 0.2mm-1 mm. The thickness of the fin is 2mm-6mm, and the fin is of a plate structure.
The invention creatively designs a composite material structure cabin body with integrally formed fins and a cabin body and an electromagnetic shielding function. The cabin body comprises: the wing panel 1 is used for controlling the flight attitude of the cabin body in the flight process of the cabin body (the number of the wing panels can be increased according to the design requirement); the cylinder 2 is a bearing structure and is provided with a control component; the barrel 2 and the fin 1 adopt winding and prepreg laying integrated forming technology, electromagnetic shielding functional layers such as special weaving materials and the like are laid in the forming process, and after the electromagnetic shielding functional layers are laid, the electromagnetic shielding functional layers are pressed and cured at high temperature through a metal matched die.
The composite material structure layer 5 and the fin raw materials are prepreg made of reinforcing materials and matrix materials; the electromagnetic shielding function layer 6 is a metal mesh of a woven material.
According to the product performance requirement, the reinforcing material can be selected from carbon fiber, glass fiber, aramid fiber and quartz fiber, and the matrix resin can be selected from epoxy resin, bismaleimide resin, polyester resin, cyanate resin and the like. The electromagnetic shielding function layer 6 is made of materials such as woven materials.
Through the design of a mould, the design of a laying layer and the process design, the continuity of fibers at the joint of the cabin body and the wing panel is ensured, and the rigidity and the strength of the joint are ensured; by means of process design, electromagnetic shielding functional layers such as seed weaving materials are laid in the structural layer and integrally cured and formed with the cabin body.
The mould is divided into a core mould 4 and an external pressing mould 3 (shown in figure 3), the core mould 4 and the external pressing mould group 3 are paved to the designed thickness of the product, then pre-pressing treatment is carried out, after the appearance of the product is repaired, the subsequent structural layer is paved according to the paving layer design. After laying, the die is closed in place and then enters heating equipment for curing and forming. And after the solidification process is finished, cooling to room temperature, splitting the mold, and taking out the product.
The molding process of the integrally molded composite cabin body capable of performing electromagnetic shielding specifically comprises the following steps:
(1) preparing a cabin body integrated forming mold, wherein the mold is made of stainless steel and consists of an external pressing mold 3 and a core mold 4, the external pressing mold is divided into an upper part and a lower part, and as shown in figure 3, the mold is combined into a hollow part of an internal cavity so as to correspondingly realize the molding of the integrated composite cabin body;
(2) cleaning the surface of the mold, and uniformly brushing a release agent on the surface after preheating the mold;
(3) preparing a composite material structure layer 5, a fin sheet 1 raw material and an electromagnetic shielding function layer 6 raw material;
(4) laying a structural layer inner layer and an electromagnetic shielding layer with corresponding thickness on the upper outer wall of the preheated core mold 4;
(5) laying a structural layer outer layer and fins with corresponding thickness on the surfaces of the upper part and the lower part of the preheated external pressing die 3;
(6) after the paving is finished, assembling the core mold 4 and the external compression mold 3, connecting the core mold and the external compression mold by using bolts and pin holes, and uniformly pressurizing the upper surface and the lower surface of the external compression mold 3 until the surfaces of the upper mold and the lower mold are completely attached (the gap is less than or equal to 0.1 mm);
(7) after the die is closed in place, heating and curing the die, after curing, removing the external pressing die and the core die in sequence after the die is naturally cooled, and taking out the product;
(8) and processing the product according to a drawing to a set size to finish the preparation of the composite cabin body capable of carrying out electromagnetic shielding.
The above-mentioned embodiments further explain the objects, technical solutions and advantages of the present invention in detail. It should be understood that the above-mentioned embodiments are only examples of the present invention, and are not intended to limit the present invention, and that the reasonable combination of the features described in the above-mentioned embodiments can be made, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an integrated into one piece can carry out combined material cabin body of electromagnetic shield which characterized in that, includes a plurality of fins (1) and barrel (2), a plurality of fins (1) and barrel (2) integrated into one piece, barrel (2) are including combined material structural layer (5), electromagnetic shield functional layer (6) and combined material structural layer inlayer (7), be equipped with electromagnetic shield functional layer (6) in combined material structural layer (5), be equipped with combined material structural layer inlayer (7) in electromagnetic shield functional layer (6).
2. The integrally formed composite cabin capable of electromagnetic shielding according to claim 1, wherein the thickness of the composite structural layer (5) is 1mm to 4 mm.
3. The integrally formed composite cabin capable of electromagnetic shielding according to claim 1, wherein the thickness of the electromagnetic shielding functional layer (6) is 0.2mm to 1 mm.
4. The integrally formed composite cabin capable of electromagnetic shielding according to claim 1, wherein the fins (1) have a thickness of 2mm to 6mm and are of a plate structure.
5. The integrally formed composite cabin capable of electromagnetic shielding according to claim 1, wherein the composite structure layer (5) and the wing pieces are made of prepreg made of reinforcing material and matrix material.
6. The integrally formed composite cabin capable of electromagnetic shielding according to claim 5, wherein the reinforcing material is one of carbon fiber, glass fiber, aramid fiber and quartz fiber.
7. The integrally molded composite cabin capable of electromagnetic shielding according to claim 5, wherein the matrix resin is one of epoxy resin, bismaleimide resin, polyester resin and cyanate ester resin.
8. The integrally formed composite cabin capable of electromagnetic shielding according to claim 1, wherein the electromagnetic shielding functional layer (6) is a woven metal mesh.
9. The molding process of the integrally molded composite cabin capable of being electromagnetically shielded according to any one of claims 1 to 8, specifically comprising the following steps:
(1) preparing an integrated molding die of the cabin body; cleaning the surface of the mold, and uniformly brushing a release agent on the surface after preheating the mold;
(2) preparing a composite material structure layer (5), a fin sheet (1) raw material and an electromagnetic shielding function layer (6) raw material;
(3) paving a composite material structure layer inner layer (7) and an electromagnetic shielding functional layer (6) on the outer wall of a core mold (4) of the preheated mold;
(4) laying composite material structure layers (5) and fins on the surfaces of the upper part and the lower part of an external compression mold (3) of the preheated mold;
(5) after the paving is finished, assembling the core mold (4) and the external pressing mold (3), connecting the core mold and the external pressing mold by using bolts and pin holes, and uniformly pressurizing the upper surface and the lower surface of the external pressing mold (3) until the surfaces of the upper mold and the lower mold are completely attached, wherein the gap is less than or equal to 0.1 mm;
(6) after the die is closed in place, heating and curing the die, after curing, removing the outer pressing die (3) and the core die (4) in sequence after the die is naturally cooled, and taking out the product;
(7) and processing the product according to a drawing to a set size to finish the preparation of the composite cabin body capable of carrying out electromagnetic shielding.
10. The process for integrally forming a composite cabin capable of electromagnetic shielding according to claim 9, wherein the cabin integral forming mold is a stainless steel mold comprising an outer pressing mold (3) and a core mold (4), and the outer pressing mold comprises an upper and a lower split structures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110307626.7A CN113119490A (en) | 2021-03-23 | 2021-03-23 | Integrally-formed composite cabin capable of performing electromagnetic shielding and forming process thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110307626.7A CN113119490A (en) | 2021-03-23 | 2021-03-23 | Integrally-formed composite cabin capable of performing electromagnetic shielding and forming process thereof |
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| Publication Number | Publication Date |
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| CN113119490A true CN113119490A (en) | 2021-07-16 |
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| CN202110307626.7A Pending CN113119490A (en) | 2021-03-23 | 2021-03-23 | Integrally-formed composite cabin capable of performing electromagnetic shielding and forming process thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115401960A (en) * | 2022-09-01 | 2022-11-29 | 哈尔滨玻璃钢研究院有限公司 | Resin-based composite material with high electromagnetic shielding efficiency and forming method and application thereof |
| CN117103723A (en) * | 2023-10-11 | 2023-11-24 | 威海光威复合材料股份有限公司 | Forming method of composite winged elastomer structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0933199A (en) * | 1995-06-07 | 1997-02-07 | Hughes Missile Syst Co | Hybrid composite body and missile member and manufacture thereof |
| CN101653990A (en) * | 2009-09-25 | 2010-02-24 | 北京航空航天大学 | Integrative solidifying and molding method of minitype unmanned aerial vehicle body and vertical fin and solidifying mold thereof |
| US8846189B1 (en) * | 2009-04-17 | 2014-09-30 | Uab Research Foundation | Long fiber thermoplastic thin-walled aeroshells for missile applications and methods of manufacture |
| CN105904741A (en) * | 2016-04-15 | 2016-08-31 | 航天材料及工艺研究所 | End-frame-carrying high temperature resistant composite material cabin forming method |
| CN107514939A (en) * | 2016-06-17 | 2017-12-26 | 浙江鑫宙竹基复合材料科技有限公司 | Rocket Composite Shell |
| CN107738457A (en) * | 2017-11-02 | 2018-02-27 | 中广核俊尔新材料有限公司 | A kind of integrated forming technique of unmanned aerial vehicle body |
| CN214582823U (en) * | 2021-03-23 | 2021-11-02 | 哈尔滨玻璃钢研究院有限公司 | Integrated formed composite cabin capable of performing electromagnetic shielding |
-
2021
- 2021-03-23 CN CN202110307626.7A patent/CN113119490A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0933199A (en) * | 1995-06-07 | 1997-02-07 | Hughes Missile Syst Co | Hybrid composite body and missile member and manufacture thereof |
| US8846189B1 (en) * | 2009-04-17 | 2014-09-30 | Uab Research Foundation | Long fiber thermoplastic thin-walled aeroshells for missile applications and methods of manufacture |
| CN101653990A (en) * | 2009-09-25 | 2010-02-24 | 北京航空航天大学 | Integrative solidifying and molding method of minitype unmanned aerial vehicle body and vertical fin and solidifying mold thereof |
| CN105904741A (en) * | 2016-04-15 | 2016-08-31 | 航天材料及工艺研究所 | End-frame-carrying high temperature resistant composite material cabin forming method |
| CN107514939A (en) * | 2016-06-17 | 2017-12-26 | 浙江鑫宙竹基复合材料科技有限公司 | Rocket Composite Shell |
| CN107738457A (en) * | 2017-11-02 | 2018-02-27 | 中广核俊尔新材料有限公司 | A kind of integrated forming technique of unmanned aerial vehicle body |
| CN214582823U (en) * | 2021-03-23 | 2021-11-02 | 哈尔滨玻璃钢研究院有限公司 | Integrated formed composite cabin capable of performing electromagnetic shielding |
Non-Patent Citations (3)
| Title |
|---|
| 于红军: "《工业配件用塑料制品与加工》", 27 February 2003, 科学技术文献出版社 * |
| 徐竹: "弹体后部件碳纤维预浸料铺贴工艺试验研究", 《合成材料老化与应用》 * |
| 薛成位: "《弹道导弹工程》", 31 October 2002, 中国宇航出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115401960A (en) * | 2022-09-01 | 2022-11-29 | 哈尔滨玻璃钢研究院有限公司 | Resin-based composite material with high electromagnetic shielding efficiency and forming method and application thereof |
| CN117103723A (en) * | 2023-10-11 | 2023-11-24 | 威海光威复合材料股份有限公司 | Forming method of composite winged elastomer structure |
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Application publication date: 20210716 |