CN102114706B - Method for forming frame, stringer and covering of composite material component through integrated co-curing - Google Patents
Method for forming frame, stringer and covering of composite material component through integrated co-curing Download PDFInfo
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- CN102114706B CN102114706B CN 201010609685 CN201010609685A CN102114706B CN 102114706 B CN102114706 B CN 102114706B CN 201010609685 CN201010609685 CN 201010609685 CN 201010609685 A CN201010609685 A CN 201010609685A CN 102114706 B CN102114706 B CN 102114706B
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Abstract
The invention belongs to the technical field of composite material forming, and relates to a method for forming a frame, a stringer and a covering of composite material through integrated co-curing. The method adopts advanced temperature-resistant pressure-resistant foams to fill the inner part of the stringer, so that the stringer and the covering can be completed through one-step paving and pasting; a positioning and curing tooling for the frame is adopted, and special sharpening processing is performed on the positioning and curing tooling, so that the pressurizing problem on a joint face of the frame and the stringer can be solved, and the integrated co-curing forming of the frame, the covering and the stringer can be achieved; in addition, a rubber lining film technology is adopted, so that the pressure uniformity of the inner complicated structure and the quality of the inner surface can be ensured. The method for forming the frame, the stringer and the covering of a composite material component through integrated co-curing solves the problem of cementing interfacial effect on the joint face of the frame, the stringer and the covering in the traditional secondary cementing forming, improves the product quality, and satisfies the strength requirement of large load of the structure.
Description
Technical field
The invention belongs to technical field of composite material molding, relate to a kind of composite frame, long purlin and the whole co-curing forming method of covering.
Background technology
Some composite material component need to adopt whole co-curing to satisfy requirement of strength.Be composite material such as certain type tail boom, it is bearing larger tail-rotor load and oscillating load, is the main bearing member of full machine, requires to adopt to adopt whole co-curing to satisfy requirement of strength to frame, long purlin and covering.If adopt traditional frame, long purlin and covering to solidify separately, carry out again the second bonding moulding, the place easily produces interfacial effect at the splicing face, easily causes when being subject to large load and comes unstuck, even affect flight safety.
Summary of the invention
The objective of the invention is: a kind composite material component frame, long purlin and the whole co-curing forming method of covering are provided, to eliminate the interfacial effect between frame, beam and the covering, improve the quality of products, satisfy the requirement of strength of the large load of structure.
Technical scheme of the present invention is: a kind of composite material component frame, long purlin and the whole co-curing forming method of covering, and this method may further comprise the steps:
The first step, mould design and manufacture namely according to the design feature of composite material component, manufactures and designs the general frame mould, the positioning tool processing of fining away of reply frame in this step;
Second step, the whole laying of covering and long purlin is namely first carried out the covering laying at mould, then puts machined lightweight, heat resisting and pressure resisting foam, repaves the covering laying of pasting above the long purlin;
In the 3rd step, frame laying and assembling are namely carried out the frame laying to each frame on the positioning tool of frame, and then the frame that laying is good makes up together with putting into the general frame mould through the positioning tool of the processing of fining away;
The 4th step, lay inner rubber lining mould, be about to make in advance good corresponding rubber lining mould and put on the frame that combines, long purlin and the covering assembly, racked rubber lining mould makes it to fit with this composite material component, to guarantee uniformity and the surface quality of inner surface pressure;
In the 5th step, seal overall vacuum bag processed; Good rubber lining mould one is reinstated the vacuum bag overall package to be composite material component, mould and lay;
The 6th step, curing molding, good rubber lining module is put into the moulding of autoclave hot setting to be about to the packaged composite material component of above-mentioned vacuum bag, mould and lay.
Advantage of the present invention is: realized the requirement of the frame of composite material component, long purlin and the whole co-curing of covering, guaranteed the bonding quality at frame, long purlin and place, covering composition surface, satisfied the requirement of strength of composite.
Description of drawings
Accompanying drawing 1 is certain type Composite Panels structural representation, and wherein, 1 is frame, and 2 are long purlin, and 3 is covering.
Accompanying drawing 2 is positioning tool schematic diagrames of frame, and wherein 4 is positioning tool.
Accompanying drawing 3 is positioning tool sectional views of frame.
The specific embodiment
The below is described in further details the present invention.This composite material component frame, long purlin and the whole co-curing forming method of covering, the co-curing moulding of composite element employing to complexity has solved traditional secondary and has gluedd joint the splicing interfacial effect that the composition surface is located between moulding center, beam, the covering.
Operation principle of the present invention is: adopt advanced heat resisting and pressure resisting foam to fill as the inside of long purlin, a paving of long purlin and covering realization is finished; Employing solves the pressurization problem of frame Liang Jiehemianchu through location and the curing frock of the frame of special sharpening processing, realizes the long purlin assembly co-curing moulding of frame and covering; Uniformity and the inner surface quality of inner labyrinth pressure that adopted rubber lining mould technique guarantee.So namely realize the whole co-curing of frame, long purlin and covering, can effectively guarantee product quality again.
One embodiment of the present of invention are as follows:
1, mould design and manufacture, design feature according to composite material component, manufacture and design the general frame mould, in order to guarantee in whole co-curing process, the junction of the positioning tool of frame and covering and long purlin can apply vacuum pressure uniformly, to the processing of fining away of the junction of the positioning tool of frame and covering and long purlin, the sharpening angle of the positioning tool of frame is less than 30 °, and cusp is less than 1mm.
2, the whole laying of covering and long purlin is carried out the covering laying at mould first, then puts lightweight, the heat resisting and pressure resisting foam of nearly machining, the covering laying above the long purlin of last paving; This foam can be the PMI closed-cell foam, adopts this foaming structure, can guarantee that the cross sectional shape of long purlin under 180 ℃, 0.3MPa pressure is indeformable; The PMI closed-cell foam that has adopted ROHACELL company to produce in the present embodiment.
3, frame laying and assembling are carried out laying to each bulkhead on the paving frock of frame, then the bulkhead that laying is good makes up together with putting into covering paving mould through the location positioning tool of the processing of fining away;
4, lay inner rubber lining mould is put on the frame that combines, long purlin and the covering assembly making in advance good corresponding rubber lining mould, and racked rubber lining mould makes it to fit with this composite material component, to guarantee uniformity and the surface quality of inner surface pressure;
5, envelope overall vacuum bag processed, the rubber lining mould vacuum bag overall package that composite and lay are good
6, curing molding, the rubber lining mould that the composite material component that above-mentioned vacuum bag is packaged, mould and lay are good is put into the moulding of autoclave hot setting.
Claims (3)
1. a composite material component frame, long purlin and the whole co-curing forming method of covering is characterized in that, this method may further comprise the steps:
The first step, mould design and manufacture namely according to the design feature of composite material component, manufactures and designs the general frame mould, the positioning tool processing of fining away of reply frame in this step;
Second step, the whole laying of covering and long purlin is namely first carried out the covering laying at mould, then puts machined lightweight, heat resisting and pressure resisting foam, repaves the covering laying of pasting above the long purlin;
In the 3rd step, frame laying and assembling are namely carried out the frame laying to each frame on the positioning tool of frame, and then the frame that laying is good makes up together with putting into the general frame mould through the positioning tool of the processing of fining away;
The 4th step, lay inner rubber lining mould, be about to make in advance good corresponding rubber lining mould and put on the frame that combines, long purlin and the covering assembly, racked rubber lining mould makes it to fit with this composite material component, to guarantee uniformity and the surface quality of inner surface pressure;
In the 5th step, seal overall vacuum bag processed; Good rubber lining mould one is reinstated the vacuum bag overall package to be composite material component, mould and lay;
The 6th step, curing molding, good rubber lining mould is put into the moulding of autoclave hot setting to be about to the packaged composite material component of above-mentioned vacuum bag, mould and lay.
2. the whole co-curing forming method of a kind of composite material component frame as claimed in claim 1, long purlin and covering, it is characterized in that: the sharpening angle of the positioning tool of the frame in the first step of described method is less than 30 °, and cusp is less than 1mm.
3. the whole co-curing forming method of a kind of composite material component frame as claimed in claim 1, long purlin and covering, it is characterized in that: the foam in the second step of described method is the PMI closed-cell foam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010609685 CN102114706B (en) | 2010-12-29 | 2010-12-29 | Method for forming frame, stringer and covering of composite material component through integrated co-curing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010609685 CN102114706B (en) | 2010-12-29 | 2010-12-29 | Method for forming frame, stringer and covering of composite material component through integrated co-curing |
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| Publication Number | Publication Date |
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| CN102114706A CN102114706A (en) | 2011-07-06 |
| CN102114706B true CN102114706B (en) | 2013-02-13 |
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| CN 201010609685 Active CN102114706B (en) | 2010-12-29 | 2010-12-29 | Method for forming frame, stringer and covering of composite material component through integrated co-curing |
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| US9333713B2 (en) * | 2012-10-04 | 2016-05-10 | The Boeing Company | Method for co-curing composite skins and stiffeners in an autoclave |
| CN102909866A (en) * | 2012-10-24 | 2013-02-06 | 中国航空工业集团公司北京航空材料研究院 | Method for forming control of long joist axial line of composite material stiffened wall panel |
| CN103341987B (en) * | 2013-06-17 | 2015-09-09 | 沈阳飞机工业（集团）有限公司 | Ω long purlin orthogonal stiffeners composites wallboard co-curing reaction |
| CN105014851A (en) * | 2014-04-29 | 2015-11-04 | 哈尔滨飞机工业集团有限责任公司 | Middle-edge rib box forming method of horizontal-stabilizer co-curing piece |
| CN104197790B (en) * | 2014-09-01 | 2016-05-04 | 北京航空航天大学 | A kind of metal reinforcement-fiber-reinforced resin matrix compound material covering missile wing and preparation method thereof |
| CN104816488B (en) * | 2015-04-29 | 2019-05-07 | 哈尔滨点航科技发展有限公司 | Reinforcing rib siding co-curing forming method |
| CN105437537A (en) * | 2015-12-08 | 2016-03-30 | 成都飞机设计研究所 | Assembling method for airfoil total composite transonic flutter model |
| EP3272640B1 (en) | 2016-07-21 | 2019-04-17 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A helicopter with a fuselage and a composite tail boom |
| CN106273539A (en) * | 2016-08-29 | 2017-01-04 | 中航复合材料有限责任公司 | A kind of shape for hat Material Stiffened Panel co-curing moulding technique |
| WO2018170330A1 (en) * | 2017-03-16 | 2018-09-20 | The Boeing Company | Methods of co-bonding a first thermoset composite and a second thermoset composite to define a cured composite part |
| CN107199714B (en) * | 2017-06-27 | 2019-05-21 | 中国航空工业集团公司基础技术研究院 | A kind of variable curvature Composite Material Stiffened Panel moulding technique of co-curing |
| CN108500569A (en) * | 2018-04-10 | 2018-09-07 | 沈阳百祥机械加工有限公司 | Rectangle woollen is processed into stringer class parts machining process |
| CN110815862B (en) * | 2019-10-12 | 2022-09-20 | 哈尔滨飞机工业集团有限责任公司 | Laying method of full-height foam sandwich airfoil surface layer |
| CN115071163B (en) * | 2022-06-22 | 2024-03-08 | 沈阳飞机工业（集团）有限公司 | Integral co-curing forming process for S-shaped air inlet channel of multi-bulkhead carbon fiber composite material |
| CN116118220B (en) * | 2022-11-22 | 2024-10-22 | 江西昌兴航空装备股份有限公司 | Co-curing molding manufacturing method for composite unmanned aerial vehicle body |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1268466A1 (en) * | 1984-01-02 | 1986-11-07 | Предприятие П/Я Р-6285 | Ship deck covering |
| US5033178A (en) * | 1988-07-06 | 1991-07-23 | The Boeing Company | Assembly jig and method for making wing panels |
| DE3923320C2 (en) * | 1989-07-14 | 1998-04-09 | Dbt Gmbh | Drive and tensioning station of a chain scraper conveyor for mining companies, especially for use in longwall companies and. the like |
| CN101219587A (en) * | 2007-12-28 | 2008-07-16 | 同济大学 | Composite Skin Structure for Aircraft Fuselage and Its Preparation Technology |
| CN101596933A (en) * | 2009-07-06 | 2009-12-09 | 北京航空航天大学 | A Civil Aircraft Fuselage Bottom Structure Based on Crashworthy Design |
-
2010
- 2010-12-29 CN CN 201010609685 patent/CN102114706B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1268466A1 (en) * | 1984-01-02 | 1986-11-07 | Предприятие П/Я Р-6285 | Ship deck covering |
| US5033178A (en) * | 1988-07-06 | 1991-07-23 | The Boeing Company | Assembly jig and method for making wing panels |
| DE3923320C2 (en) * | 1989-07-14 | 1998-04-09 | Dbt Gmbh | Drive and tensioning station of a chain scraper conveyor for mining companies, especially for use in longwall companies and. the like |
| CN101219587A (en) * | 2007-12-28 | 2008-07-16 | 同济大学 | Composite Skin Structure for Aircraft Fuselage and Its Preparation Technology |
| CN101596933A (en) * | 2009-07-06 | 2009-12-09 | 北京航空航天大学 | A Civil Aircraft Fuselage Bottom Structure Based on Crashworthy Design |
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| CN102114706A (en) | 2011-07-06 |
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