CN106976187A - A kind of many curved surfaces close corner structure technique for aircraft composite forming parts frock - Google Patents
A kind of many curved surfaces close corner structure technique for aircraft composite forming parts frock Download PDFInfo
- Publication number
- CN106976187A CN106976187A CN201710239904.3A CN201710239904A CN106976187A CN 106976187 A CN106976187 A CN 106976187A CN 201710239904 A CN201710239904 A CN 201710239904A CN 106976187 A CN106976187 A CN 106976187A
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- Prior art keywords
- split module
- split
- module
- curved surfaces
- corner structure
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Classifications
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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
- B29C33/30—Mounting, exchanging or centering
- B29C33/301—Modular mould systems [MMS], i.e. moulds built up by stacking mould elements, e.g. plates, blocks, rods
-
- 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
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3835—Designing moulds, e.g. using CAD-CAM
-
- 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
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention belongs to manufacture technology of composite material field, it is related to a kind of many curved surfaces and closes corner structure technique for aircraft composite forming parts frock.Forming frock is divided into five split modules by the present invention, allow the knockout course after forming parts that support base first is closed into corner structure technique for aircraft composite part and preceding split module, left split module from many curved surfaces, middle split module, right split module, unloaded in rear split module, middle split module is taken out using crowbar from unitary mould again, then left split module and right split module are removed, finally preceding split module and rear split module are taken out from part, the demoulding of part is completed.This die design method can solve the release problems that almost all of complexity closes corner structure composite material parts, while ensureing the operability of part manufacturing process and the quality of part after shaping.
Description
Technical field
The invention belongs to manufacture technology of composite material field, it is related to a kind of many curved surfaces and closes corner structure technique for aircraft composite part
Forming frock.
Background technology
Composite is due to its high specific strength, and high specific stiffness, designability are strong, fatigue crack-resistant performance is good, corrosion-resistant, chi
The advantages of very little stability is good and is easy to large area monolithic molding, it has also become one of contemporary topmost Aircraft Structure Materials.It is multiple
The position and consumption that condensation material is applied aboard have turned into weighs one of advanced outstanding feature of aircaft configuration.With compound
The continuous improvement of material consumption and composite material parts design level aboard, composite material parts also by original " C " type,
The conventional shapes such as " L " type, " I " type, T-shape are continued to develop, and occur in that many curved surfaces close the irregular shapes such as corner structure, and this is to compound
The shaping of material proposes higher requirement.Current composite material shaping mould includes metal die, composite material mould, rubber
Mould, foam mold, gypsum mold and soluble polymer mould etc..The manufacture of traditional irregular shape structural composite material part
Part can be obtained by the way of mould by destroying after the forming parts such as rubber shrinking die, foam, gypsum, but these moulds
Tool is only applicable to be molded once or several times, is unfavorable for batch production, and using the composite material component port of these Making molds
Face precision, quality etc. are generally not so good as metal die.Close corner structure composite material parts with many curved surfaces of metals mold manufacturing, it is necessary to
Split mold is designed, and can guarantee that parts quality, be easy to the Split mold of the demoulding to structure design, the accuracy of manufacture and coordinate positioning
Suffer from higher requirement.
The content of the invention
It is an object of the invention to provide a kind of reasonable in design, accuracy of manufacture it is high for a kind of many curved surfaces close corner structure fly
Machine composite material parts shaping metal die, while solve many curved surfaces close corner structure technique for aircraft composite part shaping and
Release problems.
The technical scheme is that,
Many curved surfaces close corner structure technique for aircraft composite forming parts frock including preceding split module, left split module, in point
Module, right split module, rear split module and support base, preceding split module, left split module, middle split module, the right side point
The outer mold surface of unitary mould closes the inner mold of corner structure technique for aircraft composite part with many curved surfaces after module, rear split block combiner
Face is consistent, and preceding split module, left split module, middle split module, right split module, rear split module are loaded on support bottom after coordinating
Positioned on seat, the assembly after described left split module, middle split module, right split block combiner and point of preceding split module
From face and support base plane angle α be 90 ° of 75 °≤α ＜, left split module, middle split module, right split block combiner after
The parting surface of assembly and rear split module and the angle β of support base plane be 75 °≤β≤90 °；Middle split module is
There are two parting surfaces, i.e. lower-left parting surface and left parting surface in T-shaped, left split module and middle split module, lower-left parting surface with
The plane of support base is parallel, and the angle of left parting surface and lower-left parting surface is θ, and θ angles are closed corner structure aircraft more than many curved surfaces and answered
1 °~20 ° of angle between condensation material part transverse center section and horizontal plane, right split module has two with middle split module
Parting surface, i.e. bottom right parting surface and right parting surface, bottom right parting surface are parallel with the plane of support base, right parting surface and bottom right point
Angle from face is 180 ° of-θ.
Described left split module is being stripped breach with the contact surface of middle split module, leaving two, during for being stripped
The separation of left split module and middle split module.
Described right split module is being stripped breach with the contact surface of middle split module, leaving two, during for being stripped
The separation of right split module and middle split module.
Described preceding split module, left split module, middle split module, right split module, rear split module and a branch
Base is supportted to manufacture using digital control processing.
Described all mold materials all use Steel material or aluminum.
Unitary mould after the combination can be used for part laying and the thermoforming of fiber-reinforced resin base prepreg.
During demoulding first by support base from many curved surfaces close corner structure technique for aircraft composite part and preceding split module,
Left split module, middle split module, right split module, unload in rear split module, then middle split module is taken out, then remove
Left split module and right split module, finally remove preceding split module and rear split module from part, complete the de- of part
Mold process.
The beneficial effect of this programme：
The present invention solves shaping and the release problems that many curved surfaces close corner structure technique for aircraft composite part, compared to traditional mould
Tool, the appearance and size precision for ensureing part is coordinated by rigid Split mold, while being designed using rational drafting angle and de-
Mould mode solves the release problems that many curved surfaces close corner structure, allow the knockout course after forming parts first by support base from
Many curved surfaces close corner structure technique for aircraft composite part and preceding split module, left split module, middle split module, right split module,
Unloaded afterwards in split module, then middle split module taken out using crowbar from unitary mould, then remove left split module and
Right split module, finally takes out preceding split module and rear split module from part, completes the demoulding of part.This mould is set
Meter method can solve almost all of complexity and close the release problems of corner structure composite material parts, while ensureing that part was manufactured
The quality of part after the operability of journey and shaping.
Present invention is mainly used for the manufacture that many curved surfaces close corner structure technique for aircraft composite part.Many curved surfaces of the present invention close angle
Structure technique for aircraft composite forming parts frock uses Split mold and compounding technique, using five pieces of Split molds and a base
Unitary mould is combined into as prepreg laying mould, mould can be ensured by the bit combination of five pieces of Split molds and support base
Have position, control element precision；Split pattern can be dismantled simultaneously, solve the release problems after forming parts.
Brief description of the drawings
Fig. 1 closes corner structure technique for aircraft composite forming parts frock schematic diagram for the present invention's for many curved surfaces, wherein, 1
It is preceding split module, 2 be left split module, and 3 be middle split module, and 4 be right split module, and 5 be rear split module, and 6 be support
Base.
Fig. 2 closes the separation signal of corner structure technique for aircraft composite forming parts tooling base for the present invention for many curved surfaces
Figure, wherein the assembly being made up of preceding split module, left split module, middle split module, right split module, rear split module
Mo(u)ld bottom half face is consistent with the type face of base die cavity.
Fig. 3 closes corner structure technique for aircraft composite forming parts frock for many curved surfaces for the present invention and removes the side after base
View, wherein, 7 be the assembly after left split module, middle split module, right split block combiner and the separation of preceding split module
Face, 8 be the assembly and the parting surface of rear split module after left split module, middle split module, right split block combiner, and 9 are
Support base plane, α is the assembly after left split module, middle split module, right split block combiner and preceding split module
Parting surface and the angle of support base plane, β are the assembly after left split module, middle split module, right split block combiner
With the parting surface and the angle of support base plane of rear split module.
Fig. 4 for the present invention be used for many curved surfaces close corner structure technique for aircraft composite forming parts frock left split module,
Mould after middle split module, right split block combiner and the parting surface sectional view of preceding split module, 10 be left split module with
The lower-left parting surface of middle split module, 11 be the left parting surface of left split module and middle split module, and its angle is θ.12 be the right side
The bottom right parting surface of split module and middle split module, 13 be the right parting surface of right split module and middle split module, its angle
For (180 ° of-θ).14 be the crowbar mouthful on left separation module, and 15 be the crowbar mouthful on right separation module.
Embodiment
The present invention is elaborated below in conjunction with the accompanying drawings.
Many curved surfaces close corner structure technique for aircraft composite forming parts frock including preceding split module 1, left split module 2, in
Split module 3, right split module 4, the support base of rear split module 5 and 6.When in use, first by preceding split module 1, left split
Module 2, middle split module 3, right split module 4, rear split module 5 are combined, and are then placed in 6 support bases and are determined
Position, then carries out laying encapsulation and solidification in unitary mould.
Knockout course after forming parts, can first by support base 6 from part and preceding split module 1, left split module 2,
Middle split module 3, right split module 4, unload in rear split module 5, then pass through the crowbar mouthful 14 on left separation module, the right side point
From the crowbar mouthful 15 in module, left parting surface 11 and right split by middle split module 3 along left split module and middle split module
Module is taken out with right 13 faces that separate of middle split module, then removes left split module 2 and right split module 4, finally from part
Preceding split module 1 and rear split module 5 are taken out, the knockout course of part is finally completed.
In above-mentioned technical proposal, split module in split module, 2 left split modules, 3 before described 1,4 right split modules,
Split module and 6 support bases use metal material Q235A steel digital control processing manufacture to ensure high temperature, high-pressure molding mistake after 5
The rigidity and precision of journey mould structure, it can be ensured that the Forming Quality and precision of part.
Claims (7)
1. a kind of many curved surfaces close corner structure technique for aircraft composite forming parts frock, it is characterised in that many curved surfaces close corner structure and flown
Machine composite material parts forming frock includes preceding split module, left split module, middle split module, right split module, rear split
It is whole after module and support base, preceding split module, left split module, middle split module, right split module, rear split block combiner
The outer mold surface of mould is consistent with the inner mold face that many curved surfaces close corner structure technique for aircraft composite part, preceding split module, left split
Module, middle split module, right split module, rear split module are loaded in support base after coordinating and positioned, described left split pattern
Assembly and the parting surface and the folder of support base plane of preceding split module after block, middle split module, right split block combiner
Angle α is 90 ° of 75 °≤α ＜, the assembly after left split module, middle split module, right split block combiner and rear split module
Parting surface and the β of support base plane included angle are 75 °≤β≤90 °；Middle split module is inverted T-shaped, left split module and middle split
There are two parting surfaces, i.e. lower-left parting surface and left parting surface in module, lower-left parting surface is parallel with the plane of support base, a left side point
Angle from face and lower-left parting surface is θ, θ angles be more than many curved surfaces close corner structure technique for aircraft composite part transverse center section and
There is two parting surfaces, i.e. bottom right parting surface and right point with middle split module in 1 °~20 ° of the angle between horizontal plane, right split module
From face, bottom right parting surface is parallel with the plane of support base, and the angle of right parting surface and bottom right parting surface is 180 ° of-θ.
2. a kind of many curved surfaces as claimed in claim 1 close corner structure technique for aircraft composite forming parts frock, it is characterised in that
Described left split module is with the contact surface of middle split module, leaving two demoulding breach, left split pattern during for being stripped
Block and the separation of middle split module.
3. a kind of many curved surfaces as claimed in claim 1 close corner structure technique for aircraft composite forming parts frock, it is characterised in that
Described right split module is with the contact surface of middle split module, leaving two demoulding breach, right split pattern during for being stripped
Block and the separation of middle split module.
4. a kind of many curved surfaces as claimed in claim 1 close corner structure technique for aircraft composite forming parts frock, it is characterised in that
Described preceding split module, left split module, middle split module, right split module, rear split module and a support base are equal
Manufactured using digital control processing.
5. a kind of many curved surfaces as claimed in claim 1 close corner structure technique for aircraft composite forming parts frock, it is characterised in that
Described all mold materials all use Steel material or aluminum.
6. a kind of many curved surfaces as claimed in claim 1 close corner structure technique for aircraft composite forming parts frock, it is characterised in that
Unitary mould after the combination can be used for part laying and the thermoforming of fiber-reinforced resin base prepreg.
7. a kind of many curved surfaces as claimed in claim 1 close corner structure technique for aircraft composite forming parts frock, it is characterised in that
Support base is first closed into corner structure technique for aircraft composite part and preceding split module, left split pattern from many curved surfaces during demoulding
Block, middle split module, right split module, unload in rear split module, then middle split module is taken out, then remove left split pattern
Block and right split module, finally remove preceding split module and rear split module from part, complete the knockout course of part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710239904.3A CN106976187B (en) | 2017-04-13 | 2017-04-13 | A kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710239904.3A CN106976187B (en) | 2017-04-13 | 2017-04-13 | A kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling |
Publications (2)
| Publication Number | Publication Date |
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| CN106976187A true CN106976187A (en) | 2017-07-25 |
| CN106976187B CN106976187B (en) | 2019-02-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710239904.3A Active CN106976187B (en) | 2017-04-13 | 2017-04-13 | A kind of more curved surfaces close corner structure technique for aircraft composite forming parts tooling |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109352877A (en) * | 2018-12-07 | 2019-02-19 | 江西洪都航空工业集团有限责任公司 | A kind of sectional type S shaped cylindrical composite material structural member forming frock structure |
| CN112092402A (en) * | 2020-08-26 | 2020-12-18 | 中国航空制造技术研究院 | Forming tool and forming method for composite material foam sandwich structure |
| CN112549590A (en) * | 2020-11-20 | 2021-03-26 | 昌河飞机工业（集团）有限责任公司 | Forming tool for waist drum-shaped molded part |
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| CN101973130A (en) * | 2010-08-27 | 2011-02-16 | 上海晋飞复合材料科技有限公司 | Emulsion liner auxiliary pre-impregnating mould pressing prepared integrated front fork mould and method thereof |
| CN105252790A (en) * | 2015-11-26 | 2016-01-20 | 中国航空工业集团公司基础技术研究院 | Composite material forming mould |
| CN105269721A (en) * | 2015-11-26 | 2016-01-27 | 中国航空工业集团公司基础技术研究院 | Forming mould for composite material part of box type closed-angle structure |
-
2017
- 2017-04-13 CN CN201710239904.3A patent/CN106976187B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101973130A (en) * | 2010-08-27 | 2011-02-16 | 上海晋飞复合材料科技有限公司 | Emulsion liner auxiliary pre-impregnating mould pressing prepared integrated front fork mould and method thereof |
| CN105252790A (en) * | 2015-11-26 | 2016-01-20 | 中国航空工业集团公司基础技术研究院 | Composite material forming mould |
| CN105269721A (en) * | 2015-11-26 | 2016-01-27 | 中国航空工业集团公司基础技术研究院 | Forming mould for composite material part of box type closed-angle structure |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109352877A (en) * | 2018-12-07 | 2019-02-19 | 江西洪都航空工业集团有限责任公司 | A kind of sectional type S shaped cylindrical composite material structural member forming frock structure |
| CN112092402A (en) * | 2020-08-26 | 2020-12-18 | 中国航空制造技术研究院 | Forming tool and forming method for composite material foam sandwich structure |
| CN112549590A (en) * | 2020-11-20 | 2021-03-26 | 昌河飞机工业（集团）有限责任公司 | Forming tool for waist drum-shaped molded part |
| CN112549590B (en) * | 2020-11-20 | 2022-11-18 | 昌河飞机工业（集团）有限责任公司 | Forming tool for waist drum-shaped molded part |
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| Publication number | Publication date |
|---|---|
| CN106976187B (en) | 2019-02-15 |
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