CN102700150B - Molding method of wall-thickness-variable composite connection skirt - Google Patents
Molding method of wall-thickness-variable composite connection skirt Download PDFInfo
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- CN102700150B CN102700150B CN201210147672.6A CN201210147672A CN102700150B CN 102700150 B CN102700150 B CN 102700150B CN 201210147672 A CN201210147672 A CN 201210147672A CN 102700150 B CN102700150 B CN 102700150B
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Abstract
The invention relates to a molding method of a wall-thickness-variable composite connection skirt, comprising the following steps of: setting ply stacking angles and a ply stacking sequence, calculating the size and the number of ply stacking contents from each angle; shearing the ply stacking contents according to the calculated size and number of the ply stacking contents; manufacturing a product forming mold; laying the ply stacking contents on a mandrel of the mold according to the distance apart from a central line or a bottom end, achieving 0.5-0.6 of the number of designed layers; winding and pressurizing onto the surface of the ply stacking by fibers under the function of winding tension to perform pre-curing; finishing the left ply stacking; winding the fibers and pressurizing, heating and curing; disassembling the mold and taking out the product; and adhering corner boxes. The molding method provided by the invention is characterized by that independent molding of the integrated composite connection skirt before molding an engine shell is realized by adopting the manual ply stacking and the fiber winding and pressurizing technique according to the best ply stacking angle and sequence.
Description
Technical field
The present invention relates to solid-rocket and start housing forming method, be specifically related to a kind of forming method that becomes wall thickness composite joint skirt.
Background technology
Solid rocket motor case joint skirt is that the integral body of housing is extended, for realize that housing inter-stage section connects or with being connected of miscellaneous part, stand the multiple load such as axial compression, moment of flexure, shearing, interior pressure, stressing conditions more complicated, how in the situation that not increasing skirt section quality, simplify moulding process, and improve its performance, most important to the raising of whole motor body performance.Along with the development of material science, composite joint skirt is because its mass ratio is high, reliability is high, fabrication cycle is short, the low metal joint skirt that progressively replaced of cost.Composite joint skirt forming method can be divided into independent moulding and global formation two classes.Forming method is first to make a cylinder separately, more on request cylinder and housing is processed, and then adopts adhesive method that skirt body cover is installed on housing; The method is destructive large to the globality of fiber, is unsuitable for the performance of fibre strength.One of integral forming method is to overlap false end socket after housing has been wound around longitudinal layer again, and false end socket is with cylindrical section, and skirt section, is wound around according to the technological requirement in skirt section is whole, cuts end socket and the unnecessary cotton yarn tape of cylinder section after being wound around, and only retains skirt section; The method is large for large-scale case material waste.The another kind of method of global formation is winding, laying scheme, and housing has been wound around after longitudinal layer and part hoop layer, then makes compound skirt, and skirt is wound around by hoop and the pre-treated tape of lay is made into type; The method waste of material is little, good stability of the dimension, but high to equipment requirement, complex forming technology.The forming method of the change wall thickness composite joint skirt of therefore designing that a kind of technique is simple, with low cost, quality light and can straight forming is very necessary.
Summary of the invention
The object of the invention is to provide the forming method of the change wall thickness composite joint skirt that a kind of technique is simple, with low cost, quality light and can straight forming.
For achieving the above object, the present invention adopts following technical scheme:
A forming method that becomes wall thickness composite joint skirt, comprises the following steps:
A. according to the requirement of load, quality and appearance and size, by finite element analysis computation, laying angle and laying order are set, calculate size and the quantity of each angle laying thing;
B. according to the laying thing size calculating and quantity cutting laying thing;
C. make product forming mould;
D. laying thing is laid on mould core according to the distance of distance center line or bottom, reaches the 0.5-0.6 design number of plies;
E. under winding tension, with Filament-wound Machine, add and be pressed on laying surface, carry out precuring;
F. complete residue laying;
G. be wound around fiber pressurization, heating cure;
H. mould unloading, takes out goods;
I. sticky corner box.
Further, in described step a, described laying angle is 0 °, ± 15 °, and ± 30 °, ± 45 °, ± 60 ° and 90 °.
Further, in described step e, g, described Filament-wound Machine moulding pressure is 15N～18N.
Further, described laying thing is carbon fiber prepreg or glass fibre prepreg or unidirectional cloth, and described winding fiber is carbon fiber or glass fibre.
Further, in described step g, described heating cure is 80 ℃ and keeps 1 hour, is then warming up to 120 ℃ and keeps 3 hours, is then warming up to 150 ℃ and keeps 3 hours.
The present invention, by best laying angle and order are set, adopts manual laying to add Filament-wound Machine pressing technology, realizes at the complete composite joint skirt of the body formed front independent moulding of engine shell.Technique of the present invention is simple, with low cost, quality is light and can straight forming.
Accompanying drawing explanation
Fig. 1 becomes wall thickness composite joint skirt cross-sectional structure schematic diagram;
Fig. 2 is the partial enlarged drawing of Fig. 1;
Fig. 3 becomes wall thickness composite joint skirt forming die structure schematic diagram;
Fig. 4 becomes wall thickness composite joint skirt periphery laying schematic diagram.
In figure: 1 section of 1-laying position; 2 sections of 2-laying position; 3 sections of 3-laying position; 4 sections of 4-laying position; 5-central datum line; 6-composite joint skirt; 7-die surface horizontal datum.
The specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail, but this embodiment should not be construed as limitation of the present invention.
Embodiment 1
One, process conditions:
| Apart from front skirt end face 10mm place | ≥φ1200 |
| End face wall thickness | 11.2～12.5 |
| Skirt point is apart from skirt end inner face height | 250±0.5 |
| Quality | ≤15kg |
| Axial compression | >=30 tons |
The material adopting is carbon fiber prepreg, and pressurization fiber is glass fibre.
Two, technical process
A. according to the requirement of load, quality and appearance and size, application Hypermesh software is by finite element analysis computation, and laying angle is set to 0 °, and ± 15 °, ± 30 °, ± 45 °, ± 60 ° and 90 °, totally 51 layers.
Laying order and position are:
B. cutting prepreg
1) according to above-mentioned laying angle and laying position, with following formula, calculate each angle parallelogram prepreg cutting size: along machine direction length y ≈ (305-x)/cos α, be highly 250mm(handled easily), cutting number is z ≈ 1200 pi/2 50sin α, wherein x is distance center linear distance, and α is laying angle.
2) in conjunction with the size of raw material prepreg, each layer of prepreg of cutting;
For example: 30 ° of the second layers, 7 of cuttings are high is 250mm, 30 ° of prepregs that machine direction Y is 345mm.
C. make product type cavity mould
With reference to Figure of description 3, make product type cavity mould.
D. carbon fiber prepreg is adopted laying method to be laid on mold cavity relevant position, 25 layers of layings to the:
According to upper table laying order, shown in by specification accompanying drawing 4, each prepreg being laid in to right side distance center line 5 distances is X, on the mould of machine direction and 3 one-tenth α angles of die horizontal line, and 25 layers of this layings to the;
E. under 18N winding tension, with glass fiber winding, add and be pressed on laying surface, carry out precuring;
1) laying of having laid and mould are contained in numerical control winding machine;
2) adjust winding tension 18N; Design winding pattern, take annular line style as main;
3) Filament-wound Machine is on die surface carbon cloth premix laying surface, and the number of plies is 2 layers;
4) according to 80 ℃, keep 1 hour, be then warming up to 120 ℃ and keep carrying out for 3 hours precuring.
F. complete all layings:
According to laying order and laying position, complete residue laying.
G. be wound around glass fibre pressurization, heating cure:
1) with step e, adopt same procedure to be wound around pressurization;
2) according to 80 ℃, keep 1 hour, be then warming up to 120 ℃ and keep 3 hours, be then warming up to 150 ℃ of maintenances and finally solidify for 3 hours.
H. mould unloading, takes out goods;
I. sticky corner box.
The compound skirt quality that adopts the method to make is: 13.25kg is 1223mm apart from front skirt end face 10mm place diameter, and skirt point is 254mm apart from skirt end inner face height, 50 tons of axial compression test axial compression load-bearing.
One, process conditions
The material adopting is glass fibre prepreg, and pressurization fiber is glass fibre.
Two, technical process
A. according to the requirement of load, quality and appearance and size, application Hypermesh software is by finite element analysis computation, and laying angle is set to 0 °, and ± 15 °, ± 30 °, ± 45 °, ± 60 ° and 90 °, totally 46 layers.
Laying order and position are:
B. cutting prepreg
1) according to above-mentioned laying angle and laying position, according to following formula, calculate each angle parallelogram prepreg cutting size: along machine direction length y ≈ (305-x)/cos α, be highly 250mm(handled easily), cutting number is z ≈ 1000 pi/2 50sin α, wherein x is distance center linear distance, and α is laying angle.
2) in conjunction with the size of raw material prepreg, each layer of prepreg of cutting;
For example: 30 ° of the second layers, 7 of cuttings are high is 250mm, 30 ° of prepregs that machine direction Y is 346mm.
C. make product type cavity mould;
With reference to Figure of description 3, make product type cavity mould.
D. adopt laying method to be laid on mold cavity relevant position glass fibre prepreg, 27 layers of layings to the;
According to upper table laying order, by each prepreg being laid in shown in Fig. 4 to right side distance center line 5 distances, be X, on the mould of machine direction and 3 one-tenth α angles of die horizontal line, laying is altogether to the 27th layer;
E. under 15N winding tension, with glass fiber winding, add and be pressed on laying surface, carry out precuring;
1) laying of having laid and mould are contained in numerical control winding machine;
2) adjust winding tension 15N; Design winding pattern, take annular line style as main;
3) Filament-wound Machine is on die surface carbon cloth premix laying surface, and the number of plies is 3 layers;
4) according to 80 ℃, keep 1 hour, be then warming up to 120 ℃ and keep carrying out for 3 hours precuring.
F. complete all layings;
According to laying order and laying position, complete residue laying.
G. be wound around glass fibre pressurization, heating cure;
1) with step e, adopt same procedure to be wound around pressurization.
2) according to 80 ℃, keep 1 hour, be then warming up to 120 ℃ and keep 3 hours, be then warming up to 150 ℃ of maintenances and finally solidify for 3 hours.
H. mould unloading, takes out goods;
I. sticky corner box, forms final products.
The compound skirt quality that adopts the method to make is: 17.25kg is 1023mm apart from front skirt end face 10mm place diameter, and skirt point is 256mm apart from skirt end inner face height, 38 tons of axial compression test axial compression load-bearing.
The content not being described in detail in this description, belongs to the known prior art of those skilled in the art.
Claims (5)
1. a forming method that becomes wall thickness composite joint skirt, comprises the following steps:
A. according to the requirement of load, quality and appearance and size, by finite element analysis computation, laying angle and laying order are set, calculate size and the quantity of each angle laying thing;
B. according to the laying thing size going out by finite element analysis computation and quantity cutting laying thing;
C. make product forming mould;
D. laying thing is laid on mould core according to the distance of distance center line or bottom, reaches the 0.5-0.6 design number of plies going out by finite element analysis computation;
E. under winding tension, with Filament-wound Machine, add and be pressed on laying surface, carry out precuring;
F. complete residue laying;
G. be wound around fiber pressurization, heating cure;
H. mould unloading, takes out goods;
I. sticky corner box.
2. the forming method of change wall thickness composite joint skirt according to claim 1, is characterized in that: in described step a, described laying angle is 0 °, ± 15 °, and ± 30 °, ± 45 °, ± 60 ° and 90 °.
3. the forming method of change wall thickness composite joint skirt according to claim 1 and 2, is characterized in that: in described step e, g, described Filament-wound Machine moulding pressure is 15N～18N.
4. the forming method of change wall thickness composite joint skirt according to claim 3, is characterized in that: described laying thing is carbon fiber prepreg or glass fibre prepreg or unidirectional cloth, and described winding fiber is carbon fiber or glass fibre.
5. the forming method of change wall thickness composite joint skirt according to claim 4, is characterized in that: in described step g, described heating cure is 80 ℃ and keeps 1 hour, is then warming up to 120 ℃ and keeps 3 hours, is then warming up to 150 ℃ and keeps 3 hours.
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| CN103895314B (en) * | 2014-03-27 | 2016-03-16 | 奇瑞汽车股份有限公司 | A kind of preparation method of carbon fibre composite luggage carrier |
| CN103909658B (en) * | 2014-03-28 | 2017-04-19 | 湖北三江航天江北机械工程有限公司 | Composite material connecting skirt forming method and mold and inner rubber core mold forming mold |
| CN105082571B (en) * | 2015-08-24 | 2017-07-18 | 哈尔滨玻璃钢研究院 | For manufacturing compound material bolt blank forming method |
| CN106515045B (en) * | 2016-12-18 | 2019-02-15 | 湖北三江航天江北机械工程有限公司 | Composite material joint skirt automatic placement molding method |
| CN107127981A (en) * | 2017-06-26 | 2017-09-05 | 江苏恒神股份有限公司 | Carbon fiber composite material casing forming method |
| CN107901448B (en) * | 2017-11-09 | 2020-05-22 | 湖北三江航天江北机械工程有限公司 | Large-diameter composite skirt compression curing method |
| CN112571830A (en) * | 2020-11-30 | 2021-03-30 | 江苏新扬新材料股份有限公司 | U-shaped beam and manufacturing method thereof |
| CN113954272A (en) * | 2021-10-29 | 2022-01-21 | 开封市新亚实业有限公司 | Mold and method for manufacturing special-shaped composite material rotary body by using same |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090071592A1 (en) * | 2003-08-01 | 2009-03-19 | Alliant Techsystems Inc. | Apparatus and methods for forming composite stiffeners and reinforcing structures |
| CN102039684A (en) * | 2009-10-20 | 2011-05-04 | 维斯塔斯风力***有限公司 | A method for manufacturing a composite body and a composite body manufacturing arrangement |
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| JP3793652B2 (en) * | 1998-08-05 | 2006-07-05 | 天龍工業株式会社 | Core material containing carbon fiber, guide roller for flexible long sheet material using the same, and manufacturing method thereof |
-
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090071592A1 (en) * | 2003-08-01 | 2009-03-19 | Alliant Techsystems Inc. | Apparatus and methods for forming composite stiffeners and reinforcing structures |
| CN102039684A (en) * | 2009-10-20 | 2011-05-04 | 维斯塔斯风力***有限公司 | A method for manufacturing a composite body and a composite body manufacturing arrangement |
Non-Patent Citations (2)
| Title |
|---|
| 固体火箭发动机复合材料裙技术研究发展;李超等;《宇航材料工艺》;20030830;全文 * |
| 李超等.固体火箭发动机复合材料裙技术研究发展.《宇航材料工艺》.2003, |
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Effective date of registration: 20170718 Address after: 431400 Hubei province Wuhan Honggang village in Xinzhou District of Yangluo Economic Development Zone, Yangluo Development Zone, five floor, room 504 Patentee after: Aerospace Science and engineering Rocket Technology Co., Ltd. Address before: 432100 Hubei city of Xiaogan province Beijing Road No. 6 Patentee before: Hubei Sanjiang Aerospace Jiangbei Machinery Engineering Co., Ltd. |