CN115416339A - Method for preparing composite material rocket engine shell formed by dry winding - Google Patents
Method for preparing composite material rocket engine shell formed by dry winding Download PDFInfo
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- CN115416339A CN115416339A CN202211084882.5A CN202211084882A CN115416339A CN 115416339 A CN115416339 A CN 115416339A CN 202211084882 A CN202211084882 A CN 202211084882A CN 115416339 A CN115416339 A CN 115416339A
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- 239000002131 composite material Substances 0.000 title claims abstract description 18
- 238000005490 dry winding Methods 0.000 title claims abstract description 14
- 238000000034 method Methods 0.000 title claims description 8
- 238000004804 winding Methods 0.000 claims abstract description 64
- 239000002184 metal Substances 0.000 claims abstract description 18
- 238000004519 manufacturing process Methods 0.000 claims abstract description 10
- 239000000835 fiber Substances 0.000 claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims description 42
- 230000001680 brushing effect Effects 0.000 claims description 9
- 238000004140 cleaning Methods 0.000 claims description 9
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 8
- 239000004917 carbon fiber Substances 0.000 claims description 8
- 230000003014 reinforcing effect Effects 0.000 claims description 8
- 238000005422 blasting Methods 0.000 claims description 6
- 239000006082 mold release agent Substances 0.000 claims description 6
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 3
- 229920000647 polyepoxide Polymers 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 abstract description 6
- 239000002994 raw material Substances 0.000 abstract description 5
- 229920005989 resin Polymers 0.000 abstract description 5
- 239000011347 resin Substances 0.000 abstract description 5
- 239000002699 waste material Substances 0.000 abstract description 3
- 238000005238 degreasing Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 230000009172 bursting Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000008187 granular material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000006116 polymerization reaction Methods 0.000 description 1
- 238000004046 wet winding Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D23/00—Producing tubular articles
- B29D23/001—Pipes; Pipe joints
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides a preparation method of a composite material rocket engine shell formed by dry winding, which relates to the technical field of aerospace equipment manufacturing and aims to solve the problems that the existing barrel winding forming die is high in resin content, not only is resistance easily reduced, but also raw material waste is caused, and the weight of a product is difficult to accurately control, so that the production efficiency is reduced, and the preparation method comprises the following steps: the metal head comprises a front joint and a rear joint, and the front joint and the rear joint are respectively arranged at the left end and the right end of the cylinder; the cylinder body is formed by a fiber layer cylinder body section. The invention can strictly control the resin content (accurate to within 2 percent), has dry operation environment and no waste of raw materials, can accurately control the weight of the product, has high production efficiency, has rich varieties of fiber winding products, has wide application, and comprises Shenzhou spaceship bearing members and the like which are applied to the high-end fields of aerospace and weaponry.
Description
Technical Field
The invention relates to the technical field of aerospace equipment manufacturing, in particular to a method for preparing a composite material rocket engine shell formed by dry winding.
Background
Along with the high-speed development of composite materials, the requirement for lightening weapons is higher and higher, the reinforced bursting strength is the main direction of a gun barrel shell, the high-performance carbon fiber composite material is used as a main material for preparing a novel weapon shell, and the weight of the high-performance carbon fiber composite material is less than half of that of metal under the condition of equal strength.
The core of manufacturing the composite material rocket engine shell is the design and preparation of a forming die, the existing rocket combustion chamber shell is mainly manufactured by adopting wet winding, the dry winding has wide prospect and advantages, and the dry winding as a novel winding technology has the advantages of easy control of the quality of a formed product, automation of the production process and the like.
At present, a winding forming die for small and medium-sized cylinders generally adopts two schemes: 1. the metal core mold structure is assembled to form a mold in the form of a shell plate, a core shaft and a support piece, an operator enters the product cavity from a polar hole to disassemble after a product is formed, and parts are conveyed out from the polar hole of the product; 2. the soluble core mould structure adopts granular materials to form a mould through polymerization by a certain means, after a product is formed, the soluble mould recovers granular shape and is taken out from a polar hole, and the small-size shell mostly adopts the form of the mould.
The existing cylinder winding forming die has too high resin content, so that the resistance is easily reduced, raw materials are wasted, the weight of a product is difficult to accurately control, and the production efficiency is reduced.
Disclosure of Invention
In view of the above, the invention provides a method for preparing a composite material rocket engine shell by dry winding molding, which aims to solve the problems that the existing barrel winding molding die is high in resin content, so that resistance is easily reduced, raw materials are wasted, the weight of a product is difficult to accurately control, and production efficiency is reduced.
The invention provides a preparation method of a composite material rocket engine shell formed by dry winding, which specifically comprises the following steps:
a composite material rocket engine shell formed by dry winding comprises a metal head and a barrel, wherein the metal head comprises a front joint and a rear joint, and the front joint and the rear joint are respectively arranged at the left end and the right end of the barrel; the cylinder body is formed by a fiber layer cylinder body section.
A preparation method of a composite material rocket engine shell formed by dry winding comprises the following steps: step 1, brushing a mold release agent on a mold, airing for more than 15min after finishing brushing the mold release agent, and repeatedly brushing for 3 times;
step 2, pre-impregnated silk carbon fibers and epoxy resin are pre-impregnated, the width of the pre-impregnated silk carbon fibers is 8mm, meanwhile, when winding is carried out, the winding tension is 45N, a heating device is used for carrying out online heating while winding is carried out, the heating temperature is 60 ℃, the heating mode is hot air, a temperature adding and controlling system is installed, the temperature can be detected and controlled in real time, the winding geodesic wire angle and the ply is [ 90/+/-45 ] s, and the thickness of the winding layer is 1mm;
step 3, winding the OPP tape after winding the prepreg filaments, wherein the winding angle and the layer of the geodesic wire are [ +/-90 ] s;
step 4, after the winding of the OPP belt is finished, heating, curing and forming are carried out through step heating, meanwhile, the curing temperature is 100-150 ℃, the heating rate is 2 ℃/min, and the curing time is 4-6h;
step 5, demolding and cleaning after curing is finished;
step 6, determining the required size and cutting off redundant parts at two ends;
step 7, polishing, degreasing and derusting the metal joint, and gluing the outer surface of the metal joint and the inner wall of the cylinder structure, wherein structural glue is J-33C;
step 8, winding a reinforcing layer on the cylinder and the metal joint which are spliced, wherein the width of the prepreg yarn is 8mm, the winding tension is 45N, a heating device is used for online heating while winding, the heating temperature is 60 ℃, the heating mode is hot air, a temperature adding control system is arranged, the temperature can be detected and controlled in real time, the winding geodesic angle and the layering are [ +/-7/90 ] s, the thickness of the winding layer is 1mm, and the total thickness of the winding layer is 2mm;
step 9, winding the OPP belt after the reinforcing layer is wound, wherein the winding angle and the layer of the geodesic wire are [ +/-90 ] s;
step 10, after the winding of the OPP belt is finished, heating, curing and forming are carried out through step heating, meanwhile, the curing temperature is 100-150 ℃, the heating rate is 2 ℃/min, and the curing time is 4-6h;
step 11, cleaning the surface of the cylinder after the reinforcing winding layer is cured;
and step 12, performing a hydraulic blasting test on the barrel after cleaning, wherein the hydraulic blasting pressure is 21MPa.
Advantageous effects
The invention can strictly control the resin content (accurate to within 2 percent), has dry operation environment and no waste of raw materials, can accurately control the weight of the product, has high production efficiency, has rich varieties of fiber winding products, has wide application, and comprises Shenzhou spaceship bearing members and the like which are applied to the high-end fields of aerospace and weaponry.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings of the embodiments will be briefly described below.
The drawings in the following description relate to only some embodiments of the invention and are not intended to limit the invention.
In the drawings:
FIG. 1 is a schematic view of the composite rocket motor case structure of the present invention.
FIG. 2 is a schematic diagram of the process flow structure of the present invention.
List of reference numerals
1. A front joint; 2. a rear joint; 3. a cylinder body.
Detailed Description
In order to make the objects, aspects and advantages of the embodiments of the present invention more apparent, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. Unless otherwise indicated, terms used herein have the ordinary meaning in the art. Like reference symbols in the various drawings indicate like elements.
Example (b): please refer to fig. 1 to fig. 2:
the invention provides a method for preparing a composite material rocket engine shell formed by dry winding, which comprises the following steps.
A composite material rocket engine shell formed by dry winding comprises a metal head and a cylinder, wherein the metal head comprises a front joint 1 and a rear joint 2, and the front joint 1 and the rear joint 2 are respectively arranged at the left end and the right end of the cylinder 3; the cylinder body is formed by a fiber layer cylinder body section 3.
A preparation method of a composite material rocket engine shell formed by dry winding comprises the following steps: step 1, brushing a mold release agent, airing for more than 15min after finishing brushing the mold release agent, and repeatedly brushing for 3 times;
step 2, pre-impregnated silk carbon fibers and epoxy resin are pre-impregnated, the width of the pre-impregnated silk carbon fibers is 8mm, meanwhile, when winding is carried out, the winding tension is 45N, a heating device is used for carrying out online heating while winding is carried out, the heating temperature is 60 ℃, the heating mode is hot air, a temperature adding and controlling system is installed, the temperature can be detected and controlled in real time, the winding geodesic wire angle and the ply is [ 90/+/-45 ] s, and the thickness of the winding layer is 1mm;
step 3, winding the OPP tape after winding the prepreg filaments, wherein the winding angle and the layer of the geodesic wire are [ +/-90 ] s;
step 4, after the winding of the OPP belt is finished, heating, curing and forming are carried out through step heating, meanwhile, the curing temperature is 100-150 ℃, the heating rate is 2 ℃/min, and the curing time is 4-6h;
step 5, demolding and cleaning after curing is finished;
step 6, determining the required size and cutting off redundant parts at two ends;
step 7, polishing, degreasing and derusting the metal joint, and gluing the outer surface of the metal joint and the inner wall of the cylinder structure, wherein structural glue is J-33C;
step 8, winding a reinforcing layer on the cylinder and the metal joint which are spliced, wherein the width of the prepreg yarn is 8mm, the winding tension is 45N, a heating device is used for online heating while winding, the heating temperature is 60 ℃, the heating mode is hot air, a temperature adding control system is arranged, the temperature can be detected and controlled in real time, the winding geodesic angle and the layering are [ +/-7/90 ] s, the thickness of the winding layer is 1mm, and the total thickness of the winding layer is 2mm;
step 9, winding the OPP belt after the reinforcing layer is wound, wherein the winding angle and the layer of the geodesic wire are [ +/-90 ] s;
step 10, after finishing winding the OPP belt, heating, curing and forming through step heating, wherein the curing temperature is 100-150 ℃, the heating rate is 2 ℃/min, and the curing time is 4-6h;
step 11, cleaning the surface of the cylinder body after the reinforcing winding layer is cured;
and step 12, performing a hydraulic blasting test on the barrel after cleaning, wherein the hydraulic blasting pressure is 21MPa.
The above description is intended to be illustrative of the present invention and not to limit the scope of the invention, which is defined by the claims appended hereto.
Claims (2)
1. The composite material rocket engine shell formed by dry winding is characterized by comprising a metal head and a barrel, wherein the metal head comprises a front joint (1) and a rear joint (2), and the front joint (1) and the rear joint (2) are respectively arranged at the left end and the right end of the barrel (3); the cylinder body is composed of a fiber layer cylinder body section (3).
2. A method of manufacturing a dry-wound composite rocket motor case according to claim 1, wherein said method comprises the steps of: the method comprises the following steps: step 1, brushing a mold release agent on a mold, airing for more than 15min after finishing brushing the mold release agent, and repeatedly brushing for 3 times;
step 2, pre-impregnated silk carbon fibers and epoxy resin are pre-impregnated, the width of the pre-impregnated silk carbon fibers is 8mm, meanwhile, when winding is carried out, the winding tension is 45N, a heating device is used for carrying out online heating while winding is carried out, the heating temperature is 60 ℃, the heating mode is hot air, a temperature adding and controlling system is installed, the temperature can be detected and controlled in real time, the winding geodesic wire angle and the ply is [ 90/+/-45 ] s, and the thickness of the winding layer is 1mm;
step 3, winding the prepreg filaments and then winding an OPP tape, wherein the winding ground wire angle and the layer laying are [ +/-90 ];
step 4, after the winding of the OPP belt is finished, heating, curing and forming are carried out through step heating, meanwhile, the curing temperature is 100-150 ℃, the heating rate is 2 ℃/min, and the curing time is 4-6h;
step 5, demolding and cleaning after curing is finished;
step 6, determining the required size and cutting off redundant parts at two ends;
step 7, polishing, deoiling and derusting the metal joint, and gluing the outer surface of the metal joint and the inner wall of the cylinder structure, wherein structural glue is J-33C;
step 8, winding the reinforced layer of the glued cylinder and the metal joint, wherein the width of the prepreg yarn is 8mm, the winding tension is 45N, a heating device is used for online heating while winding, the heating temperature is 60 ℃, the heating mode is hot air, and a temperature adding control system is arranged, so that the temperature can be detected and controlled in real time, the winding geodesic wire angle and the ply are +/-7/90 s, the thickness of the winding layer is 1mm, namely the total thickness of the winding layer is 2mm;
step 9, winding the OPP belt after the reinforcing layer is wound, wherein the winding angle and the layer of the geodesic wire are [ +/-90 ] s;
step 10, after the winding of the OPP belt is finished, heating, curing and forming are carried out through step heating, meanwhile, the curing temperature is 100-150 ℃, the heating rate is 2 ℃/min, and the curing time is 4-6h;
step 11, cleaning the surface of the cylinder body after the reinforcing winding layer is cured;
and step 12, performing a hydraulic blasting test on the barrel after cleaning, wherein the hydraulic blasting pressure is 21MPa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211084882.5A CN115416339A (en) | 2022-09-06 | 2022-09-06 | Method for preparing composite material rocket engine shell formed by dry winding |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211084882.5A CN115416339A (en) | 2022-09-06 | 2022-09-06 | Method for preparing composite material rocket engine shell formed by dry winding |
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| CN115416339A true CN115416339A (en) | 2022-12-02 |
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| CN202211084882.5A Pending CN115416339A (en) | 2022-09-06 | 2022-09-06 | Method for preparing composite material rocket engine shell formed by dry winding |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102802925A (en) * | 2009-06-26 | 2012-11-28 | Bd发明股份有限公司 | Method for manufacturing composite connecting rods, and connecting rods produced according to the method |
| 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 |
| CN112283572A (en) * | 2020-10-10 | 2021-01-29 | 南京航空航天大学 | Composite material gas cylinder and preparation method thereof |
| CN112477082A (en) * | 2020-10-12 | 2021-03-12 | 深圳烯创先进材料研究院有限公司 | Winding forming method of carbon fiber composite material structure layer |
| CN112644039A (en) * | 2020-12-28 | 2021-04-13 | 内蒙动力机械研究所 | Large-opening composite material shell, forming method and forming tool |
| CN113650318A (en) * | 2021-08-05 | 2021-11-16 | 浙江抟原复合材料有限公司 | Dry winding forming method for composite material gas cylinder |
| JP2022028221A (en) * | 2020-08-03 | 2022-02-16 | トヨタ自動車株式会社 | Manufacturing method for high pressure tank |
| CN114060393A (en) * | 2021-12-20 | 2022-02-18 | 武汉海威船舶与海洋工程科技有限公司 | Assembled carbon fiber composite transmission shaft and preparation method thereof |
-
2022
- 2022-09-06 CN CN202211084882.5A patent/CN115416339A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102802925A (en) * | 2009-06-26 | 2012-11-28 | Bd发明股份有限公司 | Method for manufacturing composite connecting rods, and connecting rods produced according to the method |
| 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 |
| JP2022028221A (en) * | 2020-08-03 | 2022-02-16 | トヨタ自動車株式会社 | Manufacturing method for high pressure tank |
| CN112283572A (en) * | 2020-10-10 | 2021-01-29 | 南京航空航天大学 | Composite material gas cylinder and preparation method thereof |
| CN112477082A (en) * | 2020-10-12 | 2021-03-12 | 深圳烯创先进材料研究院有限公司 | Winding forming method of carbon fiber composite material structure layer |
| CN112644039A (en) * | 2020-12-28 | 2021-04-13 | 内蒙动力机械研究所 | Large-opening composite material shell, forming method and forming tool |
| CN113650318A (en) * | 2021-08-05 | 2021-11-16 | 浙江抟原复合材料有限公司 | Dry winding forming method for composite material gas cylinder |
| CN114060393A (en) * | 2021-12-20 | 2022-02-18 | 武汉海威船舶与海洋工程科技有限公司 | Assembled carbon fiber composite transmission shaft and preparation method thereof |
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