CN115008784B - Forming die and method for composite material thin-wall splicing tool - Google Patents
Forming die and method for composite material thin-wall splicing tool Download PDFInfo
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- CN115008784B CN115008784B CN202210451516.2A CN202210451516A CN115008784B CN 115008784 B CN115008784 B CN 115008784B CN 202210451516 A CN202210451516 A CN 202210451516A CN 115008784 B CN115008784 B CN 115008784B
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- composite material
- material thin
- wall splicing
- splicing tool
- fixed plate
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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
-
- 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
-
- 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
- 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
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a composite material thin-wall splicing tool forming die which comprises a base body, wherein cover plates are attached to the peripheral vertical surfaces of the base body along the length direction of the base body, caulking grooves are uniformly distributed on the cover plates, inserts protruding out of the inner molded surface of the cover plates are arranged in the caulking grooves, a fixed plate carried on the cover plates is arranged above the base body in a suspended manner along the length direction of the base body, metal plates are arranged on the fixed plate and close to the two end positions of the fixed plate, and parts of the metal plates extend out of the lower edges of the fixed plate and are suspended on the molded surface of the base body; also discloses a composite material thin-wall splicing tool forming method. The invention has simple structure, low cost and general applicability to thin-wall splicing tools and parts of aircraft composite materials.
Description
Technical Field
The invention relates to the technical field of aircraft part manufacturing, in particular to a composite material thin-wall splicing tool forming die and a composite material thin-wall splicing tool forming method.
Background
The utility model provides a composite material thin wall concatenation class frock for aircraft, refers to the turn-ups all around, and the middle part has box-shaped composite material frock of connecting the angle piece, uses when mainly being applied to composite material dysmorphism part shaping.
The special-shaped part made of the composite material is an integral cylindrical part with a large middle part and small two ends, the integral forming of the part is required during forming, the tooling for forming the part is required to be divided into blocks and spliced, and the requirements on the connection form and connection surface precision between different blocks are higher during splicing.
The patent specification with the publication number of CN112476881A discloses a telescopic composite material cylinder laying tool, which comprises a main shaft, a first tool module group and a second tool module group, wherein the first tool module group and the second tool module group are composed of a plurality of arc-shaped tool modules, and the tool modules in the first tool module group and the tool modules in the second tool module group can be spliced into a cylinder laying tool encircling the outside of the main shaft; the middle part of the main shaft is fixedly sleeved with a fixed sleeve, two ends of the main shaft are respectively sleeved with a first sliding sleeve and a second sliding sleeve, and the fixed sleeve and the first sliding sleeve are hinged with the middle part of each tool module in the first tool module group through mechanical connecting rods; the second sliding sleeve and the fixed sleeve are hinged with the middle part of each tooling module in the second tooling module group through mechanical connecting rods; the middle parts of the inner sides of the tooling modules in the first tooling module group and the second tooling module group are respectively provided with a vertical double-hole lug key; the upper holes of the double-hole lug-shaped keys of the tool modules in the first tool module group are hinged with the outer walls of the first sliding sleeves at two ends of the same mechanical connecting rod, and the lower holes of the double-hole lug-shaped keys of the tool modules in the first tool module group are hinged with the outer walls of the fixed sleeves at two ends of the same mechanical connecting rod; the upper holes of the double-hole lug-shaped keys of the tooling modules in the second tooling module group are hinged with the outer walls of the fixed sleeves at two ends of the same mechanical connecting rod, and the lower holes of the double-hole lug-shaped keys of the tooling modules in the second tooling module group are hinged with the outer walls of the second sliding sleeves at two ends of the same mechanical connecting rod.
The special-shaped part of the airplane is made of composite materials, so that a tool for forming the special-shaped part is also made of composite materials, and correspondingly, the die structure and the material for forming the tool are also required to be high. The aviation manufacturing industry in China basically adopts a molding method of pressurizing and heat preserving in an autoclave at a high temperature for composite material parts for airplanes. The die material required by the processing mode is invar steel, the material is high-temperature resistant, and compared with other metal dies, the thermal expansion coefficient of the material is more similar to that of the composite material part, but the processing period is long, the processing difficulty is higher, the repair rate is low, the cost of the die material is higher, the die material is not suitable for the molding requirements of all composite material parts, and the die material is particularly suitable for the production of composite material parts with short period and urgent requirements.
The composite material thin-wall splicing tool material for the aircraft is a composite material capable of being cured at low temperature, when the material is at low temperature, the material is molded into a required shape on a die, then the material is demolded, and the material enters a high-temperature hot-pressing tank for pressurizing, heat-preserving and secondary curing, so that a qualified tool is molded. At this time, at low temperatures, conventional invar dies are not suitable for molding such composite parts. Therefore, a method which is simple in operation structure, simple in processing, low in cost and capable of being used at low temperature is needed to be considered for forming the composite material thin-wall splicing tool.
Disclosure of Invention
The invention aims to provide a composite material thin-wall splicing tool forming die which is simple in structure, low in cost and universal in applicability to aircraft composite material thin-wall splicing tools and parts.
The utility model provides a combined material thin wall concatenation class frock forming die, includes the base member, follows the laminating of facade all around of base member is provided with the apron, it has the caulking groove to follow its length direction equipartition on the apron, be provided with the inserts of protruding apron internal profile in the caulking groove, the base member top is unsettled to be provided with along its length direction and carries on the fixed plate on the apron, be close to its both ends position on the fixed plate and be provided with the metal sheet, the part of metal sheet stretches out the fixed plate lower limb and hangs on the base member profile.
The scheme utilizes the insert to be inlaid in the caulking groove for paving, thereby realizing the accurate molding of the connecting groove; and smooth demolding of the closed angle after molding is realized by utilizing the block design of the cover plate.
Preferably, the substrate is formed by bonding a plurality of pieces, and an adhesive joint is arranged between each two pieces.
Preferably, the matrix profile is curved.
Preferably, the caulking groove is an L-shaped groove, the insert is correspondingly L-shaped, and the insert protrudes 3-7mm from the inner molded surface of the cover plate.
Further preferably, the insert protrudes 5mm from the inner profile of the cover plate.
Preferably, the cover plate is provided with a convex edge corresponding to the end part of the fixing plate, and the end part of the fixing plate is clamped in the convex edge.
Preferably, at least one half of the length direction of the metal plate extends out of the lower edge of the fixing plate.
The invention further aims to provide a composite material thin-wall splicing tool forming method, which comprises the following steps of:
(1) Bonding the matrix, treating the replaceable surface and the surrounding vertical surfaces of the matrix after the bonding of the matrix is completed, ensuring the integrity of the formed edges, and filling the bonding joints with a filling agent;
(2) The L-shaped inserts are respectively inlaid into L-shaped caulking grooves on the cover plate, the inner molded surface of the cover plate protrudes 3-7mm after the L-shaped inserts are installed, and then the four cover plates are respectively installed on the substrate, so that the inner molded surface of the cover plate is guaranteed to be attached to the peripheral vertical surfaces of the substrate;
(3) Paving the composite material thin-wall splicing tool, and avoiding the bulge of the L-shaped insert when paving the composite material thin-wall splicing tool to the L-shaped insert, so that an L-shaped connecting groove is formed after the tool is formed;
(4) The metal plate is arranged on the fixed plate, the fixed plate is carried on the cover plate, and the outer surface of the metal plate and the replaceable molded surface of the matrix are used for paving and pasting to form a connecting corner piece in the middle of the tool;
(5) Solidifying at low temperature, shaping, demoulding.
The invention has the beneficial effects that:
the invention utilizes the basic principles of quick replacement and low-temperature forming, and utilizes the replaceable principle of the processable plastic to realize the replacement of the matrix in the use process and the quick processing of the formed edges; the characteristics that the composite material thin-wall tool needs to be spliced are utilized, the connection at the fourth Zhou Fanbian part is designed into an L shape, and convenience and firmness in connection are realized; the L-shaped insert is inlaid into the L-shaped caulking groove of the cover plate for paving, so that the accurate forming of the connecting groove is realized; the smooth demoulding of the closed angle after the forming is realized by utilizing the block design of the cover plate; finally, the low-cost and high-efficiency accurate forming of the aircraft composite material thin-wall splicing tool is realized, and the aircraft composite material thin-wall splicing tool has universal applicability to aircraft composite material thin-wall splicing tools and parts.
Drawings
FIG. 1 is a schematic diagram of a tooling structure;
FIG. 2 is a schematic diagram of the structure of the present invention;
FIG. 3 is a schematic diagram of a matrix structure;
FIG. 4 is a schematic view of a partial structure of a cover plate;
fig. 5 is a schematic view of a partial structure of the fixing plate.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 2-5, a composite material thin-wall splicing tool forming die comprises a base body 4, wherein the base body 4 is of a multi-block bonding structure and is provided with three blocks, an adhesive joint 5 is arranged in the middle of each block, the profile of the base body 4 is a replaceable profile 6 and is a curved surface, forming edges 7 are formed around the replaceable profile 6, and the forming edges 7 are the intersection edges of the replaceable profile 6 and vertical faces 8 around the base body 4.
Four cover plates 9 are attached along the peripheral vertical faces of the base body 4, namely, the inner face 10 of each cover plate 9 is attached to the peripheral vertical faces 8 of the base body 4; the inner molding surface 10 of each cover plate 9 is uniformly distributed with L-shaped caulking grooves 11 along the length direction thereof for the installation of L-shaped inserts 12, namely, the overall shape of the inserts 12 is L-shaped, the inserts are inlaid in the L-shaped caulking grooves 11, and the inserts are protruded out of the inner molding surface 10 of the cover plate 9 by five millimeters after installation.
The upper part of the base body 4 is suspended along the length direction thereof to be provided with a fixed plate 13 carried on the cover plate 9, in particular to a convex edge 14 which is arranged on the cover plate 9 and corresponds to the end part position of the fixed plate 13, a sliding groove 15 is arranged on the convex edge 14, the end part of the fixed plate 13 is clamped in the sliding groove 15 on the convex edge 14, and the middle part is suspended above the replaceable surface 6.
The fixing plate 13 is provided with a metal plate 16 near two end positions thereof, specifically, the metal plate 16 is correspondingly provided with a mounting groove 17, the metal plate 16 is fixed in the mounting groove 17, and one half of the length direction of the metal plate 16 extends out of the lower edge of the fixing plate 13 and is suspended on the replaceable surface 6.
The method for forming the tool shown in fig. 1 by using the forming die comprises the following steps:
(1) Bonding the matrix 4 by using a machinable plastic plate, bonding each layer with pressure, after the bonding of the matrix 4 is completed, performing numerical control milling to change the profile 6 and the vertical surfaces 8 around the matrix 4, ensuring the integrity of the formed edge 7, and filling the bonding joint 5 by using a filling agent;
(2) The L-shaped inserts 12 are respectively embedded into the L-shaped embedded grooves 11 on the cover plate 9, the inner molded surface 10 of the cover plate 9 is protruded five millimeters after the mounting, and then the four cover plates 9 are respectively mounted on the base body 4, so that the inner molded surface 10 of the cover plate 9 is bonded with the surrounding vertical surfaces 8 of the base body 4;
(3) The composite material thin-wall splicing tool 1 is paved, the forming precision of the appearance surface of the tool is ensured by utilizing the replaceable molded surface 6 of the base body 4 and the inner molded surface 10 of the cover plate 9, and when the composite material thin-wall splicing tool is paved to the L-shaped insert 12, the bulge of the L-shaped insert 12 is avoided, so that the L-shaped connecting groove 2 is formed after the tool is formed;
(4) Placing a metal plate 16 in a mounting groove 17 of a fixed plate 13, mounting the fixed plate 13 on a cover plate 9 along a sliding groove 15, and paving an outer molded surface of the metal plate 16 and the replaceable molded surface 6 to form a connecting corner piece 3 in the middle of the tool;
(5) And (3) entering an oven for low-temperature curing, after molding, removing the fixing plate 13 firstly because the flanges around the tool are provided with closed angles, and then removing the cover plate 9 successively respectively, so that the tool can be successfully demolded.
Although the present invention has been described with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements and changes may be made without departing from the spirit and principles of the present invention.
Claims (6)
1. The utility model provides a combined material thin wall concatenation class frock forming die, its characterized in that includes the base member, follow the laminating of the facade all around of base member is provided with the apron, be equipped with the caulking groove along its length direction on the apron, be provided with the inserts of protruding apron inner profile in the caulking groove, the caulking groove is "L" shape, the corresponding "L" shape of inserts, inserts protruding apron inner profile 3-7mm, the base member top is in midair along its length direction and is provided with the fixed plate that carries on the apron, be provided with the metal sheet near its both ends position on the fixed plate, the part of metal sheet stretches out the fixed plate lower limb and hangs on the base member profile; the matrix is formed by bonding a plurality of blocks, and bonding joints are arranged between each two blocks.
2. The composite material thin-wall splicing tool forming die of claim 1, wherein the matrix profile is a curved surface.
3. The composite material thin-wall splicing tool forming die according to claim 1, wherein the insert protrudes from the inner molded surface of the cover plate by 5mm.
4. The composite material thin-wall splicing tool forming die according to claim 1, wherein a convex edge is arranged on the cover plate corresponding to the end part of the fixing plate, and the end part of the fixing plate is clamped in the convex edge.
5. The composite material thin-wall splicing tool forming die according to claim 1, wherein at least one half of the length direction of the metal plate extends out of the lower edge of the fixing plate.
6. A method for forming a composite material thin-wall splicing tool, which is realized based on the composite material thin-wall splicing tool forming die according to any one of claims 1 to 5, and comprises the following steps:
(1) Bonding the matrix, treating the replaceable surface and the surrounding vertical surfaces of the matrix after the bonding of the matrix is completed, ensuring the integrity of the formed edges, and filling the bonding joints with a filling agent;
(2) The L-shaped inserts are respectively inlaid into L-shaped caulking grooves on the cover plate, the inner molded surface of the cover plate protrudes 3-7mm after the L-shaped inserts are installed, and then the four cover plates are respectively installed on the substrate, so that the inner molded surface of the cover plate is guaranteed to be attached to the peripheral vertical surfaces of the substrate;
(3) Paving the composite material thin-wall splicing tool, and avoiding the bulge of the L-shaped insert when paving the composite material thin-wall splicing tool to the L-shaped insert, so that an L-shaped connecting groove is formed after the tool is formed;
(4) The metal plate is arranged on the fixed plate, the fixed plate is carried on the cover plate, and the outer surface of the metal plate and the replaceable molded surface of the matrix are used for paving and pasting to form a connecting corner piece in the middle of the tool;
(5) Solidifying at low temperature, shaping, demoulding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210451516.2A CN115008784B (en) | 2022-04-26 | 2022-04-26 | Forming die and method for composite material thin-wall splicing tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210451516.2A CN115008784B (en) | 2022-04-26 | 2022-04-26 | Forming die and method for composite material thin-wall splicing tool |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115008784A CN115008784A (en) | 2022-09-06 |
| CN115008784B true CN115008784B (en) | 2023-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210451516.2A Active CN115008784B (en) | 2022-04-26 | 2022-04-26 | Forming die and method for composite material thin-wall splicing tool |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3087606A (en) * | 1953-10-19 | 1963-04-30 | Minnesota Mining & Mfg | Package of inter-reactive materials |
| CN1630786A (en) * | 2002-08-10 | 2005-06-22 | Zf雷姆伏尔德金属制品股份公司 | Bearing shell for a spherical joint and method for the production thereof |
| CN109501312A (en) * | 2018-11-26 | 2019-03-22 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of composite material mould and its application method of modularized design |
-
2022
- 2022-04-26 CN CN202210451516.2A patent/CN115008784B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3087606A (en) * | 1953-10-19 | 1963-04-30 | Minnesota Mining & Mfg | Package of inter-reactive materials |
| CN1630786A (en) * | 2002-08-10 | 2005-06-22 | Zf雷姆伏尔德金属制品股份公司 | Bearing shell for a spherical joint and method for the production thereof |
| CN109501312A (en) * | 2018-11-26 | 2019-03-22 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of composite material mould and its application method of modularized design |
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| Publication number | Publication date |
|---|---|
| CN115008784A (en) | 2022-09-06 |
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