CN102700150A - 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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- CN102700150A CN102700150A CN2012101476726A CN201210147672A CN102700150A CN 102700150 A CN102700150 A CN 102700150A CN 2012101476726 A CN2012101476726 A CN 2012101476726A CN 201210147672 A CN201210147672 A CN 201210147672A CN 102700150 A CN102700150 A CN 102700150A
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- ply stacking
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- shop layer
- angle
- fiber
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 239000002131 composite material Substances 0.000 title claims abstract description 20
- 238000000465 moulding Methods 0.000 title claims abstract description 11
- 239000000835 fiber Substances 0.000 claims abstract description 18
- 238000004804 winding Methods 0.000 claims abstract description 17
- 238000004519 manufacturing process Methods 0.000 claims abstract description 8
- 238000010438 heat treatment Methods 0.000 claims abstract description 7
- 238000005520 cutting process Methods 0.000 claims description 12
- 239000003365 glass fiber Substances 0.000 claims description 12
- 238000010792 warming Methods 0.000 claims description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 238000004458 analytical method Methods 0.000 claims description 4
- 239000004744 fabric Substances 0.000 claims description 4
- GNFTZDOKVXKIBK-UHFFFAOYSA-N 3-(2-methoxyethoxy)benzohydrazide Chemical compound COCCOC1=CC=CC(C(=O)NN)=C1 GNFTZDOKVXKIBK-UHFFFAOYSA-N 0.000 claims description 2
- 238000010008 shearing Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 5
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 238000012669 compression test Methods 0.000 description 2
- 238000005755 formation reaction Methods 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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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 the housing forming method, be specifically related to a kind of forming method that becomes wall thickness composite joint skirt.
Background technology
The solid rocket motor case joint skirt is that the integral body of housing is extended; Be used to realize housing inter-stage section connects or with being connected of miscellaneous part, stand multiple load such as axial compression, moment of flexure, shearing, interior pressure, the stressing conditions more complicated; How under the situation that does not increase the 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, the composite joint skirt is because of 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 two types of independent moulding and global formations.Forming method is to make a cylinder earlier separately, on request cylinder and housing is processed again, adopts adhesive method to install to skirt body cover on the housing then; This method is destructive big to the globality of fiber, is unsuitable for the performance of fibre strength.One of integral forming method is to overlap false end socket again after housing has twined longitudinal layer, and false end socket has cylindrical section, and promptly twine according to the technological requirement in skirt section is whole in the skirt section, cuts end socket and the unnecessary cotton yarn tape of tube section after having twined, and only keeps the skirt section; This method is big for large-scale case material waste.The another kind of method of global formation is winding, shop layered scheme, after promptly housing has twined longitudinal layer and part hoop layer, makes compound skirt again, and skirt is twined by hoop and lay preimpregnation adhesive tape is made moulding; This method waste of material is little, and dimensional stability is good, but high to equipment requirements, complex forming technology.Therefore design that a kind of technology is simple, with low cost, the forming method of light weight and change wall thickness composite joint skirt that can straight forming is very necessary.
Summary of the invention
The object of the invention is to provide that a kind of technology is simple, with low cost, the forming method of light weight and change wall thickness composite joint skirt that can straight forming.
For realizing above-mentioned purpose, the present invention adopts following technical scheme:
A kind of forming method that becomes wall thickness composite joint skirt may further comprise the steps:
A. according to the requirement of load, quality and appearance and size,, shop layer angle and shop layer order are set, calculate the size and the quantity of each angle shop layer thing through finite element analysis computation;
B. according to shop layer thing size that calculates and quantity cutting shop layer thing;
C. manufacturing articles mould;
D. will spread layer thing and be laid on the mould core, reach the 0.5-0.6 design number of plies according to the distance of distance center line or bottom;
E. under winding tension, twine to add with fiber and be pressed on the laminar surface of shop, carry out precuring;
F. accomplish residue shop layer;
G. twine the fiber pressurization, heating cure;
H. mould unloading takes out goods;
I. sticking angle box.
Further, among the said step a, said shop layer angle is 0 °, ± 15 °, and ± 30 °, ± 45 °, ± 60 ° and 90 °.
Further, among said step e, the g, it is 15N～18N that said fiber twines moulding pressure.
Further, said shop layer thing is carbon fiber prepreg or glass fibre prepreg or unidirectional cloth, and said winding fiber is carbon fiber or glass fibre.
Further, in the said step g, said heating cure is 80 ℃ and kept 1 hour, then is warming up to 120 ℃ and keeps 3 hours, is warming up to 150 ℃ then and keeps 3 hours.
The present invention is through being provided with best shop layer angle and order, and the manual shop of employing layer adds fiber and twines pressing technology, is implemented in the body formed preceding complete composite joint skirt of moulding separately of engine shell.Technology of the present invention is simple, with low cost, light weight and can straight forming.
Description of drawings
Fig. 1 becomes wall thickness composite joint skirt cross-sectional structure sketch map;
Fig. 2 is the partial enlarged drawing of Fig. 1;
Fig. 3 becomes wall thickness composite joint skirt forming die structure sketch map;
Fig. 4 becomes wall thickness composite joint skirt periphery shop layer sketch map.
Among the figure: 1-spreads 1 section of layer position; 2-spreads 2 sections of layer position; 3-spreads 3 sections of layer position; 4-spreads 4 sections of layer position; The 5-central datum line; 6-composite joint skirt; 7-die surface horizontal datum.
The specific embodiment
Below in conjunction with accompanying drawing and specific embodiment the present invention is made further detailed description, but this embodiment should not be construed as limitation of the present invention.
Embodiment 1
One, process conditions:
| Apart from preceding skirt end face 10mm place | ≥φ1200 |
| The end face wall thickness | 11.2～12.5 |
| The skirt point is apart from skirt end inner face height | 250±0.5 |
| Quality | ≤15kg |
| Axial compression | >;=30 tons |
The material that adopts is a carbon fiber prepreg, and the pressurization fiber is a glass fibre.
Two, technical process
A. according to the requirement of load, quality and appearance and size, use Hypermesh software through finite element analysis computation, shop layer angle is set to 0 °, and ± 15 °, ± 30 °, ± 45 °, ± 60 ° and 90 °, totally 51 layers.
Shop layer order and position are:
B. cutting prepreg
1) according to above-mentioned shop layer angle and layer position, shop; Calculate each angle parallelogram prepreg cutting size with formula: along machine direction length y ≈ (305-x)/cos α; Highly be 250mm (handled easily); The cutting number is z ≈ 1200 pi/2 50sin α, and wherein x is the distance center linear distance, and α is shop layer angle.
2) size of combination raw material prepreg, each layer of cutting prepreg;
For example: 30 ° of the second layers, 7 of cuttings are high to be 250mm, machine direction Y is 30 ° of prepregs of 345mm.
C. manufacturing articles type cavity mould
With reference to Figure of description 3 manufacturing articles type cavity moulds.
D. adopt the shop layer method to be laid on the mold cavity relevant position carbon fiber prepreg, the shop layer is to the 25th layer:
According to last table shop layer order, shown in the by specification accompanying drawing 4 each prepreg is laid in right side distance center line 5 distances and is X, on the mould of machine direction and 3 one-tenths α angles of die horizontal line, this time spread layer to the 25th layer;
E. under the 18N winding tension, twine to add with glass fibre and be pressed on the laminar surface of shop, carry out precuring;
1) shop layer and the mould that will lay completion are contained on the numerical control winding machine;
2) adjustment winding tension 18N; The design winding pattern is main with annular line style;
3) fiber is wrapped in die surface carbon cloth premix shop laminar surface, and the number of plies is 2 layers;
4) kept 1 hour according to 80 ℃, then be warming up to 120 ℃ and keep carrying out in 3 hours precuring.
F. accomplish all shop layers:
Accomplish residue shop layer according to shop layer order and layer position, shop.
G. twine the glass fibre pressurization, heating cure:
1) adopt same procedure to twine pressurization with step e;
2) kept 1 hour according to 80 ℃, then be warming up to 120 ℃ and kept 3 hours, be warming up to 150 ℃ then and keep finally solidifying in 3 hours.
H. mould unloading takes out goods;
I. sticking angle box.
The compound skirt quality that adopts this method to make is: 13.25kg, and diameter is 1223mm apart from preceding skirt end face 10mm place, the 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 that adopts is the glass fibre prepreg, and the pressurization fiber is a glass fibre.
Two, technical process
A. according to the requirement of load, quality and appearance and size, use Hypermesh software through finite element analysis computation, shop layer angle is set to 0 °, and ± 15 °, ± 30 °, ± 45 °, ± 60 ° and 90 °, totally 46 layers.
Shop layer order and position are:
B. cutting prepreg
1) according to above-mentioned shop layer angle and layer position, shop; Calculate each angle parallelogram prepreg cutting size according to formula: along machine direction length y ≈ (305-x)/cos α; Highly be 250mm (handled easily); The cutting number is z ≈ 1000 pi/2 50sin α, and wherein x is the distance center linear distance, and α is shop layer angle.
2) size of combination raw material prepreg, each layer of cutting prepreg;
For example: 30 ° of the second layers, 7 of cuttings are high to be 250mm, machine direction Y is 30 ° of prepregs of 346mm.
C. manufacturing articles type cavity mould;
With reference to Figure of description 3 manufacturing articles type cavity moulds.
D. adopt the shop layer method to be laid on the mold cavity relevant position glass fibre prepreg, the shop layer is to the 27th layer;
According to last table shop layer order, each prepreg is laid in right side distance center line 5 distances is X by shown in Figure 4, on the mould of machine direction and 3 one-tenths α angles of die horizontal line, spread layer altogether to the 27th layer;
E. under the 15N winding tension, twine to add with glass fibre and be pressed on the laminar surface of shop, carry out precuring;
1) shop layer and the mould that will lay completion are contained on the numerical control winding machine;
2) adjustment winding tension 15N; The design winding pattern is main with annular line style;
3) fiber is wrapped in die surface carbon cloth premix shop laminar surface, and the number of plies is 3 layers;
4) kept 1 hour according to 80 ℃, then be warming up to 120 ℃ and keep carrying out in 3 hours precuring.
F. accomplish all shop layers;
Accomplish residue shop layer according to shop layer order and layer position, shop.
G. twine the glass fibre pressurization, heating cure;
1) adopt same procedure to twine pressurization with step e.
2) kept 1 hour according to 80 ℃, then be warming up to 120 ℃ and kept 3 hours, be warming up to 150 ℃ then and keep finally solidifying in 3 hours.
H. mould unloading takes out goods;
I. sticking angle box forms final products.
The compound skirt quality that adopts this method to make is: 17.25kg, and diameter is 1023mm apart from preceding skirt end face 10mm place, the skirt point is 256mm apart from skirt end inner face height, 38 tons of axial compression test axial compression load-bearing.
Make the content of detailed description in this specification, belong to the those skilled in the art known prior art.
Claims (5)
1. forming method that becomes wall thickness composite joint skirt may further comprise the steps:
A. according to the requirement of load, quality and appearance and size,, shop layer angle and shop layer order are set, calculate the size and the quantity of each angle shop layer thing through finite element analysis computation;
B. according to shop layer thing size that calculates and quantity cutting shop layer thing;
C. manufacturing articles mould;
D. will spread layer thing and be laid on the mould core, reach the 0.5-0.6 design number of plies according to the distance of distance center line or bottom;
E. under winding tension, twine to add with fiber and be pressed on the laminar surface of shop, carry out precuring;
F. accomplish residue shop layer;
G. twine the fiber pressurization, heating cure;
H. mould unloading takes out goods;
I. sticking angle box.
2. the forming method of change wall thickness composite joint skirt according to claim 1 is characterized in that: among the said step a, said shop layer 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: among said step e, the g, it is 15N～18N that said fiber twines moulding pressure.
4. the forming method of change wall thickness composite joint skirt according to claim 3 is characterized in that: said shop layer thing is carbon fiber prepreg or glass fibre prepreg or unidirectional cloth, and said 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 the said step g, said heating cure is 80 ℃ and kept 1 hour, then is warming up to 120 ℃ and keeps 3 hours, is warming up to 150 ℃ then and keeps 3 hours.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210147672.6A CN102700150B (en) | 2012-05-14 | 2012-05-14 | Molding method of wall-thickness-variable composite connection skirt |
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| CN201210147672.6A CN102700150B (en) | 2012-05-14 | 2012-05-14 | Molding method of wall-thickness-variable composite connection skirt |
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| CN102700150B CN102700150B (en) | 2014-04-16 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103895314A (en) * | 2014-03-27 | 2014-07-02 | 奇瑞汽车股份有限公司 | Preparation method for carbon fiber composite material luggage rack |
| CN103909658A (en) * | 2014-03-28 | 2014-07-09 | 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 |
| CN105082571A (en) * | 2015-08-24 | 2015-11-25 | 哈尔滨玻璃钢研究院 | Blank forming method for manufacturing composite material bolt |
| CN106515045A (en) * | 2016-12-18 | 2017-03-22 | 湖北三江航天江北机械工程有限公司 | Automatic laying molding method for composite connection skirt |
| 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 |
| CN107901448A (en) * | 2017-11-09 | 2018-04-13 | 湖北三江航天江北机械工程有限公司 | The compound skirt cure under pressure method of major diameter |
| 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 |
| CN115592979A (en) * | 2022-10-21 | 2023-01-13 | 长春长光宇航复合材料有限公司（Cn） | A kind of preparation method of axial low thermal expansion coefficient composite lens barrel |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103895314A (en) * | 2014-03-27 | 2014-07-02 | 奇瑞汽车股份有限公司 | Preparation method for carbon fiber composite material luggage rack |
| CN103909658A (en) * | 2014-03-28 | 2014-07-09 | 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 |
| CN105082571A (en) * | 2015-08-24 | 2015-11-25 | 哈尔滨玻璃钢研究院 | Blank forming method for manufacturing composite material bolt |
| 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 |
| CN106515045A (en) * | 2016-12-18 | 2017-03-22 | 湖北三江航天江北机械工程有限公司 | Automatic laying molding method for composite connection skirt |
| 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 |
| CN107901448A (en) * | 2017-11-09 | 2018-04-13 | 湖北三江航天江北机械工程有限公司 | The compound skirt cure under pressure method of major diameter |
| 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 |
| CN115592979A (en) * | 2022-10-21 | 2023-01-13 | 长春长光宇航复合材料有限公司（Cn） | A kind of preparation method of axial low thermal expansion coefficient composite lens barrel |
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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. |