CN104085120A - Manufacturing process of composite arm frame - Google Patents
Manufacturing process of composite arm frame Download PDFInfo
- Publication number
- CN104085120A CN104085120A CN201410300334.0A CN201410300334A CN104085120A CN 104085120 A CN104085120 A CN 104085120A CN 201410300334 A CN201410300334 A CN 201410300334A CN 104085120 A CN104085120 A CN 104085120A
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- China
- Prior art keywords
- buttress brace
- jib
- composite
- prepreg
- vacuum bag
- 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.)
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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
- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2012/00—Frames
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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)
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides a manufacturing process of a composite arm frame. The process comprises the following steps: laying a thin film on core molds; laying a plurality of layers of fiber prepreg on the outer surface of the thin film to form a first reinforced beam and a second reinforced beam by virtue of a rubber pre-suction process; positioning the first reinforced beam and the second reinforced beam; laying carbon fiber prepreg on the outer layers of the reinforced beams to form a pre-fabricated arm frame part; putting the pre-fabricated part into an outer mold, and carefully extracting the core molds of the reinforced beams; and wrapping the pre-fabricated part with a vacuum bag, heating and solidifying the pre-fabricated part wrapped with the vacuum bag, and solidifying, cooling and de-molding to obtain the composite arm frame. According to the process, the reinforced beams and a main beam are integrally solidified, ribs are perfectly embedded into the main beam, and the maximum performance of a composite material is played to the greatest extent. The layers of prepreg give full play to the characteristic of excellent designability of the composite material, the one-way prepreg provides the strength and the rigidity in the main stress direction, an internal one-way fiber layer is prevented from cracking by virtue of the fabric prepreg, and the impact strength can be improved and the cost can be reduced by virtue of the glass fiber prepreg.
Description
Technical field
The present invention relates to a kind of manufacture craft of composite jib.
Background technology
Jib is as the critical component of pump truck, it stretches the working range that has highly determined equipment, if employing conventional metals is structural material, in improving jib length, will greatly improve the weight of jib, thereby improved complete vehicle weight and comprehensive energy consumption, and conventional metals jib has relatively high expectations to vehicle frame, domain, complete-vehicle oil consumption is larger, mobility is poor, pump truck in the middle of long-term work, the problem such as metal jib easily produces fatigue rupture, corrosion.
High performance resin based composites, because of advantages such as it have high specific strength, high ratio modulus, corrosion-resistant, performance designability is good, is to substitute traditional material as the lightweight of jib and the optimal selection of overlength.
In the manufacture method of existing disclosed composite jib, mainly contain two classes, a class is hollow structure; One class is that main beam structure adds metal inner lining or composite material as liner, and liner and girder glued joint and form, and optimum performance and the structural stability of the not best performance composite of this two class formation are slightly poor.
Summary of the invention
The object of this invention is to provide a kind of manufacture craft of composite jib, can bring into play to greatest extent the maximum performance of composite, solve optimum performance and the slightly poor problem of structural stability of the not best performance composite existing in prior art.
Technical solution of the present invention is:
A manufacture craft for composite jib, comprises the following steps:
The sizing of S1, buttress brace: lay thin film on core, form one deck smooth can release layer, at release layer outer surface lay multi-layer fiber prepreg, form the first buttress brace through the pre-adhesive process of inhaling, use the same method and make the second buttress brace;
S2, girder sizing: by the first buttress brace and the second buttress brace location, at the outer lay carbon fiber prepreg of buttress brace, form jib prefabricated component;
S3, prefabricated component sizing: prefabricated component is put into external mold inside, and by the extraction careful core of buttress brace, coated outside vacuum bag;
S4, curing: the prefabricated component of parcel vacuum bag is heated up and solidified, and curing cooling and demolding obtains composite jib.
Further, step S1 is specially:
S11, mandrel surface are cleaned with acetone, then apply releasing agent;
S12, cover thin film mandrel surface paving, film adopts barrier film, vacuum bag or polyester film one wherein;
S13, cover multi-layer fiber prepreg film surface paving;
S14, at prepreg surface lay release cloth, inhale adhesive plaster, porose barrier film, vacuum bag, be evacuated to 0.05Mpa-0.1Mpa, and keep 20min-30min, inhale in advance adhesive process.
Further, step S2 is specially:
S21, by the first buttress brace and the second buttress brace registration, fill unidirectional fibre prepreg at connecting sewing place;
S22, cover carbon fiber prepreg buttress brace outer surface paving.
Further, step S3 is specially:
Clean with acetone on S31, external mold surface, then applies releasing agent;
S32, prefabricated component is put into external mold inside, and buttress brace core is carefully extracted out;
S33: be inserted in vacuum bag in buttress brace inside, surperficial lay airfelt outside, vacuum bag;
S34, is connected buttress brace inner vacuum bag with the vacuum bag on external mold surface.
Further, the curing step that heats up in step S4 is: be warming up to 120 DEG C-135 DEG C, and be incubated 90min-120min, curing equipment maybe can provide the pressure vessel of pressure and temp for autoclave.
Further, described buttress brace adopts multilayer carbon fiber prepreg, or employing carbon fiber prepreg and glass fibre, aramid fiber mixing prepreg, girder is multilayer carbon fibre composite, the inside and outside layer paving of girder is covered with carbon fibre fabric prepreg, Fabric prereg is plain weave, twill or satin fabric prepreg one wherein, intermediate layer paving be covered with 0 ° of unidirectional fibre prepreg, 90 ° of unidirectional fibre prepregs and ± 45 ° of unidirectional fibre prepregs.
Consider the costliness of autoclave equipment, the present invention also provides a kind of improved low-cost production technique.
A manufacture craft for improved low cost composite jib, comprises the following steps:
S1, buttress brace sizing: cover one deck expanded rubber mandrel surface paving, at rubber surface lay multi-layer fiber prepreg, form the first buttress brace through the pre-adhesive process of inhaling, use the same method and make the second buttress brace;
S2, girder sizing: by the first buttress brace and the second buttress brace location, at the outer lay carbon fiber prepreg of buttress brace, form jib prefabricated component;
S3, prefabricated component sizing: prefabricated component is put into external mold inside, parcel vacuum bag;
S4, curing: the prefabricated component of parcel vacuum bag is heated up and solidified, and curing cooling and demolding obtains composite jib.
Further, in step S1, the thickness of expanded rubber is 3mm-5mm, and expanded rubber is silicon rubber.
Further, in step S3, prefabricated component is put into external mold inside, parcel airfelt, with vacuum bag parcel external mold and core.
Further, step S4 is specially:
S41, by parcel vacuum bag prefabricated component connect vavuum pump, vacuumize;
S42, prefabricated component is put into the equipment of curing oven or baking oven or other heating that can provide;
S43, be warming up to 120 DEG C-135 DEG C, and be incubated 90min-120min;
S44, be cooled to 60 DEG C of demouldings and can obtain jib.
The manufacture craft of this kind of improved low cost composite jib, by core and external mold location, expanded rubber expanded by heating pressurizes and vacuumizes to prefabricated component to prefabricated component and pressurizes, up-to-standard jib not only can be provided, and solidification process avoided the expensive equipment such as autoclave, reduce cost of manufacture.
The invention has the beneficial effects as follows: solidify by buttress brace and girder one, rib is perfectly set in to girder inside, bring into play to greatest extent the maximum performance of composite.Multilayer prepreg is given full play to the good feature of designability of composite, unidirectional pre-immersion material provides the strength and stiffness that are mainly subject to force direction, and Fabric prereg prevents inner unidirectional fiber layers cracking, and aesthetic is provided, glass fibre prepreg can improve impact strength, reduces costs.Composite jib of the present invention, take full advantage of the advantages such as the high specific strength, high specific stiffness of composite, corrosion-resistant, endurance, make jib gentlier, longer, and the good damping characteristic of carbon fibre composite, reduce jib vibrations in use, improved service life and the security performance of pump truck.
Brief description of the drawings
Fig. 1 shows the schematic cross-section of a kind of composite jib of embodiment;
Wherein, 1-core, 2-film, 3-the first buttress brace, 4-the second buttress brace, 5-girder, 9-external mold.
Fig. 2 shows the curing schematic diagram of a kind of composite jib of embodiment;
Wherein, 3-the first buttress brace, 4-the second buttress brace, 5-girder, 6-inner vacuum bag, 7-external vacuum bag, 9-external mold.
Fig. 3 shows the schematic cross-section in the manufacturing process of a kind of improved low cost composite jib of embodiment;
Wherein, 1-core, 3-the first buttress brace, 4-the second buttress brace, 5-girder, 7-external vacuum bag, 8-expanded rubber, 9-external mold.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, technical scheme in the embodiment of the present invention is described in detail, but following embodiment and accompanying drawing are only to further illustrate of the present invention, and can not limit the present invention, the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
In the typical embodiment of one of the present invention, as shown in Figure 1, the manufacture craft of composite jib, provides a kind of composite jib, comprise the first composite buttress brace 3, the second composite buttress brace 4 and the 3rd composite girder 5, girder 5 solidifies and forms with buttress brace one.Buttress brace number can increase according to design, and manufacture craft is the same with the first buttress brace 3.
Buttress brace is mainly multilayer carbon fiber prepreg or carbon fiber prepreg and glass fibre, aramid fiber mixing prepreg, and the concrete number of plies and fiber laying are determined according to jib design strength.Buttress brace paving be covered with 0 ° of unidirectional fibre prepreg, 90 ° of unidirectional fibre prepregs and ± 45 ° of unidirectional fibre prepregs.
Girder 5 is other fibers of multilayer carbon fibre composite or similar carbon fiber strength modulus, and girder 5 ectonexine pavings are covered with carbon fibre fabric prepreg, and Fabric prereg can be according to being designed to plain weave, twill or satin fabric prepreg one wherein.Intermediate layer paving be covered with 0 ° of unidirectional fibre prepreg, 90 ° of unidirectional fibre prepregs and ± 45 ° of unidirectional fibre prepregs.
Embodiment 1
Fibrous material adopts carbon fiber one-way prepreg, carbon fiber twills prepreg, glass fibre prepreg.
As Fig. 1, shown in 2, clean with acetone on core 1 surface, then apply releasing agent, cover thin film 2 core 1 surface paving, film 2 can be barrier film, vacuum bag or polyester film one wherein, cover multi-layer fiber prepreg film 2 surface pavings, at prepreg surface lay release cloth, inhale adhesive plaster, porose barrier film, vacuum bag, be evacuated to 0.05mpa and keep 30min to form the first buttress brace 3, use the same method and make the second buttress brace 4, the first buttress brace 3 and the second buttress brace 4 are located, between gap fill up with unidirectional pre-immersion material, then at buttress brace surface lay down fibre prepreg, form girder 5, at the surperficial lay release cloth of girder 5, inhale adhesive plaster, porose barrier film, vacuum bag, be evacuated to 0.1mpa and keep 20min to form prefabricated component, clean with acetone on external mold 9 surfaces, then apply releasing agent, prefabricated component is put into external mold 9 inside, and buttress brace core 1 is carefully extracted out, be inserted in ring-shaped inner part vacuum bag 6 in buttress brace inside, in external mold surface lay airfelt, external vacuum bag 7, buttress brace inner vacuum bag 6 is connected with the external vacuum bag 7 on external mold surface, prefabricated component is put into autoclave and be warming up to 120 DEG C-135 DEG C, and be incubated 90min-120min, after the demoulding, get final product to obtain composite jib.
Embodiment 2
Fibrous material adopts carbon fiber one-way prepreg, carbon fiber twills prepreg.
As shown in Figure 3, clean with acetone on core 1 surface, then apply releasing agent, cover one deck silica gel thin film 8 core 1 surface paving, cover multi-layer fiber prepreg silica gel thin film 8 surface pavings, at prepreg surface lay release cloth, inhale adhesive plaster, porose barrier film, vacuum bag, be evacuated to 0.08Mpa and keep 20min to form the first buttress brace 3, use the same method and make the second buttress brace 4, the first buttress brace 3 and the second buttress brace 4 are located, between gap fill up with unidirectional pre-immersion material, then at buttress brace surface lay down fibre prepreg, form girder 5, at the surperficial lay release cloth of girder 5, inhale adhesive plaster, porose barrier film, vacuum bag, be evacuated to 0.1Mpa and keep 20min to form prefabricated component, clean with acetone on external mold 9 surfaces, then apply releasing agent, prefabricated component is put into external mold 9 inside, at the surperficial lay release cloth of external mold 9, external vacuum bag 7, put into baking oven, be evacuated to 0.08Mpa, be warming up to 120 DEG C-135 DEG C, and be incubated 90min-120min, after the demoulding, get final product to obtain composite jib.
Claims (10)
1. a manufacture craft for composite jib, is characterized in that, comprises the following steps:
The sizing of S1, buttress brace: lay thin film on core, form one deck smooth can release layer, at release layer outer surface lay multi-layer fiber prepreg, form the first buttress brace through the pre-adhesive process of inhaling, use the same method and make the second buttress brace;
S2, girder sizing: by the first buttress brace and the second buttress brace location, at the outer lay carbon fiber prepreg of buttress brace, form jib prefabricated component;
S3, prefabricated component sizing: prefabricated component is put into external mold inside, and by the extraction careful core of buttress brace, coated outside vacuum bag;
S4, curing: the prefabricated component of parcel vacuum bag is heated up and solidified, and curing cooling and demolding obtains composite jib.
2. the manufacture craft of composite jib as claimed in claim 1, is characterized in that, step S1 is specially:
S11, mandrel surface are cleaned with acetone, then apply releasing agent;
S12, cover thin film mandrel surface paving, film adopts barrier film, vacuum bag or polyester film one wherein;
S13, cover multi-layer fiber prepreg film surface paving;
S14, at prepreg surface lay release cloth, inhale adhesive plaster, porose barrier film, vacuum bag, be evacuated to 0.05Mpa-0.1Mpa, and keep 20min-30min, inhale in advance adhesive process.
3. the manufacture craft of composite jib as claimed in claim 2, is characterized in that, step S2 is specially:
S21, by the first buttress brace and the second buttress brace registration, fill unidirectional fibre prepreg at connecting sewing place;
S22, cover carbon fiber prepreg buttress brace outer surface paving.
4. the manufacture craft of composite jib as claimed in claim 3, is characterized in that, step S3 is specially:
Clean with acetone on S31, external mold surface, then applies releasing agent;
S32, prefabricated component is put into external mold inside, and buttress brace core is carefully extracted out;
S33: be inserted in vacuum bag in buttress brace inside, surperficial lay airfelt outside, vacuum bag;
S34, is connected buttress brace inner vacuum bag with the vacuum bag on external mold surface.
5. the manufacture craft of composite jib as described in claim 1-3 any one, it is characterized in that: the curing step that heats up in step S4 is: be warming up to 120 DEG C-135 DEG C, and being incubated 90min-120min, curing equipment maybe can provide the pressure vessel of pressure and temp for autoclave.
6. the manufacture craft of composite jib as claimed in claim 5, it is characterized in that: described buttress brace adopts multilayer carbon fiber prepreg, or employing carbon fiber prepreg and glass fibre, aramid fiber mixing prepreg, girder is multilayer carbon fibre composite, the inside and outside layer paving of girder is covered with carbon fibre fabric prepreg, Fabric prereg is plain weave, twill or satin fabric prepreg one wherein, intermediate layer paving be covered with 0 ° of unidirectional fibre prepreg, 90 ° of unidirectional fibre prepregs and ± 45 ° of unidirectional fibre prepregs.
7. a manufacture craft for improved low cost composite jib, is characterized in that, comprises the following steps:
S1, buttress brace sizing: cover one deck expanded rubber mandrel surface paving, at rubber surface lay multi-layer fiber prepreg, form the first buttress brace through the pre-adhesive process of inhaling, use the same method and make the second buttress brace;
S2, girder sizing: by the first buttress brace and the second buttress brace location, at the outer lay carbon fiber prepreg of buttress brace, form jib prefabricated component;
S3, prefabricated component sizing: prefabricated component is put into external mold inside, parcel vacuum bag;
S4, curing: the prefabricated component of parcel vacuum bag is heated up and solidified, and curing cooling and demolding obtains composite jib.
8. the manufacture craft of improved low cost composite jib as claimed in claim 7, is characterized in that: in step S1, the thickness of expanded rubber is 3mm-5mm, and expanded rubber is silicon rubber.
9. the manufacture craft of improved low cost composite jib as claimed in claim 8, is characterized in that: in step S3, prefabricated component is put into external mold inside, parcel airfelt, with vacuum bag parcel external mold and core.
10. the manufacture craft of improved low cost composite jib as described in claim 7-9 any one, is characterized in that, step S4 is specially:
S41, by parcel vacuum bag prefabricated component connect vavuum pump, vacuumize;
S42, prefabricated component is put into the equipment of curing oven or baking oven or other heating that can provide;
S43, be warming up to 120 DEG C-135 DEG C, and be incubated 90min-120min;
S44, be cooled to 60 DEG C of demouldings and can obtain jib.
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| CN201410300334.0A CN104085120A (en) | 2014-06-30 | 2014-06-30 | Manufacturing process of composite arm frame |
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| CN201410300334.0A CN104085120A (en) | 2014-06-30 | 2014-06-30 | Manufacturing process of composite arm frame |
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| CN104999672A (en) * | 2015-06-25 | 2015-10-28 | 航天材料及工艺研究所 | Molding method of double-curvature variable-section variable-thickness through beam |
| CN106548810A (en) * | 2017-01-16 | 2017-03-29 | 江苏恒神股份有限公司 | Carbon fibre composite indication control board operates skeleton |
| CN106564199A (en) * | 2015-10-13 | 2017-04-19 | 河南卓尔航空科技有限公司 | Closed-mould internal-pressure molding process for prepreg carbon fiber reinforced plastic |
| CN106564200A (en) * | 2015-10-13 | 2017-04-19 | 河南卓尔航空科技有限公司 | Mold closing core material interference pressure moulding process for prepreg carbon fiber reinforced plastic |
| CN107187020A (en) * | 2017-06-06 | 2017-09-22 | 中国电子科技集团公司第三十八研究所 | A kind of fibre reinforced composites 3D printing assistant formation method |
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| CN104999672A (en) * | 2015-06-25 | 2015-10-28 | 航天材料及工艺研究所 | Molding method of double-curvature variable-section variable-thickness through beam |
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| CN106564199A (en) * | 2015-10-13 | 2017-04-19 | 河南卓尔航空科技有限公司 | Closed-mould internal-pressure molding process for prepreg carbon fiber reinforced plastic |
| CN106564200A (en) * | 2015-10-13 | 2017-04-19 | 河南卓尔航空科技有限公司 | Mold closing core material interference pressure moulding process for prepreg carbon fiber reinforced plastic |
| CN106548810A (en) * | 2017-01-16 | 2017-03-29 | 江苏恒神股份有限公司 | Carbon fibre composite indication control board operates skeleton |
| CN107187020B (en) * | 2017-06-06 | 2019-09-10 | 中国电子科技集团公司第三十八研究所 | A kind of fibre reinforced composites 3D printing assistant formation method |
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