CN104369392A - Method for manufacturing composite material component - Google Patents
Method for manufacturing composite material component Download PDFInfo
- Publication number
- CN104369392A CN104369392A CN201410683928.4A CN201410683928A CN104369392A CN 104369392 A CN104369392 A CN 104369392A CN 201410683928 A CN201410683928 A CN 201410683928A CN 104369392 A CN104369392 A CN 104369392A
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- China
- Prior art keywords
- composite element
- mould
- bolster
- precast body
- gum
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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
- B29C70/36—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 impregnating by casting, e.g. vacuum casting
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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)
Abstract
The invention discloses a method for manufacturing a composite material component. The method comprises the following steps of S1: coating the side wall of a cavity of a die with a demolding agent; S2: paving a prefabricated body in the cavity: S21: paving continuous fibers on two layers on the outmost surface of the prefabricated body, and arranging a combined paved layer structure of the continuous fibers and chopped fibers between the two layers of the continuous fibers, and S22: positioning the prefabricated body in cavities formed in an upper die board and a lower die board, and performing high-temperature compaction; S3, sealing the upper die board and the lower die board for die assembling, locking the upper and lower die boards by a locking bolt; S41: heating the die to required glue injection temperature; S42: vacuuming through a glue outlet until the vacuum environment is stable; S5: injecting resin into the cavity, closing the glue outlet and a glue injection opening after the glue is completely discharged from the glue outlet, and stopping glue injection; and S6: heating and solidifying the die, and demolding to obtain a required product. The method has the beneficial effects that the composite material component meeting the requirement on the appearance is manufactured, so that the product is unlikely to deform, and the processing cost can be effectively lowered.
Description
Technical field
The present invention relates to a kind of field of compound material, be specifically related to a kind of method making composite element.
Background technology
Along with the development of aeronautical and space technology, aerospace vehicle is also faced with huge cost pressure, and weight is then the topmost cost source of Aero-Space.Along with the development of advanced composite material technology, composite consumption constantly increases, and composite comparatively aluminium alloy is light, is widely used in aerospace field.
Use a large amount of long and narrow variable cross-section composite elements (ratio that its length and width are thick is more than or equal to 500:20:10) at aerospace field, it mainly plays a part to tie up shape, belongs to not load-carrying construction parts.At present this type of long and narrow variable cross-section composite element can pass through aluminium alloy numerical control machine-shaping on the one hand, and another aspect can adopt autoclave press moulding mode shaping, then carries out secondary digital control processing and can obtain required composite element.
Usually, the density of the density ratio composite of aluminium alloy is large, and adopts aluminium alloy digital control processing processing cost high, and the component finished product after processing also easily deforms; Carry out secondary digital control processing again after adopting autoclave mold pressing, although reach the requirement of composite loss of weight, composite digital control processing cost is higher, and needs specialized nc machine tool, limits the popularization of this technique.
Therefore, long and narrow non-uniform member needs to adopt polymer matrix composites machine-shaping, and polymer matrix composites are divided into two kinds.A, continuous fiber machine-shaping, because fiber is different from the thermal coefficient of expansion of resin, (coefficient of expansion of resin is large and the thermal coefficient of expansion of fiber is little, the coefficient of expansion of resin is far longer than the thermal coefficient of expansion of fiber), and the net shape of polymer matrix composites is them is formed in high solidification temperature, in the process of cooling after solidification, because fiber is different from the thermal coefficient of expansion of resin, resin will shrink, and fibre deformation is little, fiber is by pressurized, resin tension, such fiber and interlaminar resin interface just have internal stress.And be directed to the composite of length and width thickness rate comparatively large (ratio that its length and width are thick is more than or equal to 500:20:10), and according to continuous fiber, the easy torsional deformation of composite element of manufacture.Therefore often adopt and manufacture the larger product of thickness width, the final numerical-control processing method that adopts is worked into required shape, size; Even if but like this, the product after processing also easily bends, the distortion such as distortion, and uncontrollable.B, the composite adopting chopped strand to manufacture, the problem of composite distortion can be solved completely, but because chopped strand performance is lower, manufacture process is short-and-medium, and to cut fiber-reinforced resin matrix compound material more crisp, easily there is brittle fracture equivalent damage during the demoulding, the performance requirement in composite material manufacturing process cannot be met.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art, provide a kind of method making composite element, can produce the composite element meeting appearance requirement, product is not yielding, effectively lowers processing cost simultaneously.
The object of the invention is to be achieved through the following technical solutions: a kind of method making composite element, the ratio that the length and width of described composite element are thick is more than or equal to 500:20:10, the method of described making composite element depends on composite element making mould and has come, composite element makes mould and comprises gum-injecting port, gum outlet and bolster, be provided with the die cavity that shape is consistent with composite element profile between bolster, it comprises the following steps:
S1: apply releasing agent in the cavity lateral of mould;
S2: precast body is laid in die cavity, it comprises following sub-step:
S21: prepared by precast body, the two-layer laying continuous fiber of outermost of precast body, places the combination ply angles of continuous fiber and chopped strand between two-layer continuous fiber,
S22: precast body is positioned on bolster, high temperature compacting;
S3: after bolster sealing matched moulds, lock with lock-screw;
S4: prepare before injecting glue, it comprises following two sub-steps:
S41: mould is warming up to required injecting glue temperature,
S42: vacuumized by gum outlet, discharge type intracavity gas, until vacuum is stablized;
S5: resin is injected die cavity by gum-injecting port, after the whole plastic emitting of gum outlet and after gum outlet bubble-free, closes gum outlet and gum-injecting port successively, stops resin by injection.
S6: after mould elevated cure, the demoulding can obtain required product.
Combination ply angles in described step S21 is that continuous fiber and chopped strand replace laying structure.
Setting agent or toughened film is adopted to be positioned on bolster by precast body in described step S22.
Mould elevated cure in described step S6 adopts and solidifies from heating mould.
Mould elevated cure in described step S6 adopts baking oven to be heating and curing.
The invention has the beneficial effects as follows:
1), relative aluminium alloy digital control processing part, same volume profile loss of weight more than 1/3, and without the need to the digital control processing work of complexity;
2), shaping relative to continuous fiber, avoid deformation of products, or secondary digital control processing, reduce cost;
3), polymer matrix composites are strengthened relative to chopped strand, product is strengthened jointly by continuous fiber and chopped strand, both the performance (as height stretching, compression performance) of partial continuous fiber had been remained, also the isotropism advantage of chopped strand has been played, solve the problem of the easy torsional deformation of composite element, shock resistance is good.
4), adopt this method, the shape of component product is determined by mold cavity, and product appearance accordance is good especially, and does not need into solidification of hot-press tank, and can adopt and be heating and curing from heating mould or baking oven, manufacturing cost is lower.
Accompanying drawing explanation
Fig. 1 is the structural representation of precast body in the embodiment of the present invention;
Fig. 2 is the cross section enlarged diagram of precast body in the embodiment of the present invention;
Fig. 3 is the flow chart that the present invention makes composite element method;
In figure, 1-precast body, 2-continuous fiber, 3-chopped strand.
Detailed description of the invention
Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail, but protection scope of the present invention is not limited to the following stated.
As shown in Figure 3, a kind of method making composite element, be applicable to the composite element that the thick ratio of length and width is more than or equal to 500:20:10, as shown in Figure 1, its cross section is step shape to the composite preform component that the present embodiment makes, long 2160mm, wide 70mm, stepped area thickness 1.56 ~ 3.8mm, component in the longitudinal direction geometry is asymmetric, also geometry is asymmetric in the direction of the width for component, the geometric shape that thick one end is thin in one end.The method of described making composite element depends on composite element making mould and has come, composite element makes mould and comprises gum-injecting port, gum outlet and bolster, mould allowable stress 0.3 ~ 2.3Mpa, be provided with the die cavity that shape is consistent with composite element profile between bolster, it comprises the following steps:
S1: apply releasing agent in the cavity lateral of mould;
S2: precast body is laid in die cavity, it comprises following sub-step:
S21: prepared by precast body, the two-layer laying continuous fiber of outermost (can be individual event fabric, plain cloth or satin fabric etc.) of precast body, the combination ply angles of continuous fiber and chopped strand (can be carbon felt, glass felt etc.) is placed between two-layer continuous fiber, continuous fiber anisotropy, for improving the mechanical property (as height stretching, compression performance) of composite products, chopped strand is isotropism, for laying internal stress between balanced continuous fiber, composite product is prevented to be out of shape
S22: adopt setting agent or toughened film to be positioned on bolster by precast body, high temperature compacting;
S3: after bolster sealing matched moulds, die cavity outer ring is sealed by double-layer seal bar, adopts the sealing of double-layer seal bar to ensure that mould has good sealing, locks with lock-screw;
S4: prepare before injecting glue, it comprises following two sub-steps:
S41: mould is warming up to required injecting glue temperature 115 DEG C (resin viscosity such as glue can be epoxy resin, span is at the resin of (0.1 ~ 1.5) PaS),
S42: vacuumized by gum outlet, discharge type intracavity gas, until vacuum is stablized;
S5: high temperature bismaleimide resin QY6421 is injected die cavity by gum-injecting port, injecting glue speed is 3c/s, and the injecting glue time is 15min, after the whole plastic emitting of gum outlet and after gum outlet bubble-free, closes gum outlet and gum-injecting port successively, stops resin by injection.
S6: after mould elevated cure, the demoulding can obtain required product.
As shown in Figure 2, the combination ply angles in described step S21 is that continuous fiber and chopped strand replace laying structure, and this ply angles is middle is continuous fiber, the chopped strand of laying up and down of continuous fiber.
Mould elevated cure in described step S6 adopts from heating mould solidification or adopts baking oven to be heating and curing.
Claims (6)
1. make a method for composite element, the ratio that the length and width of described composite element are thick is more than or equal to 500:
20:10, the method of described making composite element depends on composite element making mould and has come, composite element makes mould and comprises gum-injecting port, gum outlet and bolster, be provided with the die cavity that shape is consistent with composite element profile between bolster, it is characterized in that: it comprises the following steps:
S1: apply releasing agent in the cavity lateral of mould;
S2: precast body is laid in die cavity, it comprises following sub-step:
S21: prepared by precast body, the two-layer laying continuous fiber of outermost of precast body, places the combination ply angles of continuous fiber and chopped strand between two-layer continuous fiber,
S22: precast body is positioned in the die cavity of bolster setting, high temperature compacting;
S3: after bolster sealing matched moulds, lock with lock-screw;
S4: prepare before injecting glue, it comprises following two sub-steps:
S41: mould is warming up to required injecting glue temperature,
S42: vacuumized by gum outlet, discharge type intracavity gas, until vacuum is stablized;
S5: resin is injected die cavity by gum-injecting port, after the whole plastic emitting of gum outlet and after gum outlet bubble-free, closes gum outlet and gum-injecting port successively, stops resin by injection;
S6: after mould elevated cure, the demoulding can obtain required product.
2. a kind of method making composite element according to claim 1, is characterized in that: the combination ply angles in described step S21 is that continuous fiber and chopped strand replace laying structure.
3. a kind of method making composite element according to claim 1, is characterized in that: adopt setting agent to be positioned on bolster by precast body in described step S22.
4. a kind of method making composite element according to claim 1, is characterized in that: adopt toughened film to be positioned on bolster by precast body in described step S22.
5. a kind of method making composite element according to claim 1, is characterized in that: the mould elevated cure in described step S6 adopts and solidifies from heating mould.
6. a kind of method making composite element according to claim 1, is characterized in that: the mould elevated cure in described step S6 adopts baking oven to be heating and curing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410683928.4A CN104369392A (en) | 2014-11-25 | 2014-11-25 | Method for manufacturing composite material component |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410683928.4A CN104369392A (en) | 2014-11-25 | 2014-11-25 | Method for manufacturing composite material component |
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| Publication Number | Publication Date |
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| CN104369392A true CN104369392A (en) | 2015-02-25 |
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| CN201410683928.4A Pending CN104369392A (en) | 2014-11-25 | 2014-11-25 | Method for manufacturing composite material component |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106827587A (en) * | 2017-01-22 | 2017-06-13 | 厦门市豪尔新材料股份有限公司 | The forming method of application and its wing of the HSM techniques in wing shaping |
| CN108908965A (en) * | 2018-06-29 | 2018-11-30 | 江苏恒神股份有限公司 | A kind of forming method of the more wall construction products of carbon fiber |
| CN109732945A (en) * | 2019-01-24 | 2019-05-10 | 上海伽材新材料科技有限公司 | A kind of secondary forming process of composite material |
| CN110524757A (en) * | 2019-08-07 | 2019-12-03 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The flat-plate molded mold of PMI foam core and its application method |
| CN110524756A (en) * | 2019-08-07 | 2019-12-03 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Treadmill test part molding die, treadmill test part production method and treadmill test part |
| CN111098529A (en) * | 2019-11-28 | 2020-05-05 | 广东亚太新材料科技有限公司 | Fiber preform mold-entering positioning system and method |
| CN111959538A (en) * | 2020-08-28 | 2020-11-20 | 株洲时代新材料科技股份有限公司 | Fire-resistant wheel cover of rail transit vehicle and manufacturing method thereof |
-
2014
- 2014-11-25 CN CN201410683928.4A patent/CN104369392A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106827587A (en) * | 2017-01-22 | 2017-06-13 | 厦门市豪尔新材料股份有限公司 | The forming method of application and its wing of the HSM techniques in wing shaping |
| WO2018133177A1 (en) * | 2017-01-22 | 2018-07-26 | 厦门市豪尔新材料股份有限公司 | Application of hsm process in wing moulding and method for moulding wing |
| CN108908965A (en) * | 2018-06-29 | 2018-11-30 | 江苏恒神股份有限公司 | A kind of forming method of the more wall construction products of carbon fiber |
| CN109732945A (en) * | 2019-01-24 | 2019-05-10 | 上海伽材新材料科技有限公司 | A kind of secondary forming process of composite material |
| CN110524757A (en) * | 2019-08-07 | 2019-12-03 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | The flat-plate molded mold of PMI foam core and its application method |
| CN110524756A (en) * | 2019-08-07 | 2019-12-03 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Treadmill test part molding die, treadmill test part production method and treadmill test part |
| CN111098529A (en) * | 2019-11-28 | 2020-05-05 | 广东亚太新材料科技有限公司 | Fiber preform mold-entering positioning system and method |
| CN111098529B (en) * | 2019-11-28 | 2021-09-17 | 广东亚太新材料科技有限公司 | Fiber preform mold-entering positioning system and method |
| CN111959538A (en) * | 2020-08-28 | 2020-11-20 | 株洲时代新材料科技股份有限公司 | Fire-resistant wheel cover of rail transit vehicle and manufacturing method thereof |
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Application publication date: 20150225 |
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