CN101474839A - Mold structure for molding composite material - Google Patents
Mold structure for molding composite material Download PDFInfo
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- CN101474839A CN101474839A CNA2008101882899A CN200810188289A CN101474839A CN 101474839 A CN101474839 A CN 101474839A CN A2008101882899 A CNA2008101882899 A CN A2008101882899A CN 200810188289 A CN200810188289 A CN 200810188289A CN 101474839 A CN101474839 A CN 101474839A
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Abstract
The present invention provides a mold structure which is used for forming composite material, which comprises a forming body and a bracket. The forming body adopts iron-nickel low-expansion alloy material. The bracket adopts common steel material. A large-clearance connection mode is adopted between the forming body and the bracket. The invention has the advantage that the deformation of bracket is absorbed and counteracted through the clearance between connectors so that the deformation of bracket does not affect the deformation of forming body thereby the component has high accuracy after forming.
Description
Technical field
The invention belongs to machinery product, particularly a kind of mould structure that is used for composite material forming.
Background technology
Composite is as a kind of new and high technology material---and light and handy, tough and tensile, in social life, particularly in the manufacturing of aircraft, brought into play more and more important effect.As everyone knows, the moulding of the composite material parts environment compacted under that need vacuumize at high temperature (200 ℃): vacuumize strict airtight requirement (after vacuumizing, close vacuum valve, the vacuum seepage is no more than 0.010MPa in 5 minutes).Especially for the composite material parts of aircraft, its required precision strictness.The mould of composite material parts require to be heated heat up evenly with guarantee internal stress distortion that mould produces in temperature-rise period each to evenly, and mould can be more than 200OC, uses for a long time under the above condition of 0.5MPa.
Composite formed mould of the prior art uses common iron, aluminium mostly.The problem that prior art exists is that the thermal coefficient of expansion of shaping dies and the thermal coefficient of expansion of composite differ greatly.The distortion that the difference of this coefficient of thermal expansion causes composite material parts to get back to the generation of normal temperature natural conditions after the high-temperature vacuum moulding has very strong uncontrollability.Particularly resemble the composite material parts that aircraft is used, its complex structure, usually have a plurality of direction curvatures, utilize the designed mould of common material when being out of shape according to the curvature of part, its deflection does not just have having divided of primary and secondary, the distortion of all directions is different, and this distortion is relevant with various factors, comprises curvature, heating rate, evacuation rate, final temperature, temperature retention time of part or the like.In sum, the problem of traditional shaping mould existence has: 1, the thermal coefficient of expansion of mold materials (common iron, aluminium) and the thermal coefficient of expansion of composite differ greatly, and cause not reaching required precision behind the forming parts.2, the structure of part has complicated curvature, causes the mould structure complexity, and die deformation is uncontrollable.
Summary of the invention
The object of the present invention is to provide a kind of a kind of mould structure that is used for composite material forming that can overcome the prior art shortcoming.
A kind of being used for, contain contoured body and support, it is characterized in that described contoured body selects iron nickel low-expansion alloy material for use, support is selected the ordinary steel material for use, adopts big gap connected mode between contoured body and the support.
Above-mentioned contoured body is connected with big gap between the support and is meant the cantilever-shaped connecting bolt that is provided with a plurality of levels on support, contoured body is made up of forming surface and a plurality of stiffener, stiffener is vertically fixed on the inboard of forming surface, the lower end of stiffener is provided with connecting hole, cantilever bolt on the support is supported in the connecting hole of stiffener, between this connecting hole and the cantilever bolt enough gaps is arranged.
Iron nickel low-expansion alloy material, English INVAR steel also claims invar alloy, formal name used at school: iron nickel low-expansion alloy 4J36.Be commonly called as invar, constant steel.The INVAR steel is a kind of dilval of nickeliferous 36%, is at first found by Frenchman C.E.Guillaume in 1896.Near the thermal coefficient of expansion of this alloy room temperature is low.The coefficient of expansion is average out at normal temperatures: 1.6X10-6/ ℃, and the coefficient of expansion is more stable at 80～200 ℃.
Composite material forming mould structure of the present invention, its contoured body adopts iron nickel low-expansion alloy material to make, major advantage is that the heat spray of the iron nickel low-expansion alloy material coefficient that expands is approaching with the bloated coefficient of heat spray of composite, thereby has very high accuracy after making forming parts.
In order to reduce the manufacturing cost of shaping dies, the holder part of composite material forming mould structure of the present invention still adopts common iron or aluminum alloy materials, in order to coordinate the thermal coefficient of expansion of mould molding body holder part, the temperature distortion that overcomes holder part influences the shape of contoured body, the present invention connects being designed to contoured body and being connected of support a kind of big gap, support only plays a supportive role to contoured body, the distortion of support absorbs by the gap between the connector offsets, and makes the distortion of support not influence the distortion of contoured body.
Forming die structure below in conjunction with certain aircraft composite material parts describes in further detail the present invention, so that more can understand design feature advantage of the present invention.
Description of drawings
Fig. 1 is the overall structure signal of composite formed mould
Fig. 2 is the signal of mould molding main body structure
Fig. 3 is the structural representation of mould rack
Fig. 4 is that the mould molding body is connected the horizontal section structural representation with support
Fig. 5 is that the mould molding body is connected the longitudinal profile structural representation with support
Fig. 6 is the auxiliary structural representation of bleeding of mould part
Number description: 1 part noumenon, 2 contoured body, 3 stiffeners, 4 profile bodies, 5 supports, 6 connecting plates, 7 tilt props, 8 cantilever bolts, 9 screws, 10 pressing plates, 11 link slots, 12 pedestals, 13 auxiliary bleed structure, 14 through holes, 15 big gaps
By way of example
Embodiment provided by the invention is the mould of certain aircraft engine outer cover covering support member, and this aircraft engine outer cover covering support member is a composite, and profile is semicircle, and diameter reaches 3.7m, and the cross section is L shaped.Spare part outside measurement precision prescribed height mustn't have big slit when theoretical profile and outer skin assembling.This has just strengthened the manufacture difficulty of part.And the manufacturing tolerance of mould is 1/3rd of a part tolerance.This makes the difficulty of Mould design and manufacturing also difficult more.
Referring to accompanying drawing, Fig. 1 is the overall structure signal of this forming parts mould, and among the figure, die main body is made up of the contoured body 2 on top and support 5 two parts of bottom.Contoured body 2 is made by iron nickel low-expansion alloy material, contain profile body 4 and stiffener 3, profile body 4 is arc-shaped slot plate structures that design according to the formal parameter of part noumenon 1, stiffener 4 is a kind of for increasing the platy structure of contoured body intensity, have a plurality of stiffeners 3 to distribute and be fixed on the inboard of profile body 4, the space plane of each stiffener and profile body 4 are preferably in vertical state; The support 5 of mould is made by common iron, contains the frame-type pedestal 12 and a plurality of connecting plates 6 that are vertically fixed on the pedestal of Fang Gang welding, and the position of this connecting plate 6 is corresponding with the stiffener 3 of contoured body with quantity.
In order to realize that contoured body is connected with the big gap of holder part, as shown in Figures 2 and 3, be provided with two inverted U link slots 11 at the downside of contoured body stiffener 3; Upper end at each connecting plate of support is fixed with two cantilever bolts 8, for stable support, is fixed with tilt prop 7 between the lower end of the opposite direction connecting plate of cantilever bolt and pedestal 12.Being worth ben is that the height of this U type link slot 11 and width are greater than the diameter of cantilever bolt 8.During assembling, the link slot 11 of contoured body stiffener is placed on the cantilever bolt 8 of rack connecting plate, pressing plate 10 fixedly is enclosed on the notch of link slot 11 with screw 9 again, make the cantilever bolt except that the top and between the stiffener 3 of contoured body, enough big gap 15 be arranged, to adapt to the distortion of support.
For the big gap of further satisfying between two kinds of different materials of contoured body and support combines, middle part with the contoured body stiffener among the embodiment is provided with strip through hole 14, be used for installing the auxiliary structure 13 of bleeding, as shown in Figure 6, even auxiliary in the mould bleeds between structure 13 and the contoured body also to be a kind of big gap or to flexibly connect, in order that the thermal deformation of the auxiliary structure of bleeding is unlikely to have influence on contoured body.
Claims (3)
1, a kind of mould structure that is used for composite material forming contains contoured body and support, it is characterized in that described contoured body selects iron nickel low-expansion alloy material for use, and support is selected the ordinary steel material for use, adopts big gap connected mode between contoured body and the support.
2, the mould structure that is used for composite material forming as claimed in claim 1, it is characterized in that described contoured body is connected with big gap between the support is meant the cantilever bolt that is provided with a plurality of levels on support, contoured body is made up of forming surface and a plurality of stiffener, stiffener is vertically fixed on the inboard of forming surface, the lower end of stiffener is provided with connecting hole, cantilever bolt on the support is supported in the connecting hole of stiffener, between this connecting hole and the cantilever bolt enough gaps is arranged.
3, the mould structure that is used for composite material forming as claimed in claim 2 is characterized in that the through hole that supplementary structure is installed is arranged on the described reinforcement plate body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008101882899A CN101474839A (en) | 2008-12-24 | 2008-12-24 | Mold structure for molding composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008101882899A CN101474839A (en) | 2008-12-24 | 2008-12-24 | Mold structure for molding composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101474839A true CN101474839A (en) | 2009-07-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2008101882899A Pending CN101474839A (en) | 2008-12-24 | 2008-12-24 | Mold structure for molding composite material |
Country Status (1)
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| CN (1) | CN101474839A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104339495A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Connecting mode of sample plate frame type forming mold body and frame |
| CN105711110A (en) * | 2016-04-01 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Die and compression forming method for composite-material formed parts |
| CN106738505A (en) * | 2016-12-02 | 2017-05-31 | 哈尔滨工业大学 | A kind of manufacture method of the composite material shaping mould with composite construction |
| CN111452261A (en) * | 2020-04-09 | 2020-07-28 | 中车青岛四方机车车辆股份有限公司 | Mould and autoclave molding process equipment |
| CN112589474A (en) * | 2020-12-11 | 2021-04-02 | 彭州东硕数控设备有限公司 | Thermal expansion machine tool precision retaining device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2449887Y (en) * | 2000-11-17 | 2001-09-26 | 丽晨企业厂有限公司 | Mould frame |
| WO2007087786A1 (en) * | 2006-02-02 | 2007-08-09 | Thyssenkrupp Vdm Gmbh | Iron-nickel-cobalt alloy |
| AT503547A4 (en) * | 2006-05-16 | 2007-11-15 | Fischer Adv Components Gmbh | hardening tool |
-
2008
- 2008-12-24 CN CNA2008101882899A patent/CN101474839A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2449887Y (en) * | 2000-11-17 | 2001-09-26 | 丽晨企业厂有限公司 | Mould frame |
| WO2007087786A1 (en) * | 2006-02-02 | 2007-08-09 | Thyssenkrupp Vdm Gmbh | Iron-nickel-cobalt alloy |
| AT503547A4 (en) * | 2006-05-16 | 2007-11-15 | Fischer Adv Components Gmbh | hardening tool |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104339495A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Connecting mode of sample plate frame type forming mold body and frame |
| CN105711110A (en) * | 2016-04-01 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Die and compression forming method for composite-material formed parts |
| CN106738505A (en) * | 2016-12-02 | 2017-05-31 | 哈尔滨工业大学 | A kind of manufacture method of the composite material shaping mould with composite construction |
| CN111452261A (en) * | 2020-04-09 | 2020-07-28 | 中车青岛四方机车车辆股份有限公司 | Mould and autoclave molding process equipment |
| CN111452261B (en) * | 2020-04-09 | 2022-02-15 | 中车青岛四方机车车辆股份有限公司 | Mould and autoclave molding process equipment |
| CN112589474A (en) * | 2020-12-11 | 2021-04-02 | 彭州东硕数控设备有限公司 | Thermal expansion machine tool precision retaining device |
| CN112589474B (en) * | 2020-12-11 | 2023-04-14 | 彭州东硕数控设备有限公司 | Thermal expansion machine tool precision retaining device |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20090708 |