CN113733594B - Method and die for manufacturing pre-impregnated glass roving wrinkle defect test piece - Google Patents
Method and die for manufacturing pre-impregnated glass roving wrinkle defect test piece Download PDFInfo
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- CN113733594B CN113733594B CN202110962615.2A CN202110962615A CN113733594B CN 113733594 B CN113733594 B CN 113733594B CN 202110962615 A CN202110962615 A CN 202110962615A CN 113733594 B CN113733594 B CN 113733594B
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- glass roving
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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
- B29C70/34—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 shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—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 shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
Abstract
The invention discloses a method and a die for manufacturing a pre-impregnated glass roving wrinkle defect test piece. The method comprises the following steps: a. paving more than one layer of straight pre-impregnated glass roving (1) in a lower die cavity; b. rolling the straight pre-impregnated glass roving for exhausting, paving a vacuum film outside the molded surface of the cavity, and vacuumizing the cavity; c. after vacuumizing, putting the lower die paved with the vacuum film into a curing furnace to perform pre-curing on the flat pre-impregnated glass roving (1); d. after the precuring is finished, pulling off the vacuum film, and placing a bulge (2) rolled by using the prepreg glass roving at the position of the prefabricated defect; e. continuously laying the prepreg glass roving on the flat prepreg glass roving with the bulges (2) until the thickness requirement of the test piece is met; f. and e, flattening the pre-impregnated glass roving laid in the step e, exhausting air, closing the mold and curing again. The invention realizes the accurate control of the defects in the prepreg glass roving belt test piece.
Description
Technical Field
The invention belongs to the technical field of composite material molding, and particularly relates to a method and a die for manufacturing a pre-impregnated glass roving wrinkle defect test piece.
Background
In helicopter production, in order to study the performance of composite parts in defects, for example: the influence of rigidity and fatigue needs to be made into a test piece made of the prepreg glass roving belt, so that the data of the influence of accumulated defects on the performance is determined, and the research on the subsequent part production is facilitated. However, at present, aiming at the manufacture of defects in a prepreg glass roving belt test piece, the process is just in the research and simulation stages, and the defects in the prepreg glass roving belt test piece made of the composite material are difficult to accurately control according to requirements, so that the fine research is hindered.
Disclosure of Invention
The purpose of the invention is: a method and a die for manufacturing a test piece with wrinkle defects of prepreg glass roving are provided. The invention realizes the accurate control of the defects in the prepreg glass roving belt test piece.
The technical scheme of the invention is as follows: a method of making a prepreg roving wrinkle defect test piece, comprising the steps of:
a. paving more than one layer of straight pre-impregnated glass roving in the lower die cavity;
b. rolling the straight pre-impregnated glass roving for exhausting, paving a vacuum film outside the molded surface of the cavity, and vacuumizing the cavity;
c. after vacuumizing, putting the lower die paved with the vacuum film into a curing furnace to perform pre-curing on the flat pre-impregnated glass roving;
d. after the precuring is finished, pulling the vacuum film, and placing a bulge rolled by using the prepreg glass roving at the position of the prefabricated defect;
e. continuously laying the prepreg glass roving on the flat prepreg glass roving with the bulge until the thickness requirement of the test piece is met;
f. and e, flattening the pre-impregnated glass roving laid in the step e, exhausting air, closing the mold and curing again.
In step c of the method for manufacturing the test piece with the wrinkle defect of the prepreg glass roving, the parameters of pre-curing are as follows:
the heating rate is as follows: 0.5-4 ℃/min, heat preservation temperature: 80 +/-5 ℃, and the heat preservation time is as follows: 2-2.5 hours, cooling mode: and (5) air cooling along with the furnace.
In step d of the method for manufacturing the prepreg roving wrinkle defect test piece, the rolling process of the bulge is as follows:
manufacturing a preliminary shape of a wrinkle defect by using a prepreg glass roving tape roll; curing the wrinkle defect with the preliminary shape; and refining the wrinkle defects after curing to meet the size requirement.
In the method for manufacturing the test piece with the wrinkle defect of the prepreg glass roving, refining is carried out by using a clamp repairing or grinding process.
In the method for manufacturing the pre-impregnated glass roving wrinkle defect test piece, for large-size wrinkle defects, the refining process adopts numerical control center processing.
In step f of the method for manufacturing the test piece with the wrinkle defect of the prepreg glass roving, the curing parameters are as follows:
heating to 80 + -5 deg.C at a temperature rising rate of not more than 1.5Mpa and not more than 2 deg.C/min, keeping the temperature for 30min + -15 min, pressurizing to 6MPa + -1 MPa, continuously heating to 125 + -5 deg.C, keeping the temperature and pressure for 135 + -30 min, and reducing the temperature to below 60 deg.C at a temperature falling rate of not more than 2 deg.C/min to release the pressure and mold.
The mold used in the method for manufacturing the pre-impregnated glass roving wrinkle defect test piece comprises an upper mold and a lower mold, wherein the upper surface of the lower mold is provided with a cavity, and the bottom surface of the upper mold can completely cover the cavity when the upper mold and the lower mold are closed.
In the mould used in the method for manufacturing the pre-impregnated glass roving wrinkle defect test piece, the upper surface of the lower mould positioned at the periphery of the cavity is also distributed with the gummosis grooves.
In the mould used in the method for manufacturing the test piece with the wrinkle defect of the prepreg glass roving, the distance between the glue flowing groove and the outer edge of the cavity is not more than 5mm.
The invention has the advantages that: according to the method, the pre-impregnated glass roving belt is firstly laid on the test piece for one time and then is pre-cured to obtain the substrate with certain hardness, and the rolled bulge is supported, so that the method can prevent the wrinkle defect from sinking during preparation, and effectively improves the accuracy of wrinkle defect preparation; in addition, the bulge has certain hardness after being solidified when being rolled; the method is beneficial to the precise processing of the external shape and size of the bulge, and prevents the bulge from deforming, thereby further ensuring the preparation precision of the wrinkle defect. Meanwhile, the glass roving belt is adopted to roll the protrusion, the formed wrinkle defect and a test piece form a unified whole by utilizing the principle of material consistency, and the forming quality of the wrinkle defect is ensured. Through the cooperative matching of the steps, the accurate control of the wrinkle defect preparation is finally realized.
Drawings
FIG. 1 is a schematic structural diagram of a prepreg glass roving tape wrinkle defect test piece manufactured according to the present invention;
FIG. 2 is a schematic view of the mold construction of the present invention;
fig. 3 is a plan view of the lower mold.
Reference numerals: 1-straight pre-impregnated glass roving, 2-protrusions, 3-upper die, 4-lower die and 5-gummosis groove.
Detailed Description
The invention is further illustrated by the following figures and examples, which are not to be construed as limiting the invention.
Example 1. A method for manufacturing a test piece for wrinkle defects of a prepreg glass roving comprises the following steps:
a. paving more than one layer of straight pre-impregnated glass roving 1 in the lower die cavity;
b. rolling the straight pre-impregnated glass roving for exhausting, paving a vacuum film outside the molded surface of the cavity, and vacuumizing the cavity;
c. after vacuumizing, putting the lower die paved with the vacuum film into a curing furnace to perform pre-curing on the flat pre-impregnated glass roving 1; and the glass roving is used for rolling, so that the defect later stage and a test piece can form a unified whole conveniently, a substrate is endowed with certain hardness and is used for supporting a bulge, and the defect can be formed into a required shape.
d. After the precuring is finished, pulling off the vacuum film, and placing a bulge 2 rolled by using the prepreg glass roving at the position of the prefabricated defect;
e. continuously laying the prepreg glass roving on the flat prepreg glass roving with the bulge 2 until the thickness requirement of the test piece is met;
f. c, flattening the pre-impregnated glass roving laid in the step e, exhausting air, closing the mold and curing again; the final prepreg roving tape wrinkle defect test piece is shown in fig. 1.
In the foregoing step c, the parameters of the pre-curing are as follows:
the heating rate is as follows: 0.5-4 ℃/min, heat preservation temperature: 80 +/-5 ℃, and the heat preservation time is as follows: 2-2.5 hours, cooling mode: and (5) air cooling along with the furnace. Compared with the subsequent curing process, the curing process is only cut off to 80 +/-5 ℃, so that the subsequent process cannot be influenced even if the temperature rise rate exceeds 2 ℃/min, and the efficiency can be improved by adopting the temperature rise rate exceeding 2 ℃/min.
In the foregoing step d, the rolling process of the protrusion 2 is as follows:
manufacturing a preliminary shape of a wrinkle defect by using a prepreg glass roving tape roll; curing the wrinkle defect with the preliminary shape; after curing, the wrinkle defects are refined to meet the size requirement. The cured product has certain hardness, and is beneficial to forming defects into required shapes.
The refining is carried out by a clinching or grinding process.
And for the large-size wrinkle defect, the refining process adopts numerical control center processing.
In the foregoing step f, the curing parameters are as follows:
heating to 80 + -5 deg.C at a temperature rising rate of not more than 1.5Mpa and not more than 2 deg.C/min, keeping the temperature for 30min + -15 min, pressurizing to 6MPa + -1 MPa, heating to 125 + -5 deg.C, keeping the temperature for 135 + -30 min, cooling to below 60 deg.C at a temperature falling rate of not more than 2 deg.C/min, and releasing the pressure. The method can ensure that the surface quality of the test piece is transparent and no white spots appear; if the pressure is over 80 degrees, the undesired wrinkle area can generate wrinkles; if the temperature rise rate is too fast, bubbles are generated, resulting in a large internal porosity. If the cooling rate is too fast, the test piece will be warped and deformed.
The mold used in the method for manufacturing the pre-impregnated glass roving wrinkle defect test piece comprises an upper mold 3 and a lower mold 4, wherein the upper surface of the lower mold 4 is provided with a cavity, and the bottom surface of the upper mold 3 can completely cover the cavity when the upper mold and the lower mold are closed.
And glue flowing grooves 5 are also distributed on the upper surface of the lower die 4 positioned at the periphery of the cavity.
The distance between the glue flowing groove 5 and the outer edge of the cavity is not more than 5mm.
Example 2. A method for manufacturing a test piece for wrinkle defects of a prepreg glass roving comprises the following steps:
1. paving four layers of flat pre-impregnated glass roving in a cavity of a lower die 4 in the figure 2;
2. manufacturing a vacuum bag, vacuumizing for 30min, disassembling the vacuum bag, rolling the bubbles which are not removed in the pre-impregnated glass roving by using a rolling plate, and discharging the bubbles;
3. re-manufacturing a vacuum bag, placing the part in a curing furnace, raising the temperature to 80 +/-5 ℃ at the temperature rise rate of 0.5-4 ℃/min, preserving the heat for 2-2.5 hours, cooling and discharging;
4. rolling the pre-impregnated glass roving into the required wrinkle defect size (the size comprises the length, the width and the height), and placing the wrinkle defect size at the required position of the defect;
5. continuously paving and pasting the residual prepreg glass roving, rolling the prepreg glass roving except the defect placement area by using a rolling plate, and discharging air bubbles;
6. closing the die, namely fixing an upper die 3 in the figure 2 with a lower die 4 in the figure 2 through a positioning pin;
7. placing into a hot press, heating to 80 + -5 deg.C at a temperature rising rate of 2 deg.C/min under a contact pressure of 1.5Mpa or less, holding for 30min + -15 min, pressurizing to 6MPa + -1 MPa, heating to 125 + -5 deg.C, holding for 135 + -30 min, cooling to 60 deg.C at a temperature lowering rate of 2 deg.C/min, and demolding.
8. Trimming: trimming the burrs orderly along the cutting line of the part; finally, a test piece capable of accurately controlling the length lambda, the height delta and the angle theta of the inner fold defect is prepared.
Claims (9)
1. A method for manufacturing a test piece for wrinkle defect of a prepreg glass roving is characterized by comprising the following steps: the method comprises the following steps:
a. paving more than one layer of straight pre-impregnated glass roving (1) in a lower die cavity;
b. rolling the straight pre-impregnated glass roving for exhausting, paving a vacuum film outside the molded surface of the cavity, and vacuumizing the cavity;
c. after vacuumizing, putting the lower die paved with the vacuum film into a curing furnace to pre-cure the flat pre-impregnated glass roving (1);
d. after the precuring is finished, pulling out the vacuum film, and placing a bulge (2) rolled by using the prepreg glass roving at the position of the prefabricated defect;
e. continuously laying the prepreg glass roving on the flat prepreg glass roving with the bulges (2) until the thickness requirement of the test piece is met;
f. and e, flattening the pre-impregnated glass roving laid in the step e, exhausting air, closing the mold and curing again.
2. The method of manufacturing a prepreg roving wrinkle defect test piece as claimed in claim 1, wherein in step c, the parameters of pre-curing are as follows:
the heating rate is as follows: 0.5-4 ℃/min, heat preservation temperature: 80 +/-5 ℃, and the heat preservation time is as follows: 2-2.5 hours, cooling mode: and (5) air cooling along with the furnace.
3. The method for manufacturing a prepreg roving wrinkle defect test piece as claimed in claim 1, wherein in step d, the protrusions (2) are rolled as follows:
manufacturing a preliminary shape of a wrinkle defect by using a prepreg glass roving tape roll; curing the wrinkle defect with the preliminary shape; and refining the wrinkle defects after curing to meet the size requirement.
4. The method of manufacturing a prepreg roving crimp defect trial of claim 3 wherein the refining is performed using a clinching or grinding process.
5. The method of claim 3, wherein for large size crimp defects, the refining process uses a NC center process.
6. The method of manufacturing a prepreg roving wrinkle defect test piece as claimed in claim 1, wherein in step f, the curing parameters are as follows:
heating to 80 + -5 deg.C at a temperature rising rate of not more than 1.5Mpa and not more than 2 deg.C/min, keeping the temperature for 30min + -15 min, pressurizing to 6MPa + -1 MPa, continuously heating to 125 + -5 deg.C, keeping the temperature and pressure for 135 + -30 min, and reducing the temperature to below 60 deg.C at a temperature falling rate of not more than 2 deg.C/min to release the pressure and mold.
7. A mould used in the method for manufacturing the test piece with the wrinkle defect of the pre-impregnated glass roving as claimed in the claims 1 to 6, characterized by comprising an upper mould (3) and a lower mould (4), wherein the upper surface of the lower mould (4) is provided with a cavity, and the bottom surface of the upper mould (3) can completely cover the cavity when the upper mould and the lower mould are closed.
8. The mould for manufacturing the test piece of the pre-impregnated glass roving with the wrinkle defect in the claim 7 is characterized in that the upper surface of the lower mould (4) at the periphery of the cavity is also distributed with glue flowing grooves (5).
9. The mold for manufacturing the test piece of the prepreg glass roving with the wrinkle defect as set forth in claim 8, characterized in that the distance between the rubber flowing groove (5) and the outer edge of the cavity is not more than 5mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110962615.2A CN113733594B (en) | 2021-08-20 | 2021-08-20 | Method and die for manufacturing pre-impregnated glass roving wrinkle defect test piece |
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| CN202110962615.2A CN113733594B (en) | 2021-08-20 | 2021-08-20 | Method and die for manufacturing pre-impregnated glass roving wrinkle defect test piece |
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| CN113733594A CN113733594A (en) | 2021-12-03 |
| CN113733594B true CN113733594B (en) | 2023-03-28 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2769834A1 (en) * | 2013-02-26 | 2014-08-27 | Airbus Operations, S.L. | An artificially defective cured laminate. |
| EP3379231A2 (en) * | 2017-03-21 | 2018-09-26 | Bell Helicopter Textron Inc. | Methods of making a tubular specimen with a predetemined wrinkle defect |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102975376A (en) * | 2012-12-11 | 2013-03-20 | 成都飞机工业（集团）有限责任公司 | Split die vacuum bag-autoclave forming method of irregular composite material |
| CN204773155U (en) * | 2015-04-07 | 2015-11-18 | 中国直升机设计研究所 | Combined material paddle forming die |
| CN105823666A (en) * | 2016-05-16 | 2016-08-03 | 中国航空工业集团公司西安飞机设计研究所 | Method for prefabricating composite laminate special-shaped layering defects |
| CN205853389U (en) * | 2016-07-20 | 2017-01-04 | 保定华翼风电叶片研究开发有限公司 | A kind of preparation facilities of extruded bright finish uniform thickness fiberglass test flat board |
| US10744727B2 (en) * | 2017-03-21 | 2020-08-18 | Textron Innovations Inc. | Methods of making a specimen with a predetermined wrinkle defect |
| CN108819286A (en) * | 2018-04-25 | 2018-11-16 | 成都飞机工业（集团）有限责任公司 | A kind of embedded copper band and material prepreg are total to adhering method |
| CN112248482B (en) * | 2020-08-25 | 2022-04-12 | 航天材料及工艺研究所 | Preparation method of internal delamination defect of composite material |
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2021
- 2021-08-20 CN CN202110962615.2A patent/CN113733594B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2769834A1 (en) * | 2013-02-26 | 2014-08-27 | Airbus Operations, S.L. | An artificially defective cured laminate. |
| EP3379231A2 (en) * | 2017-03-21 | 2018-09-26 | Bell Helicopter Textron Inc. | Methods of making a tubular specimen with a predetemined wrinkle defect |
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