CN110815632A - Single-diaphragm preforming method for composite material lamination - Google Patents
Single-diaphragm preforming method for composite material lamination Download PDFInfo
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- CN110815632A CN110815632A CN201910971128.5A CN201910971128A CN110815632A CN 110815632 A CN110815632 A CN 110815632A CN 201910971128 A CN201910971128 A CN 201910971128A CN 110815632 A CN110815632 A CN 110815632A
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- composite material
- forming tool
- preforming
- auxiliary supporting
- flat plate
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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
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/06—Making preforms by moulding the material
- B29B11/12—Compression moulding
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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
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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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/386—Automated tape laying [ATL]
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- 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
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
Abstract
The invention belongs to the technical field of composite material manufacturing, and relates to a single-diaphragm preforming method for composite material lamination, which comprises the following steps: the silicone rubber membrane [1] is hung above the vacuum working platform [4], and a product forming tool [3] and a composite material flat plate lamination [5] are placed at the central position of the vacuum working platform [4 ]; placing the auxiliary supporting devices [2] at two sides of the product forming tool [3 ]; heating, and raising the temperature to 55-80 ℃ for the composite material flat plate lamination [5 ]; after the temperature reaches the equilibrium, starting to apply vacuum pressure; the auxiliary supporting device is adopted to balance the normal pressure received by the composite material flat plate lamination in the preforming process, the generation of layering wrinkles can be effectively prevented, and the auxiliary supporting device has good applicability for higher forming tools and products. The accurate pressurization control can be realized by calculation according to the elasticity and the weight of the silicon rubber.
Description
Technical Field
The invention belongs to the composite material manufacturing technology, and relates to a single-diaphragm preforming method for composite material lamination.
Background
The traditional composite material manufacturing process adopts a manual paving mode to finish paving on a corresponding forming tool, then pastes a vacuum bag for packaging, and then enters an autoclave for curing. With the large application of the composite material in the aircraft structural member and the gradual upsizing and complication of the structural member, the development of the application of the composite material is limited by the problems of low production efficiency, unstable molding quality and the like of the traditional prepreg/autoclave process due to the adoption of manual laying, so that the automatic tape laying technology of the composite material part is rapidly developed. However, the automatic tape laying machine cannot manufacture a member having a large curvature due to the limitation of the automatic tape laying machine. In order to apply the automatic tape laying technique to the manufacture of complex configuration composite structural members, patent CN106142587B discloses a composite double-bag thermal diaphragm preforming method: the diaphragm bag adopted by the method is a disposable product, two layers of diaphragm bags need to be laid on the whole preforming device before preforming is carried out each time, and the diaphragm bags need to be kept in a tensioning state. The operation is complicated, and the material waste is serious; because the diaphragm bag is a plastic film, the risk of bag explosion is high in the preforming process; because prepreg spreads the layer and encapsulates in two diaphragm bags, its relation with preforming frock is difficult to the accuracy and guarantees, and the preforming body after the completion need carry out the secondary and shift, fixes a position to the shaping frock on, probably has error accumulation location inaccuracy and preforming body and tears the deformation problem.
Disclosure of Invention
The purpose of the invention is: the preforming method of the composite material lamination is provided to solve the technical problems of complex operation, high cost and unstable quality in the prior art.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a method of single membrane preforming of a composite material laminate, the method comprising the steps of:
firstly, a silicon rubber film 1 is hung above a vacuum working platform 4, and a product forming tool 3 and a composite material flat plate lamination 5 are placed at the central position of the vacuum working platform 4; placing the auxiliary supporting devices 2 at two sides of the product forming tool 3;
step two, heating and raising the temperature, namely raising the temperature of the composite material flat plate lamination 5 to 55-80 ℃;
step three, after the temperature reaches the balance, starting to apply vacuum pressure;
and step four, cooling and releasing pressure to complete preforming.
The interval of shaping frock 3 and the optional position of auxiliary stay device 2, auxiliary stay device 2's height, the height of shaping frock 3, the following relation should be satisfied to the three:
h is more than H +0.4L and less than or equal to 2L, L is the distance between the forming tool 3 and the auxiliary supporting device 2 at any position, H is the height of the auxiliary supporting device 2, and H is the height of the forming tool 3.
The distance L is a single-side distance between the auxiliary supporting device 2 and the product forming tool 3 at any position of the opposite surface, the distances L on the two sides of the forming tool 3 can be adjusted according to the bending size of the preformed part and the width of the working table top according to conditions, the complete identity is not required to be ensured, but the corresponding H and H meet the relation requirement, and the requirement is also suitable for products which are formed asymmetrically (only on one side).
In the first step, the composite material flat lamination layer 5 is positioned on the forming tool 3 according to a positioning block or a tool, an isolation film is covered on the composite material flat lamination layer 5, and a temperature monitoring thermocouple is placed in the margin area of the composite material flat lamination layer 5.
Preferably, the first step further comprises the operation of preheating the tool. If the thermal inertia of the tool is large, the tool can be preheated before performing operation if the temperature is difficult to rise.
And step two, after heating and temperature rising, keeping the temperature for at least 5 min.
The third step is specifically operated as follows: pressurizing to vacuum pressure of-50 to-80 kp, and stopping pressurizing and maintaining the pressure for at least 5 min. The composite material flat laminate 5 starts to bend under the action of the silicone rubber membrane 1. Until the silicone rubber membrane 1 completely covers the composite material flat laminate 5.
And fourthly, cooling the composite material flat plate lamination layer 5 to be not more than 50 ℃, and then lifting the silicon rubber membrane 1.
The cooling and pressure relief in the fourth step have no sequential requirements.
The size of the silicon rubber membrane 1 is slightly larger than that of the vacuum working platform 4, and the silicon rubber membrane 1 and the vacuum working platform 4 form a sealed space.
The invention has the beneficial effects that:
in the temperature range of the second step of the invention, the prepreg layers of the composite material flat plate lamination 5 have good slippage, meanwhile, the modulus of elasticity of the silicon rubber film 1 when heated is reduced, and the phenomenon of gravity extension occurs, but due to the supporting effect of the auxiliary supporting device 2, the silicon rubber film 1 does not coat the composite material flat plate lamination 5, so that the possibility of bending of the composite material flat plate lamination 5 at the stage is effectively prevented, and the defect of ply folding is avoided.
The invention has simple operation and the silicon rubber film can be repeatedly used. The preformed composite material lamination does not need to be transferred and positioned for the second time, so that the problems of error accumulation and tearing deformation caused by the second positioning are avoided; the composite material flat plate lamination can be directly preformed on a final product forming tool without manufacturing a special preforming tool, and the composite material flat plate lamination has good economy; the preformed composite material lamination has good shape consistency with the product.
The auxiliary supporting device is adopted to balance the normal pressure received by the composite material flat plate lamination in the preforming process, the generation of layering wrinkles can be effectively prevented, and the auxiliary supporting device has good applicability for higher forming tools and products. The accurate pressurization control can be realized by calculation according to the elasticity and the weight of the silicon rubber.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a pre-preform state of the method of the present invention;
FIG. 2 is a pre-formed state of the method of the present invention;
FIG. 3 is a schematic view of an embodiment of a composite structural member profile; the figure shows a schematic appearance of a composite material member with a C-shaped section;
FIG. 4 is a schematic view of the outer shape of a composite material structural member according to a second embodiment; the figure shows a schematic view of the profile of a composite member with a concave cross-section;
FIG. 5 is a schematic view showing a relationship among a distance L between a forming tool and an auxiliary supporting device at any position, a height H of the auxiliary supporting device, and a height H of the forming tool; in fig. 5, the height H of the forming tool 3 is determined by the product structure, and after L is determined according to the objective conditions of the product and the equipment, the height H of the auxiliary supporting device 2 can be adjusted to ensure that the relationship between H +0.4L and H is less than or equal to 2L, that is, H1 corresponds to L1 and H1, H2 corresponds to L2 and H2, and H3 corresponds to L3 and H3.
Wherein, the device comprises a 1-silicon rubber film, a 2-supporting device, a 3-forming tool, a 4-vacuum working platform and a 5-composite material lamination.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.
In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
The first embodiment is as follows: preforming of a C-section composite lay-up as shown in figure 3:
1) ply
Paving a composite material flat plate lamination 5 by adopting an automatic tape paving machine according to the structural member paving information;
2) equipment preparation and tooling preparation
The forming tool 3 is placed on a vacuum working platform 4 of the pre-forming equipment, then the auxiliary supporting devices 2 are placed on two sides of the forming tool 3 in parallel to the forming tool 3, the height of the forming tool 3 is 300mm, the height of the auxiliary supporting devices 2 is 350mm, and the distance between the forming tool and the auxiliary supporting devices is 250 mm. The auxiliary supporting means 2 are coated with airfelt or other soft material. And checking whether sharp bulges or depressions exist on the forming tool 3 and the vacuum working platform 4 or not, and protecting to prevent the silicon rubber membrane 1 from being torn in the pre-forming process.
3) Preheating forming tool 3
Preheating thermocouples are arranged at the leading and lagging positions of the forming tool 3, the silicon rubber film 1 is moved downwards, the forming tool 3 is heated to about 40 ℃, and the silicon rubber film 1 is lifted.
4) Placing a composite material flat laminate 5
The composite material flat plate lamination 5 is placed on the forming tool 3 by utilizing a transfer tool, and the composite material flat plate lamination 5 is protected by using an isolation film to prevent the pollution. Temperature thermocouples are arranged at two ends of the composite material flat plate lamination layer 5.
5) Preforming
a. The silicone rubber membrane 1 is moved downwards, the composite material flat plate lamination 5 is heated to 65(-10, +15) DEG C and then is insulated for 5min at least for 5 min. If the thermal inertia of the tool is large, the tool can be preheated before performing operation if the temperature is difficult to rise;
b. applying vacuum pressure at a rate of about 6kpa/min in the initial stage of pressurization, gradually increasing the vacuum rate until the vacuum pressure is-60 +/-10 kpa, and stopping pressurization to maintain the pressure for at least 5 min;
c. removing the vacuum pressure, cooling the composite material flat plate lamination 5 to 50 ℃, and raising the silicon rubber membrane 1; and (5) protecting the preformed composite material flat plate lamination 5 by using an isolation film, and naturally cooling to room temperature to complete preforming.
Example two: the concave section composite material laminate preform as shown in figure 4:
1) ply
Paving a composite material flat plate lamination 5 by adopting an automatic tape paving machine according to the structural member paving information;
2) equipment preparation and tooling preparation
Placing the forming tool 3 on a vacuum working platform 4 of the pre-forming equipment, then placing the auxiliary supporting device 2 on two sides of the forming tool 3 in parallel with the forming tool 3, wherein the forming tool 3 is 200mm high, the auxiliary supporting device 2 is 250mm high, and the distance between the forming tool and the auxiliary supporting device is 200 mm. The auxiliary supporting means 2 are coated with airfelt or other soft material. And checking whether sharp bulges or depressions exist on the forming tool 3 and the vacuum working platform 4 or not, and protecting to prevent the silicon rubber membrane 1 from being torn in the pre-forming process.
3) Preheating forming tool 3
Preheating thermocouples are arranged at the leading and lagging positions of the forming tool 3, the silicon rubber film 1 is moved downwards, the forming tool 3 is heated to about 40 ℃, and the silicon rubber film 1 is lifted.
4) Placing a composite material flat laminate 5
The composite material flat plate lamination 5 is placed on the forming tool 3 by utilizing a transfer tool, and the composite material flat plate lamination 5 is protected by using an isolation film to prevent the pollution. Temperature thermocouples are arranged at two ends of the composite material flat plate lamination layer 5.
5) Preforming
a. The silicone rubber membrane 1 is moved downwards, the composite material flat plate lamination 5 is heated to 65(-10, +15) DEG C and then is insulated for 5min at least for 5 min. If the thermal inertia of the tool is large, the tool can be preheated before performing operation if the temperature is difficult to rise;
b. applying vacuum pressure at a rate of about 6kpa/min in the initial stage of pressurization, gradually increasing the vacuum rate until the vacuum pressure is-70 +/-10 kpa, and stopping pressurization to maintain the pressure for at least 5 min;
c. removing the vacuum pressure, cooling the composite material flat plate lamination 5 to 50 ℃, and raising the silicon rubber membrane 1; and (5) protecting the preformed composite material flat plate lamination 5 by using an isolation film, and naturally cooling to room temperature to complete preforming.
The invention adopts the silicon rubber membrane which can be repeatedly used and has better extensibility in a heating state, utilizes the auxiliary supporting device to balance the normal pressure of the composite material flat plate lamination in the preforming process, and presses the flat plate lamination to the forming tool in the preforming process by the silicon rubber membrane and is jointed with the forming tool. The invention simplifies the operation and improves the quality stability of the formed body. The surface of the pre-forming body is smooth, and the defects of ply wrinkling, ply buckling and the like are avoided.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (9)
1. A method of single membrane preforming of a composite laminate, characterized by: the single-membrane preforming method of the composite material lamination comprises the following steps:
firstly, a silicon rubber film [1] is hung above a vacuum working platform [4], and a product forming tool [3] and a composite material flat plate lamination [5] are placed at the center of the vacuum working platform [4 ]; placing the auxiliary supporting devices [2] at two sides of the product forming tool [3 ];
heating to raise the temperature, namely raising the temperature of the composite material flat plate lamination [5] to 55-80 ℃;
step three, after the temperature reaches the balance, starting to apply vacuum pressure;
and step four, cooling and releasing pressure to complete preforming.
2. A method of single-membrane preforming of a composite laminate according to claim 1, characterised in that: the interval between the forming tool [3] and the auxiliary supporting device [2] at any position, the height of the auxiliary supporting device [2], and the height of the forming tool [3] satisfy the following relations:
h is more than H and less than or equal to 2L, L is the distance between the forming tool [3] and the auxiliary supporting device [2] at any position, H is the height of the auxiliary supporting device [2], and H is the height of the forming tool [3 ].
3. A method of single-membrane preforming of a composite laminate according to claim 1, characterised in that: in the first step, the composite material flat lamination layer [5] is positioned on the forming tool [3] according to a positioning block or a tool, an isolation film is covered on the composite material flat lamination layer [5], and a temperature monitoring thermocouple is placed in the margin area of the composite material flat lamination layer [5 ].
4. A method of single-membrane preforming of a composite laminate according to claim 1, characterised in that: the first step also comprises the operation of preheating the tool.
5. A method of single-membrane preforming of a composite laminate according to claim 1, characterised in that: and in the second step, the temperature is kept for at least 5min after heating and temperature rising.
6. A method of single-membrane preforming of a composite laminate according to claim 1, characterised in that: the third step is specifically operated as follows: pressurizing to vacuum pressure of-50 to-80 kp, and stopping pressurizing and maintaining the pressure for at least 5 min.
7. A method of single-membrane preforming of a composite laminate according to claim 1, characterised in that: and in the fourth step, the composite material flat plate lamination layer [5] is cooled to be not more than 50 ℃, and then the silicon rubber film [1] is lifted.
8. A method of single-membrane preforming of a composite laminate according to claim 1, characterised in that: the cooling and the pressure relief in the fourth step have no sequential requirements.
9. Method of single-membrane preforming of a composite material laminate according to any of the claims 1 to 8, characterized in that: the size of the silicon rubber membrane [1] is slightly larger than that of the vacuum working platform [4 ].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910971128.5A CN110815632A (en) | 2019-10-12 | 2019-10-12 | Single-diaphragm preforming method for composite material lamination |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910971128.5A CN110815632A (en) | 2019-10-12 | 2019-10-12 | Single-diaphragm preforming method for composite material lamination |
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| CN110815632A true CN110815632A (en) | 2020-02-21 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101835583A (en) * | 2007-10-04 | 2010-09-15 | 空中客车英国有限公司 | Method of moulding a charge |
| EP3505320A1 (en) * | 2017-12-29 | 2019-07-03 | Premium AEROTEC GmbH | Method and device for producing a fibre preform |
| CN110193954A (en) * | 2019-05-21 | 2019-09-03 | 安徽佳力奇碳纤维科技股份公司 | A kind of carbon fiber answers material skin assemblies and preparation method thereof |
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2019
- 2019-10-12 CN CN201910971128.5A patent/CN110815632A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101835583A (en) * | 2007-10-04 | 2010-09-15 | 空中客车英国有限公司 | Method of moulding a charge |
| EP3505320A1 (en) * | 2017-12-29 | 2019-07-03 | Premium AEROTEC GmbH | Method and device for producing a fibre preform |
| CN110193954A (en) * | 2019-05-21 | 2019-09-03 | 安徽佳力奇碳纤维科技股份公司 | A kind of carbon fiber answers material skin assemblies and preparation method thereof |
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