CN108466435B - Composite material wing solidification deformation prevention mold design - Google Patents
Composite material wing solidification deformation prevention mold design Download PDFInfo
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- CN108466435B CN108466435B CN201810151683.9A CN201810151683A CN108466435B CN 108466435 B CN108466435 B CN 108466435B CN 201810151683 A CN201810151683 A CN 201810151683A CN 108466435 B CN108466435 B CN 108466435B
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- composite material
- bottom plate
- suspension plate
- strip
- 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
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
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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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-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
- B29C70/54—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
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Devices Affording Protection Of Roads Or Walls For Sound Insulation (AREA)
Abstract
The invention discloses a design of a composite material wing solidification deformation prevention mold. And (3) sequentially placing a demoulding material layer, a composite material wing, an upper demoulding material and a ventilated felt on the composite material mould from bottom to top, and covering a vacuum bag to finish air extraction and vacuum degree measurement. And (4) dismounting the bottom plate, and hanging the two sides of the bottom plate on pulley assemblies correspondingly designed on the two sides of the suspension plate through bottom plate lifting ropes which are installed at equal intervals. The suspension plate is hung on the upper surface inside the autoclave; the pulley assembly has freedom of movement toward the central position of the suspension plate. And then, heating, curing and demolding to obtain the composite material structure with less thermal stress influence. The invention realizes the change of the support mode of the composite material mould at different stages, reduces the thermal stress generated by the structural support mode and lightens the influence of the mould on the curing deformation of the composite material structure by converting the fixed support of the mould into the sliding friction between the pulley and the suspension plate.
Description
Technical Field
The invention relates to the technical field of composite material component autoclave molding tool design, in particular to a composite material wing solidification deformation prevention mold design, which can realize the change of a support mode of a composite material mold, thereby reducing the thermal stress of the mold and lightening the influence of the mold on the solidification deformation of a composite material structure.
Background
In the process of curing the composite material, the composite material structure is deformed due to the relative deformation between the composite material structure and the mold, so that the quality of the composite material structure is influenced, and the assembly difficulty is increased. The coefficient of thermal expansion of the Invar steel is similar to that of the composite material, and the deformation of the composite material member in the molding process can be effectively reduced by using the Invar steel as a molding die of a composite material part. However, in the first step of the composite curing process, the mould itself needs to be fixed due to the lay-up requirements. In the process of curing and heating, the mould needs to be ensured to deform along with the temperature similar to the structure of the composite material, so that the thermal stress is reduced. Therefore, the supporting manner of the mold needs to be changed correspondingly according to the manufacturing steps.
Disclosure of Invention
The invention provides a universal composite mold design for changing the support mode according to the requirement change of the mold support mode in the composite structure manufacturing process.
The invention relates to a design of a composite material wing solidification deformation prevention mold, which comprises the following steps of firstly, manufacturing a composite material mold and fixing the composite material mold on a bottom plate, and fixing the bottom plate on the ground; and sequentially placing a demoulding material layer, a composite material wing, an upper demoulding material and a ventilated felt on the composite material mould from bottom to top, covering a vacuum bag, and finishing air suction and vacuum degree measurement. The bottom plate is disassembled, and the two sides of the bottom plate are hung on pulley assemblies correspondingly designed on the two sides of the hanging plate through bottom plate hanging ropes which are installed at equal intervals; the suspension plate is hung on the upper surface inside the autoclave; the pulley assembly has a freedom of movement towards the central position of the suspension plate; and then heating, curing and demolding according to the autoclave composite material manufacturing method to finally obtain the composite material structure with less thermal stress influence.
In the process of heating and curing, the mold heats and expands, and due to the adoption of the rope hanging mode, the deformation of the composite material mold is converted into outward movement of the pulley assembly, and the stress concentration change of the composite material mold caused by the deformation is less, so that the influence on the composite material structure is less. In the cooling process, the deformation of the die is converted into the inward movement of the pulley assembly, and the stress concentration change of the composite material die caused by the deformation is less, so that the influence on the composite material structure is less.
The invention has the advantages that:
1. according to the design of the composite material wing solidification deformation prevention mold, the fixed support of the mold is converted into the sliding friction between the pulley and the suspension plate, so that the thermal stress generated by a structural support mode is reduced, and the influence of the mold on the solidification deformation of a composite material structure is reduced.
Drawings
FIG. 1 is a schematic structural diagram of a composite material wing solidification deformation prevention mold design according to the present invention;
FIG. 2 is a schematic view of the installation of a composite material mold and a base plate in the design of the composite material wing anti-solidification deformation mold of the invention;
FIG. 3 is a schematic view of a baseplate structure in the design of the composite material wing solidification deformation prevention mold of the present invention;
FIG. 4 is a schematic structural view of a suspension plate in the design of the composite material wing solidification deformation prevention mold of the invention;
FIG. 5 is a schematic view of the installation mode of the suspension plate and the pulley in the design of the composite material wing solidification deformation prevention mold.
1-bottom plate 2-suspension plate 3-pulley assembly 4-suspension plate lifting rope
5-bottom plate lifting rope 6-composite material mould 7-demoulding material layer 8-composite material wing
9-upper demoulding material 10-air-permeable felt 11-vacuum bag 12-bolt
101-bottom plate fixing hole 102-bottom plate lifting rope hanging interface 201-strip-shaped groove 401-pulley
402 connecting shaft 403 bearing
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The invention relates to a composite material wing solidification deformation prevention die design, which comprises a bottom plate 1, a suspension plate 2, a pulley assembly 3, a suspension plate lifting rope 4 and a bottom plate lifting rope 5, and is shown in figure 1.
As shown in fig. 2 and 3, the bottom plate 1 is arranged opposite to the suspension plate 2; wherein, the middle part of the bottom plate 1 is a die mounting area, die mounting holes are designed on the left side and the right side of the die mounting area, the composite material die 6 is arranged in the die mounting area, and the composite material die 6 can be fixed on the bottom plate 1 by matching the die mounting holes with bolts. The left and right sides of the bottom plate 1 are provided with bottom plate fixing holes 101 along the left and right direction, and the bottom plate 1 is fixed on the ground by matching the bottom plate fixing holes 101 through bolts. The left side and the right side of the bottom plate 1 are also provided with n bottom plate lifting rope hanging interfaces 102 at equal intervals along the left-right direction for connecting the bottom plate lifting ropes 5. One of the n floor hoist rope suspension interfaces 102 is located at a central position, and the remaining floor hoist rope suspension interfaces 102 are distributed bilaterally symmetrically with respect to the floor hoist rope suspension interface 102 at the central position.
The suspension plate 2 is parallel to the bottom plate 1 and is arranged above the bottom plate 1. Hang the equal interval design of board 2 upper surface left and right sides along the left and right sides direction and have and hang the board and hang the interface, hang 5 bottoms of board lifting rope and hang the board and hang interface connection, the top is connected on the inside upper surface of autoclave, realizes hanging the hoist and mount of board 2. As shown in fig. 4, the hanging plate 2 is provided with a strip-shaped groove 201 opened by scattering rays from the center of the hanging plate 2 to the periphery, specifically: the strip-shaped grooves 201 are n groups of empty grooves penetrating the upper and lower surfaces of the suspension plate 2. Each group of strip-shaped grooves 201 is two and is respectively positioned at the left side and the right side of the hanging plate 2 and is symmetrical relative to the center of the hanging plate 2; the left side and the right side of the suspension plate 2 are respectively provided with n strip-shaped grooves 201, and the positions of the n strip-shaped grooves 201 respectively correspond to the positions of the n bottom plate lifting rope suspension interfaces 102 on the bottom plate 1 on the same side; and the central connecting line of the corresponding bottom plate lifting rope hanging interface 102 and the strip-shaped groove 201 is vertical to the bottom plate 1. The length direction of each strip-shaped groove 201 is connected with the center of the suspension plate 2 along the position of the strip-shaped groove 201; and the lengths of the left and right strip-shaped grooves 201 of the middle strip-shaped groove 201 are gradually decreased progressively.
When the composite material wing solidification deformation prevention mold with the structure is applied, the method comprises the following steps:
(1) designing and manufacturing a corresponding composite material mould 6 according to the structural characteristics of the composite material;
(2) and (3) carrying out curing preparation work, fixing the composite material mold 6 on the bottom plate 1 in a fixing mode such as bolts, and fixing the bottom plate 1 on the ground to ensure the stability of the composite material mold 6 during paving. Then, sequentially placing a demoulding material layer 7, a composite material wing 8, an upper demoulding material 9 and a ventilated felt 10 on the composite material mould 6 from bottom to top, covering a vacuum bag 11, and completing preparation work such as air extraction, vacuum degree measurement and the like;
(3) before curing, the floor 1 is removed from the ground and the floor 1 is suspended from the sheave assembly 4 on the suspension plate 3 by the floor suspension ropes 2.
(4) According to the manufacturing method of the autoclave composite material, the temperature is raised for curing, and the mold is removed, so that the composite material structure with less influence of thermal stress is finally obtained. In the process of temperature rise curing, the mold is heated and expanded, and due to the adoption of a rope hanging mode, the deformation of the composite material mold 6 is converted into outward movement of the pulley assembly 3, so that the fixed support of the composite material mold 6 is converted into sliding friction between the pulley assembly 3 and the suspension plate 2, the thermal stress generated by a structural support mode is reduced, and the influence of the composite material mold 6 on the curing deformation of the composite material structure is reduced. In the cooling process, the deformation of the die is converted into the inward movement of the pulley assembly 3, and the stress concentration change of the composite material die 6 caused by the deformation is less, so that the influence on the composite material structure is less.
Claims (6)
1. The utility model provides a combined material wing prevents solidification deformation mould design which characterized in that: the composite material manufacturing mold is fixed on the bottom plate, and the bottom plate is fixed on the ground; sequentially placing a demoulding material layer, a composite material wing, an upper demoulding material and a ventilated felt on a composite material mould from bottom to top, and covering a vacuum bag to finish air extraction and vacuum degree measurement; two sides of the bottom plate are hung on pulley components correspondingly designed on two sides of the hanging plate through bottom plate hanging ropes installed at equal intervals; the suspension plate is hung on the upper surface inside the autoclave; the pulley assembly has a freedom of movement towards the central position of the suspension plate; and then heating, curing and demolding according to the autoclave composite material manufacturing method to finally obtain the composite material structure with less thermal stress influence.
2. The composite airfoil solidification deformation prevention mold design of claim 1, wherein: one of the installation positions of the bottom plate lifting ropes on the left side and the right side of the bottom plate is positioned at the central position of the side part of the bottom plate, and the other bottom plate lifting ropes are symmetrically distributed left and right relative to the central position of the bottom plate lifting ropes.
3. The composite airfoil solidification deformation prevention mold design of claim 1, wherein: the sliding range of the pulleys positioned in the middle of the pulleys towards the left and the right is gradually decreased.
4. The composite airfoil solidification deformation prevention mold design of claim 1, wherein: the pulley component is arranged in a strip-shaped groove which is formed in the suspension plate and is opened from the center of the suspension plate to the periphery in a ray scattering manner, so that the pulley block slides along the strip-shaped groove.
5. The composite airfoil solidification deformation prevention mold design of claim 4, wherein: the method specifically comprises the following steps: the strip-shaped groove is a hollow groove which penetrates through the upper surface and the lower surface of the suspension plate; the two are in a group, are respectively positioned at two sides of the suspension plate and are symmetrical relative to the center of the suspension plate; the positions of the strip-shaped grooves on the two sides of the suspension plate respectively correspond to the connecting positions of the lifting ropes of the bottom plate on the same side; the connecting positions of the mutually corresponding bottom plate lifting ropes and the central connecting line of the strip-shaped groove are vertical to the bottom plate; the length direction of each strip-shaped groove is connected with the center of the suspension plate along the position of the strip-shaped groove.
6. The composite airfoil solidification deformation prevention mold design of claim 4, wherein: the pulley assembly comprises two pulleys and a connecting shaft; the two pulleys are positioned on the upper surface of the suspension plate and are in matched lap joint with the long edges on the two sides of the strip-shaped groove through shoulders; two ends of the connecting shaft are connected with the two pulleys through bearings to form an integral pulley assembly; the connecting shaft is used for connecting a bottom plate lifting rope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810151683.9A CN108466435B (en) | 2018-02-14 | 2018-02-14 | Composite material wing solidification deformation prevention mold design |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810151683.9A CN108466435B (en) | 2018-02-14 | 2018-02-14 | Composite material wing solidification deformation prevention mold design |
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| Publication Number | Publication Date |
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| CN108466435A CN108466435A (en) | 2018-08-31 |
| CN108466435B true CN108466435B (en) | 2020-04-28 |
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| CN111645341B (en) * | 2020-06-11 | 2022-06-10 | 中国航空制造技术研究院 | Method for controlling curing deformation of composite material reinforced wall plate |
| CN118003531B (en) * | 2024-04-02 | 2024-05-31 | 中国科学院沈阳自动化研究所 | Modularized forming device and forming process for concave wing made of micro composite material |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP3116907B2 (en) * | 1998-05-14 | 2000-12-11 | 日本電気株式会社 | Hollow mold package |
| GB2391834B (en) * | 2001-05-31 | 2005-08-17 | Jhm Technologies Inc | Method and apparatus for molding composite articles |
| CN101181796B (en) * | 2006-11-14 | 2010-09-15 | 上海市建筑构件制品有限公司 | Curvature radius adjustable prefabricated box-beam mold and construction method thereof |
| JP2008262939A (en) * | 2007-04-10 | 2008-10-30 | Matsushita Electric Ind Co Ltd | Lead frame, sealing mold, and sealing method |
| CN102744854A (en) * | 2012-06-27 | 2012-10-24 | 苏州烁尔新材料有限公司 | Die head structure of ethylene-vinyl acetate (EVA) film extruder |
| JP5976568B2 (en) * | 2013-02-14 | 2016-08-23 | 住友重機械工業株式会社 | Injection molding machine |
| CN204999544U (en) * | 2015-09-22 | 2016-01-27 | 东莞市鸿田塑胶制品有限公司 | Injection mold hanging device |
| WO2017061047A1 (en) * | 2015-10-09 | 2017-04-13 | 株式会社Ihi | Fiber-reinforced composite member forming device |
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Application publication date: 20180831 Assignee: Beijing northern sky long hawk UAV Technology Co.,Ltd. Assignor: BEIHANG University Contract record no.: X2021990000039 Denomination of invention: Design of anti solidification deformation die for composite wing Granted publication date: 20200428 License type: Exclusive License Record date: 20210119 |
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