CN109605777B - Method for manufacturing solid composite material edge strip prefabricated body - Google Patents
Method for manufacturing solid composite material edge strip prefabricated body Download PDFInfo
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- CN109605777B CN109605777B CN201811464404.0A CN201811464404A CN109605777B CN 109605777 B CN109605777 B CN 109605777B CN 201811464404 A CN201811464404 A CN 201811464404A CN 109605777 B CN109605777 B CN 109605777B
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- edge strip
- prefabricated body
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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
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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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
- B29L2031/3097—Cosmonautical vehicles; Rockets
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulds, Cores, Or Mandrels (AREA)
Abstract
The invention relates to a method for manufacturing a solid composite material edge strip prefabricated part, and belongs to the technology of manufacturing aerospace composite material components. The manufacturing method comprises the steps of dividing the solid core composite material edge strip structure, manufacturing a mould structure and pressing; the prefabricated body prepared by the method can realize the RTM extraction process and the autoclave process to manufacture the solid wing type composite material edge strip and the composite material wing type integral structural component containing the edge strip.
Description
Technical Field
The invention relates to a method for manufacturing a solid composite material edge strip prefabricated part, and belongs to the technology of manufacturing aerospace composite material components.
Background
The application and technical development of composite materials in the aerospace field are always in a leading position, and the development direction of composite material technology is led, wherein the development of fiber reinforced polymer matrix composite material technology is the most rapid. With ever-increasing demands on aerospace vehicle performance, fiber reinforced polymer matrix composite structural design and fabrication has moved towards integrated manufacturing, with integrated fabrication of airfoil composite structures being the most typical. One of the key technologies to achieve the integral fabrication of airfoil composite structural members is the precision fabrication of the composite flanges. The composite edge strip is usually of a solid structure, the section of a workpiece is complex in shape, the upper composite skin part and the lower composite skin part are enabled to be bonded or co-cured into an integral component through the composite edge strip, and the aerodynamic shape requirement of the tip position of the airfoil profile is met.
Disclosure of Invention
The invention aims at a solid airfoil composite material edge strip and provides a method for manufacturing a solid composite material edge strip prefabricated body. By the method, the composite material edge strip and the skin prefabricated body can be co-cured and formed into an integral part by adopting an RTM (resin transfer molding) process or an autoclave process.
In order to achieve the purpose, the invention adopts the following technical scheme:
a method for manufacturing a prefabricated body of an edge strip of a solid core composite material comprises the steps of dividing a solid core composite material edge strip structure, manufacturing a mould structure and pressing;
the solid core composite material edge strip structure is divided into:
the solid composite material edge strip is used for being integrally formed with the composite material skin edge into a wing structural member;
the edge strip prefabricated body is divided into two parts, namely the edge strip prefabricated body is divided into the upper part of the edge strip prefabricated body and the lower part of the edge strip prefabricated body by the central line of the section of the edge strip prefabricated body;
the manufacturing mold structure is as follows:
the upper part of the edge strip prefabricated body consists of a first lower template, a first upper template and a first steel plate for manufacturing a skin step;
the first parting surface corresponds to the center line of the section of the edge strip prefabricated body, and the first parting surface is a contact surface of the first lower template and the first upper template;
the upper end of the first lower template is an upper tip profile;
the lower part of the edge strip prefabricated body consists of a second lower template, a second upper template, a second steel plate and a third steel plate for manufacturing a skin step;
the second die parting surface corresponds to the center line of the section of the edge strip prefabricated body, and the second die parting surface is a contact surface of a second lower template and a second upper template;
the pressing method comprises the following steps:
the pressing method of the solid core composite material edge strip comprises the steps of firstly preparing a die, preparing the die in place, and placing a first steel plate, a second steel plate and a third steel plate;
then opening the first upper template and the second upper template, and laying the carbon fiber filaments soaked with the sizing agent in the first lower template and the second lower template on the upper part of the edge strip preform and the lower part of the edge strip preform according to the length direction and the angle of the fiber laying layer of the edge strip;
adjusting the spreading layer of the surface to be flat and exceed the lower die surface, covering a first upper die plate and a second upper die plate, sending the materials to a press for die pressing until the materials are attached to the die, and then adjusting the temperature and the heat preservation time according to the process method of a sizing agent under the pressure maintaining condition;
opening the upper die plate after cooling and taking out the upper part of the edge strip prefabricated body and the lower part of the edge strip prefabricated body;
when the edge strip part is formed, the upper part of the edge strip prefabricated body and the lower part of the edge strip prefabricated body are spliced and placed into a corresponding forming die to be matched with the skin prefabricated body in place for forming.
Furthermore, the size and the molded surface of the first steel plate are matched with the die to form an upper prefabricated body step which is placed freely.
Furthermore, the profile of the second steel plate is a right angle, the thickness of the second steel plate is the thickness of the flange skin step, and the second steel plate is matched with the die and the third steel plate to form the lower prefabricated body step and the lower structure shape.
Further, the third steel plate is a flat plate.
Further, the spreading layer of the surface is adjusted to be smooth, the first upper template and the second upper template are covered after the spreading layer exceeds the lower die surface, and the distance between the spreading layer and the second upper template exceeding the lower die surface is 1mm-2 mm.
Further, the solid composite material edge strip and the composite material skin edge are integrally formed by an autoclave co-curing method, a co-bonding method or an RTM (resin transfer molding) method.
Further, when the edge strip part is formed, the upper part of the edge strip prefabricated body and the lower part of the edge strip prefabricated body are spliced, and the edge strip prefabricated body is placed into a corresponding forming die to be matched with the skin prefabricated body in place, and then the forming mode is as follows: and performing RTM (resin transfer molding) process integral molding, or performing co-curing or co-cementing molding by using an autoclave process.
The solid wing type composite material edge strip prefabricated body is characterized in that a fiber bundle laying structure is arranged at the joint of an upper skin and a lower skin. The edge strip prefabricated body is divided into two parts, the two parts are respectively molded to form the prefabricated body, and then the prefabricated body is spliced and placed into a composite material forming die to form the composite material part. For easy demoulding, the mould surface uses a metal sheet metal part which can be removed from the main mould and is specified as a skin thickness plate.
The invention has the beneficial effects that:
the prefabricated part manufacturing tool is simple and the size is accurately controlled. The prefabricated body prepared by the method can realize the RTM extraction process and the autoclave process to manufacture the solid wing type composite material edge strip and the composite material wing type integral structural component containing the edge strip.
Drawings
FIG. 1 is a schematic view of a solid core composite edge strip of the present invention;
FIG. 2 is a schematic view of the upper part (4) of the edge strip preform according to the present invention;
fig. 3 is a schematic view showing the structure of the lower part (5) of the edge strip preform of the present invention.
Detailed Description
The invention is described in detail below with reference to the attached drawing figures:
a method for manufacturing a prefabricated body of an edge strip of a solid core composite material comprises the steps of dividing a solid core composite material edge strip structure, manufacturing a mould structure and pressing;
the solid core composite material edge strip structure is divided into:
as shown in fig. 1: a solid core composite material edge strip 1 for integrally forming with a composite material skin edge 2 into a wing type structural member;
the edge strip prefabricated body is manufactured by dividing the edge strip prefabricated body into two parts, namely dividing the edge strip prefabricated body into an upper part 4 of the edge strip prefabricated body and a lower part 5 of the edge strip prefabricated body by using a central line 3 of the section of the edge strip prefabricated body;
the manufacturing mold structure is as follows:
as shown in fig. 2: the edge strip prefabricated body upper part 4 consists of a first lower template 6, a first upper template 7 and a first steel plate 10 for manufacturing a skin step;
a first parting surface 8 corresponding to the center line 3 of the section of the edge strip preform, wherein the first parting surface 8 is a contact surface of the first lower template 6 and the first upper template 7;
the upper end of the first lower template 6 is an upper tip molded surface 9;
as shown in fig. 3: the lower part 5 of the edge strip preform consists of a second lower template 11, a second upper template 12, a second steel plate 13 and a third steel plate 14 for manufacturing a skin step;
a second parting surface 15 corresponding to the center line 3 of the section of the edge strip preform, wherein the second parting surface 15 is a contact surface of the second lower template 11 and the second upper template 12;
the pressing method comprises the following steps:
the pressing method of the solid core composite material edge strip comprises the steps of firstly preparing a die, preparing the die in place according to figures 2 and 3, and placing a first steel plate 10, a second steel plate 13 and a third steel plate 14;
then opening a first upper template 7 and a second upper template 12, and laying the carbon fiber filaments soaked with the sizing agent in a first lower template 6 and a second lower template 11 on the upper part 4 and the lower part 5 of the edge strip preform according to the length direction and the angle of the fiber laying layer of the edge strip;
adjusting the spreading of the surface to be smooth and exceed the lower die surface, covering a first upper die plate 7 and a second upper die plate 12, sending the materials to a press for die pressing until the materials are attached to the die, and then adjusting the temperature and the heat preservation time according to the process method of a sizing agent under the pressure maintaining condition;
after cooling, opening the upper die plate and taking out the upper part 4 of the edge strip prefabricated body and the lower part 5 of the edge strip prefabricated body;
when the edge strip part is formed, the upper part 4 of the edge strip prefabricated body and the lower part 5 of the edge strip prefabricated body are spliced according to the figure 1 and are placed into a corresponding forming die to be matched with the skin prefabricated body in place for forming.
Further, the size and profile of the first steel plate 10 cooperate with the mold to form an upper preform step for free placement.
Furthermore, the profile of the second steel plate 13 is a right angle, the thickness of the profile is the thickness of the flange skin step, and the profile is matched with a mould and the third steel plate 14 to form the shape of the lower prefabricated body step and the lower structure.
Further, the third steel plate 14 is a flat plate.
Further, the layer of the adjusting surface is smooth and exceeds the lower die surface, and then the first upper die plate 7 and the second upper die plate 12 are covered, wherein the distance between the layer of the adjusting surface and the layer of the adjusting surface exceeds the lower die surface by 1mm-2 mm.
Further, the solid composite edge strip 1 and the composite skin edge 2 are integrally formed by autoclave co-curing, co-bonding or RTM.
Further, when the edge strip part is formed, the upper part 4 of the edge strip prefabricated body and the lower part 5 of the edge strip prefabricated body are spliced, and the edge strip prefabricated body is placed into a corresponding forming die to be matched with the skin prefabricated body in place and then formed: and performing RTM (resin transfer molding) process integral molding, or performing co-curing or co-cementing molding by using an autoclave process.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A method for manufacturing a solid core composite material edge strip prefabricated body is characterized by comprising the following steps: the manufacturing method comprises the steps of dividing the solid core composite material edge strip structure, manufacturing a mould structure and pressing;
the solid core composite material edge strip structure is divided into:
the solid composite material edge strip (1) is used for being integrally formed with the composite material skin edge (2) into a wing structural member;
the edge strip prefabricated body is divided into two parts, namely the edge strip prefabricated body is divided into an upper part (4) of the edge strip prefabricated body and a lower part (5) of the edge strip prefabricated body by a section center line (3) of the edge strip prefabricated body;
the manufacturing mold structure is as follows:
the upper part (4) of the edge strip prefabricated body consists of a first lower template (6), a first upper template (7) and a first steel plate (10) for manufacturing a skin step;
a first parting surface (8) corresponding to the center line (3) of the section of the edge strip preform, wherein the first parting surface (8) is a contact surface of a first lower template (6) and a first upper template (7);
the upper end of the first lower template (6) is an upper tip profile (9);
the lower part (5) of the edge strip prefabricated body consists of a second lower template (11), a second upper template (12), a second steel plate (13) and a third steel plate (14) for manufacturing a skin step;
a second die parting surface (15) corresponding to the center line (3) of the section of the edge strip preform, wherein the second die parting surface (15) is a contact surface of a second lower template (11) and a second upper template (12);
the pressing method comprises the following steps:
the pressing method of the solid core composite material edge strip comprises the steps of firstly preparing a die, preparing the die in place, and placing a first steel plate (10), a second steel plate (13) and a third steel plate (14);
then opening a first upper template (7) and a second upper template (12), and laying the carbon fiber filaments soaked with the sizing agent in a first lower template (6) and a second lower template (11) on the upper part (4) and the lower part (5) of the edge strip preform according to the length direction and the angle of the fiber laying layer of the edge strip;
after the spreading layer on the surface is adjusted to be flat and exceeds the lower die surface, a first upper die plate (7) and a second upper die plate (12) are covered, the materials are sent to a press to be molded until the materials are attached to the die, and then the temperature and the heat preservation time are adjusted according to the technological method of a sizing agent under the pressure maintaining condition;
after cooling, opening the upper die plate and taking out the upper part (4) and the lower part (5) of the edge strip prefabricated body;
when the edge strip part is formed, the upper part (4) of the edge strip prefabricated body and the lower part (5) of the edge strip prefabricated body are spliced and placed into a corresponding forming die to be matched with the skin prefabricated body in place for forming.
2. A method of manufacturing a solid core composite edge strip preform according to claim 1, wherein: the size and the molded surface of the first steel plate (10) are matched with the mold to form an upper prefabricated body step which is placed freely.
3. A method of manufacturing a solid core composite edge strip preform according to claim 1, wherein: the profile of the second steel plate (13) is a right angle, the thickness of the second steel plate is the thickness of an edge strip skin step, and the second steel plate is matched with the mould and the third steel plate (14) to form the shapes of a lower prefabricated body step and a lower structure.
4. A method of manufacturing a solid core composite edge strip preform according to claim 1, wherein: the third steel plate (14) is a flat plate.
5. A method of manufacturing a solid core composite edge strip preform according to claim 1, wherein: after the spreading layer of the surface is adjusted to be flat and exceeds the lower die surface, a first upper die plate (7) and a second upper die plate (12) are covered, and the distance of the first upper die plate and the second upper die plate exceeding the lower die surface is 1-2 mm.
6. A method of manufacturing a solid core composite edge strip preform according to claim 1, wherein: the solid composite material edge strip (1) and the composite material skin edge (2) are integrally formed by an autoclave co-curing method, a co-bonding method or an RTM method.
7. A method of manufacturing a solid core composite edge strip preform according to claim 1, wherein: when the edge strip part is formed, splicing the upper part (4) of the edge strip prefabricated body and the lower part (5) of the edge strip prefabricated body, and putting the edge strip prefabricated body into a corresponding forming die to be matched with the skin prefabricated body in place to form the edge strip part in the following mode: and performing RTM (resin transfer molding) process integral molding, or performing co-curing or co-cementing molding by using an autoclave process.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811464404.0A CN109605777B (en) | 2018-12-03 | 2018-12-03 | Method for manufacturing solid composite material edge strip prefabricated body |
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| CN201811464404.0A CN109605777B (en) | 2018-12-03 | 2018-12-03 | Method for manufacturing solid composite material edge strip prefabricated body |
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| CN109605777B true CN109605777B (en) | 2021-01-26 |
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| CN101695871A (en) * | 2009-11-12 | 2010-04-21 | 江苏九鼎新材料股份有限公司 | Large wind force blade and manufacturing process thereof |
| FR2965202B1 (en) * | 2010-09-28 | 2012-10-12 | Snecma | PROCESS FOR MANUFACTURING A PIECE AND COMPOSITE MASSIVE PART OBTAINED BY THIS METHOD |
| CN204399464U (en) * | 2014-12-12 | 2015-06-17 | 中国航天空气动力技术研究院 | Integrated composite controlsurface structure |
| CN104626605B (en) * | 2014-12-16 | 2017-02-22 | 西安爱生技术集团公司 | Composite material wing integral molding technological method and composite material wing integral molding tool |
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