CN114633496A - Demoulding device and method for composite material barrel section structure integral forming tool - Google Patents
Demoulding device and method for composite material barrel section structure integral forming tool Download PDFInfo
- Publication number
- CN114633496A CN114633496A CN202210300015.4A CN202210300015A CN114633496A CN 114633496 A CN114633496 A CN 114633496A CN 202210300015 A CN202210300015 A CN 202210300015A CN 114633496 A CN114633496 A CN 114633496A
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- demoulding
- forming tool
- demolding
- integral forming
- positioning
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- 239000002131 composite material Substances 0.000 title claims abstract description 17
- 238000000034 method Methods 0.000 title claims abstract description 13
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims abstract description 4
- 235000017491 Bambusa tulda Nutrition 0.000 claims abstract description 4
- 241001330002 Bambuseae Species 0.000 claims abstract description 4
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims abstract description 4
- 239000011425 bamboo Substances 0.000 claims abstract description 4
- 238000000465 moulding Methods 0.000 claims description 7
- 238000007493 shaping process Methods 0.000 claims description 4
- 239000000463 material Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
-
- 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
-
- 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
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulds, Cores, Or Mandrels (AREA)
Abstract
The invention belongs to the aerospace manufacturing technology, and particularly relates to a demoulding device and a demoulding method for an integral forming tool of a composite material cylinder section structure. The hydraulic rod is connected to drive the split forming tool to contract so as to realize integral demoulding of the combined tool, so that the combined tool is high in cost, difficult to move and incapable of realizing simple demoulding. The demoulding bracket is provided with a clamping ring at the bottom and positioning devices which are circumferentially distributed at the top; the drawing of patterns pull rod is integrative rotary rod and connecting block in the middle part, has a threaded rod respectively at connecting block both sides, and the screw thread of two threaded rods revolves to opposite, at threaded rod outer end respectively with an internal thread sleeve threaded connection, at the telescopic outer end of internal thread be the connector, through rotating the rotary rod pulling arc structure drawing of patterns. The demoulding pull rod is simple to operate and low in cost, and can be applied to demoulding of the cylinder section structure combined tools with different sizes and shapes. Through the fixed section of thick bamboo section structure combination frock of drawing of patterns support and part, guaranteed the security of drawing of patterns operation.
Description
Technical Field
The invention belongs to the aerospace manufacturing technology, and particularly relates to a demoulding device and a demoulding method for an integral forming tool of a composite material cylinder section structure.
Background
At present, most of the composite material fuselage wall panels are assembled by combining a plurality of wall panels, a large number of metal parts, fasteners, tools and labor cost are consumed, the number of parts, fasteners and tools can be greatly reduced by the integral forming technology of the fuselage section, the assembly is simplified, the composite material fuselage wall panel is an important measure for reducing the weight of a composite material structure, and the composite material fuselage wall panel is an effective method for reducing the cost.
However, the integral forming also puts higher requirements on the design of the die, for example, the barrel section structure aimed at by the invention adopts male die forming, although the whole structure is a cone structure, the distortion of part of the stringers is larger, and the middle part of the stringers is broken, so that the tool cannot be demoulded from the large head end to the small head end, and therefore, the design of a split tool is adopted. Because the split tool is arranged on the inner side of the wall plate of the composite material cylinder section structure, the split tool can only be separated from the inner side, and thus, the demoulding is realized. How to realize the quick and simple demoulding of the split combined tool is one of the key technologies for realizing the integral forming of the barrel section structure of the machine body.
Currently, there are few reports on the integral formation of composite fuselage panels. CN 204340231U provides a section of thick bamboo section structure integrated into one piece frock hydraulic pressure shedder, and hydraulic means comprises hydraulic stem and central main shaft, connects through the hydraulic stem and drives the shrink of components of a whole that can function independently shaping frock and realize the integrated drawing of patterns of combination frock. However, the demolding direction of the hydraulic demolding device is only limited to the cross direction, the demolding is realized by accurately positioning the combined tool and the hydraulic device, and the hydraulic device is heavy in weight, high in cost, difficult to move and incapable of realizing simple demolding.
Disclosure of Invention
The invention provides a demoulding device and a method of a composite material barrel section structure integral forming tool aiming at the problems of complex operation and high cost of a hydraulic demoulding device, and lays a technical foundation for realizing the manufacture of a large-size full composite material machine body barrel section with low cost.
The invention provides a demoulding device of an integral forming tool of a composite material cylinder section structure, the integral forming tool is a split combined tool structure and comprises a plurality of arc structures extending along the axial direction, the arc structures are combined to form an integral male die, the demoulding device comprises a demoulding bracket and a demoulding pull rod,
the bottom of the demoulding support is provided with a clamping ring, the top of the demoulding support is provided with positioning devices distributed in the circumferential direction, the bottom of the integral forming tool is clamped on the clamping ring, and the top of the integral forming tool is fixed on the positioning devices in the circumferential direction;
the demolding pull rod is provided with a rotary rod and a connecting block which are integrated in the middle, two sides of the connecting block are respectively provided with a threaded rod, the thread turning directions of the two threaded rods are opposite, the outer end parts of the threaded rods are respectively in threaded connection with an internal thread sleeve, and the outer end parts of the internal thread sleeves are provided with connectors which are connected with mould plates at opposite positions in the integral molding tool; and the arc-shaped structure is pulled to be demoulded by rotating the rotating rod.
Advantageously, the barrel section structure is a barrel section part of a fuselage section.
Advantageously, the stripping support is of a double-frame construction, with a base, on which a support frame of the intermediate layer and a support frame extending through the intermediate layer in an annular arrangement are fixed, with an annular frame on top of the support frame, on which several positioning means are arranged.
Advantageously, the annular frame is of polygonal configuration.
Advantageously, the positioning means comprise a positioning block fixed to the annular frame, the end of the positioning block being a bolt.
Advantageously, the large-diameter end face of the integral forming tool is provided with a positioning hole, and the positioning hole is connected with the positioning device.
Advantageously, a template is arranged on the inner side of the arc-shaped structure of the integral forming tool, demoulding holes are formed in the template, and connectors at two ends of the demoulding pull rod are connected with the opposite template.
The invention also provides a demoulding method of the composite material barrel section structure integral forming tool, and the method utilizes the demoulding device and comprises the following steps:
s1, clamping the bottom of the integral forming tool on a clamping ring of the demoulding support;
s2, connecting the top of the integral forming tool with a positioning device for a circle;
s3, connecting and fixing the connectors at the two sides of the demoulding pull rod with the mould plates at the opposite positions in the integral forming tool;
s4, disassembling the connection of the positioning device and the integral forming tool in the same direction with the demoulding pull rod;
s5, rotating the rotating rod to drive the template to move inwards, so that the two opposite arc structures are separated;
and S6, repeating the steps S3-S5 to separate the rest arc structures, and realizing demoulding.
Has the advantages that: compared with a hydraulic demoulding device, the demoulding pull rod is simple to operate and low in cost, and can be applied to demoulding of the cylinder section structure combined tools with different sizes and shapes. Through the fixed section of thick bamboo section structure combination frock of drawing of patterns support and part, guaranteed the security of drawing of patterns operation.
The features, functions, and advantages that have been discussed can be achieved independently in various examples or may be combined in yet other examples. Further details of the examples can be seen with reference to the following description and the accompanying drawings.
Drawings
The illustrative examples, as well as a preferred mode of use, further objectives, and descriptions thereof, will best be understood by reference to the following detailed description of an example of the present invention when read in conjunction with the accompanying drawings, wherein:
FIG. 1 is a top view of the integrated molding tooling installed on a demolding device;
FIG. 2 is a front view of the integrated molding tooling installed on the demolding device;
FIG. 3 is a schematic view of the connection of the knockout pull rod inside the forming tool;
FIG. 4 is a schematic structural view of a stripper bracket;
FIG. 5 is a schematic structural diagram of the positioning device;
fig. 6 is a schematic structural view of the ejector tie bar.
Detailed Description
The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. Indeed, many different examples may be described and should not be construed as limited to the examples set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
Referring now to the embodiment shown in the drawings, an integral molding tool 1 of a composite material cylinder section structure shown in fig. 1 is installed on a demolding bracket 3, and a cylinder section part 2 is arranged on the outer side surface of the integral molding tool 1. The integral forming tool 1 is a split combined tool structure, and comprises a plurality of arc-shaped structures extending along the axial direction, the embodiment in the figure is 8 segmented arc-shaped structures, and the integral forming tool structure is formed after combination. The segmented arc structure has a positioning hole 17 at the large diameter end face, a plurality of arc-shaped templates 16 inside, and a demoulding hole 18 on the templates 16.
The demoulding device comprises a demoulding bracket 3 and a demoulding pull rod 4. The right lower part of the demoulding support 3 at least comprises a base 7, a clamping ring 6, a supporting frame 10 and a positioning device 5. Wherein the positioning device 5 comprises a positioning block 8 and a bolt 9.
The demoulding pull rod 4 comprises a rotary rod 15 and a connecting block 14 which are integrated in the middle, threaded rods 13 are arranged on two sides of the connecting block 14, the outer ends of the threaded rods 13 are in threaded connection with an internal threaded sleeve 12, the thread directions of the two ends are opposite, and the outer end of the internal threaded sleeve 12 is a connector. Wherein, the connector 11 is fixedly connected with the template 16 of the combined tool 1 through bolts and nuts. The external screw thread direction of both sides threaded rod 13 is opposite, drives threaded rod 13 rotatory through manual rotation rotary rod 15 to the internal thread sleeve 12 of internal pulling realizes drawing of patterns pull rod 4 and contracts in length, separates the ascending integrated into one piece of frock 1 component of a pair of direction.
The demolding method of the composite material cylinder section structure integral forming tool in one embodiment comprises the following execution processes:
(1) the integral forming tool 1 is integrally placed in a clamping ring 6 at the upper part of a base 7 of the demoulding bracket 3;
(2) fixing the integral forming tool 1 by using a positioning device 5 at the top of the demoulding support 3 and a clamping ring 6 at the bottom, wherein a positioning block 8 in the positioning device 5 is connected and fixed with the large-diameter end face of the barrel section forming tool 1 at the end part through a bolt 9;
(3) the opposite shaping plates 16 are connected and fixed with the connecting head 11 of the demoulding pull rod 4 in the diameter direction through bolts and nuts;
(4) in the direction parallel to the overall forming tool 1 and the demoulding pull rod 4, the large-diameter end part of the overall forming tool 1 is detached from the bolt and the nut of the positioning device 5;
(5) the rotating rod 15 is manually rotated to drive the threaded rods 13 on the two sides to rotate, so that the demoulding pull rod 4 is contracted, and the two opposite segmental arc structures connected with the demoulding pull rod 4 are separated;
(6) and (5) repeating the steps (3) to (5) to separate the rest segmental arc structures, thereby realizing the demoulding of the cylinder segment structure.
In some cases, components of the apparatus and/or system may be configured to perform functions such that the components are actually configured and constructed (using hardware and/or software) to enable such performance. In other examples, components of an apparatus and/or system may be arranged to be suitable, capable, or adapted to perform a function, such as when operating in a particular manner. The method may include one or more operations, functions, or actions as illustrated by one or more of the blocks. Although the blocks are illustrated sequentially, the blocks may also be performed in parallel and/or in a different order than that described herein. In addition, various blocks may be combined into fewer blocks, divided into additional blocks, and/or removed based on a desired implementation.
The description of the different advantageous arrangements has been presented for purposes of illustration and description, but is not intended to be exhaustive or limited to the examples in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Additionally, the different advantageous examples may describe different advantages as compared to other advantageous examples. The example or examples selected are chosen and described in order to best explain the principles of the examples, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various examples with various modifications as are suited to the particular use contemplated.
Claims (8)
1. The utility model provides a shedder of combined material section of thick bamboo structure integrated into one piece frock, this integrated into one piece frock (1) is split combined formula frock structure, includes a plurality of arc structures along axial extension, constitutes whole formpiston, its characterized in that after the arc structure makes up: the demoulding device comprises a demoulding bracket (3) and a demoulding pull rod (4),
the bottom of the demolding support (3) is provided with a clamping ring (6), the top of the demolding support is provided with positioning devices (5) distributed in the circumferential direction, the bottom of the integral forming tool (1) is clamped on the clamping ring (6), and the top of the integral forming tool is fixed on the positioning devices (5) in the circumferential direction;
the demolding pull rod (4) is provided with a rotating rod (15) and a connecting block (14) which are integrated in the middle, two sides of the connecting block (14) are respectively provided with a threaded rod (13), the thread turning directions of the two threaded rods (13) are opposite, the outer end part of each threaded rod (13) is respectively in threaded connection with an internal thread sleeve (12), the outer end part of each internal thread sleeve (12) is provided with a connector (11) which is connected with a shaping plate (16) at a relative position in the integral molding tool (1); the arc-shaped structure is pulled to be demoulded by rotating the rotating rod (15).
2. The demolding device as claimed in claim 1, wherein: the barrel section structure is a barrel section part (2) of the fuselage section.
3. The demolding device as claimed in claim 1, wherein: the demolding support (3) is of a double-layer frame type structure and is provided with a base (7), a support frame of an intermediate layer and a support frame (10) which penetrates through the intermediate layer and is arranged in an annular mode are fixed on the base (7), the top of the support frame (10) is provided with the annular frame, and the annular frame is provided with a plurality of positioning devices (5).
4. The demolding device as claimed in claim 3, wherein: the annular frame is of a polygonal structure.
5. The demolding device as claimed in claim 3 or 4, wherein: the positioning device (5) comprises a positioning block (8) fixed on the annular frame, and a bolt (9) is arranged at the end part of the positioning block (8).
6. The demolding device as claimed in claim 1, wherein: the large-diameter end face of the integral forming tool (1) is provided with a positioning hole (17) and is connected with the positioning device (5) through the positioning hole (17).
7. The demolding device as claimed in claim 1, wherein: a template (16) is arranged on the inner side of an arc-shaped structure of the integral forming tool (1), demoulding holes (18) are formed in the template (16), and connectors (11) at two ends of the demoulding pull rod (4) are connected with the opposite template (16).
8. The demolding method of the composite material cylinder section structure integral molding tool is characterized in that: the method using the demolding device as claimed in any of claims 1 to 7, comprising the steps of:
s1, clamping the bottom of the integral forming tool (1) on a clamping ring (6) of the demolding support (3);
s2, connecting the top of the integral forming tool (1) with the positioning device (5) for a circle;
s3, connecting and fixing the connectors (11) on the two sides of the demoulding pull rod (4) with the mould plates (16) at the opposite positions in the integral forming tool (1);
s4, disassembling the connection between the positioning device (5) and the integral forming tool (1) in the same direction as the demoulding pull rod (4);
s5, rotating the rotating rod (15) to drive the shaping plate (16) to move inwards, so that the two opposite arc structures are separated;
s6, repeating the steps S3-S5 to separate the rest arc structures, and realizing demoulding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210300015.4A CN114633496B (en) | 2022-03-25 | 2022-03-25 | Demolding device and method for integral molding tool of composite material cylinder section structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210300015.4A CN114633496B (en) | 2022-03-25 | 2022-03-25 | Demolding device and method for integral molding tool of composite material cylinder section structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114633496A true CN114633496A (en) | 2022-06-17 |
| CN114633496B CN114633496B (en) | 2023-11-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210300015.4A Active CN114633496B (en) | 2022-03-25 | 2022-03-25 | Demolding device and method for integral molding tool of composite material cylinder section structure |
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| Country | Link |
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| CN (1) | CN114633496B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115071116A (en) * | 2022-08-23 | 2022-09-20 | 四川航天拓达玄武岩纤维开发有限公司 | Core mould for basalt fiber composite pipe production |
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| US6257479B1 (en) * | 1999-12-07 | 2001-07-10 | The Boeing Company | Tooling and methods for circumferential friction stir welding |
| US20120119412A1 (en) * | 2010-11-11 | 2012-05-17 | Spirit Aerosystems, Inc. | Method for removing a smp apparatus from a cured composite part |
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| CN106363935A (en) * | 2016-11-23 | 2017-02-01 | 江苏恒神股份有限公司 | Novel demolding tool for wound mold |
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| US20200094991A1 (en) * | 2018-09-25 | 2020-03-26 | Airbus Operations Sas | Method for assembling an aircraft fuselage section from two superposed upper and lower parts, multipurpose mounting support, gear and fuselage section production unit for implementing said method |
| CN111620231A (en) * | 2020-06-22 | 2020-09-04 | 北京玻钢院复合材料有限公司 | Tool structure for demolding engine spray pipe diffusion section |
| CN211968114U (en) * | 2019-12-26 | 2020-11-20 | 迪皮埃复材构件（太仓）有限公司 | Negative angle demoulding structure of wind power male mould |
| CN212193837U (en) * | 2020-04-03 | 2020-12-22 | 绵阳职业技术学院 | Mould for nondestructive demoulding of glass fiber reinforced plastic flange plate |
| CN112173161A (en) * | 2020-09-21 | 2021-01-05 | 中航复合材料有限责任公司 | Auxiliary manufacturing device for composite material fuselage wallboard |
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2022
- 2022-03-25 CN CN202210300015.4A patent/CN114633496B/en active Active
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| US4080144A (en) * | 1975-10-04 | 1978-03-21 | Karl Hehl | Tie rod structure for die closing unit of injection molding machine |
| US6257479B1 (en) * | 1999-12-07 | 2001-07-10 | The Boeing Company | Tooling and methods for circumferential friction stir welding |
| US20120119412A1 (en) * | 2010-11-11 | 2012-05-17 | Spirit Aerosystems, Inc. | Method for removing a smp apparatus from a cured composite part |
| CN204340231U (en) * | 2014-11-28 | 2015-05-20 | 沈阳飞机工业（集团）有限公司 | A kind of cylinder segment structure composite material component global formation frock of the easy demoulding |
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| CN115071116A (en) * | 2022-08-23 | 2022-09-20 | 四川航天拓达玄武岩纤维开发有限公司 | Core mould for basalt fiber composite pipe production |
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| Publication number | Publication date |
|---|---|
| CN114633496B (en) | 2023-11-21 |
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