CN102114706A - 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
- Publication number
- CN102114706A CN102114706A CN2010106096851A CN201010609685A CN102114706A CN 102114706 A CN102114706 A CN 102114706A CN 2010106096851 A CN2010106096851 A CN 2010106096851A CN 201010609685 A CN201010609685 A CN 201010609685A CN 102114706 A CN102114706 A CN 102114706A
- Authority
- CN
- China
- Prior art keywords
- frame
- covering
- composite material
- curing
- mould
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
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 adopt whole co-curing to satisfy requirement of strength.As certain type tail boom is the full composite material structure, and it is bearing bigger 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 the second bonding moulding again, the place is easy to generate interfacial effect at the splicing face, causes easily when being subjected to big load and comes unstuck, even influence 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,, improve the quality of products, satisfy the requirement of strength of the big load of structure to eliminate the interfacial effect between frame, beam and the covering.
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 manufactures and designs, and promptly 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;
In second step, the whole shop of covering and long purlin layer promptly carries out earlier covering shop layer on mould, put lightweight, heat resisting and pressure resisting foam through machining then, repaves the covering shop layer that pastes above the long purlin;
In the 3rd step, frame is spread layer and is assembled, and promptly on the positioning tool of frame each frame is carried out frame shop layer, will spread layer good frame then and make up together with putting into the general frame mould through the location 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 the uniformity and the surface quality of inner surface pressure;
The 5th step, envelope system overall vacuum bag; Good rubber lining mould one is reinstated the vacuum bag overall package to be composite material component, mould and lay;
In the 6th step, curing molding is about to the packaged parts of above-mentioned vacuum bag and puts into the moulding of autoclave hot setting.
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 wall panel structure schematic diagram, 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
Below the present invention is described in further details.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 the location and the curing frock of the frame of special sharpening processing, realizes the long purlin assembly co-curing moulding of frame and covering; The uniformity and the inner surface quality of inner labyrinth pressure that adopted rubber lining mould technical guarantee.So promptly 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 manufactures and designs, 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 shop of covering and long purlin layer carries out earlier covering shop layer on mould, puts lightweight, the heat resisting and pressure resisting foam of nearly machining then, the covering shop layer 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 is spread layer and assembling, on the paving frock of frame each bulkhead is spread layer, will spread the good bulkhead of layer then and make 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 good corresponding rubber lining mould in advance, and racked rubber lining mould makes it to fit with this composite material component, to guarantee the uniformity and the surface quality of inner surface pressure;
5, envelope system overall vacuum bag, the rubber lining mould vacuum bag overall package that composite and lay are good
6, curing molding, the parts that above-mentioned vacuum bag is packaged are 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 manufactures and designs, and promptly 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;
In second step, the whole shop of covering and long purlin layer promptly carries out earlier covering shop layer on mould, put lightweight, heat resisting and pressure resisting foam through machining then, repaves the covering shop layer that pastes above the long purlin;
In the 3rd step, frame is spread layer and is assembled, and promptly on the positioning tool of frame each frame is carried out frame shop layer, will spread layer good frame then and make up together with putting into the general frame mould through the location 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 the uniformity and the surface quality of inner surface pressure;
The 5th step, envelope system overall vacuum bag, good rubber lining mould one is reinstated the vacuum bag overall package to be about to composite material component, mould and lay;
In the 6th step, curing molding is about to the packaged parts of above-mentioned vacuum bag and puts into the moulding of autoclave hot setting.
2. a composite material component frame, long purlin and the whole co-curing forming method of 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. a composite material component frame, long purlin and the whole co-curing forming method of covering, it is characterized in that: the foam in 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102114706A true CN102114706A (en) | 2011-07-06 |
| CN102114706B CN102114706B (en) | 2013-02-13 |
Family
ID=44213678
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102114706B (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103341987A (en) * | 2013-06-17 | 2013-10-09 | 沈阳飞机工业（集团）有限公司 | Co-curing process for omega-stringer vertical and horizontal reinforcement composite integral wallboard |
| CN104197790A (en) * | 2014-09-01 | 2014-12-10 | 北京航空航天大学 | Metal reinforced bar-fiber reinforced resin matrix composite material skin missile wing and manufacturing method thereof |
| KR20150063355A (en) * | 2012-10-04 | 2015-06-09 | 더 보잉 컴파니 | Method and apparatus for co-curing composite skins and stiffeners in an autoclave |
| CN104816488A (en) * | 2015-04-29 | 2015-08-05 | 哈尔滨点航科技发展有限公司 | Reinforcing rib wall plate co-curing forming method |
| 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 |
| 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 |
| 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 |
| CN107199714A (en) * | 2017-06-27 | 2017-09-26 | 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 |
| EP3272640A1 (en) | 2016-07-21 | 2018-01-24 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A helicopter with a fuselage and a composite tail boom |
| 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 |
| CN110167745A (en) * | 2017-03-16 | 2019-08-23 | 波音公司 | It is glued the first same with thermosetting compound material and the second same with thermosetting compound material altogether to define the method for solidifying composite material component |
| CN110815862A (en) * | 2019-10-12 | 2020-02-21 | 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 |
| CN115071163A (en) * | 2022-06-22 | 2022-09-20 | 沈阳飞机工业（集团）有限公司 | Integral co-curing forming process for multi-partition-frame carbon fiber composite S-shaped air inlet channel |
| CN116118220A (en) * | 2022-11-22 | 2023-05-16 | 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 stressed-skin construction for fuselage and technique of preparing the same |
| CN101596933A (en) * | 2009-07-06 | 2009-12-09 | 北京航空航天大学 | A kind of based on crash-worthiness design-calculated civil aircraft fuselage bottom structure |
-
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 stressed-skin construction for fuselage and technique of preparing the same |
| CN101596933A (en) * | 2009-07-06 | 2009-12-09 | 北京航空航天大学 | A kind of based on crash-worthiness design-calculated civil aircraft fuselage bottom structure |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102059227B1 (en) | 2012-10-04 | 2019-12-24 | 더 보잉 컴파니 | Method and apparatus for co-curing composite skins and stiffeners in an autoclave |
| CN104703782B (en) * | 2012-10-04 | 2017-05-17 | 波音公司 | Method and apparatus for co-curing composite skins and stiffeners in an autoclave |
| KR20150063355A (en) * | 2012-10-04 | 2015-06-09 | 더 보잉 컴파니 | Method and apparatus 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 |
| CN103341987A (en) * | 2013-06-17 | 2013-10-09 | 沈阳飞机工业（集团）有限公司 | Co-curing process for omega-stringer vertical and horizontal reinforcement composite integral wallboard |
| 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 |
| CN104197790A (en) * | 2014-09-01 | 2014-12-10 | 北京航空航天大学 | Metal reinforced bar-fiber reinforced resin matrix composite material skin missile wing and manufacturing 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 |
| CN104816488A (en) * | 2015-04-29 | 2015-08-05 | 哈尔滨点航科技发展有限公司 | Reinforcing rib wall plate 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 |
| EP3272640A1 (en) | 2016-07-21 | 2018-01-24 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A helicopter with a fuselage and a composite tail boom |
| US10457373B2 (en) | 2016-07-21 | 2019-10-29 | Airbus Helicopters Deutschland GmbH | Aircraft 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 |
| CN110167745A (en) * | 2017-03-16 | 2019-08-23 | 波音公司 | It is glued the first same with thermosetting compound material and the second same with thermosetting compound material altogether to define the method for solidifying composite material component |
| CN107199714A (en) * | 2017-06-27 | 2017-09-26 | 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 |
| CN110815862A (en) * | 2019-10-12 | 2020-02-21 | 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 |
| CN115071163A (en) * | 2022-06-22 | 2022-09-20 | 沈阳飞机工业（集团）有限公司 | Integral co-curing forming process for multi-partition-frame carbon fiber composite S-shaped air inlet channel |
| 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 |
| CN116118220A (en) * | 2022-11-22 | 2023-05-16 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102114706B (en) | 2013-02-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102114706B (en) | Method for forming frame, stringer and covering of composite material component through integrated co-curing | |
| CN105965917B (en) | The co-curing moulding technique of composite material bilateral reinforcement fuselage framework | |
| CN101489769B (en) | Composite manufacturing method | |
| CN105538746B (en) | Composite large-scale product part shaped face autoclave molding mould and method | |
| CN107738457A (en) | A kind of integrated forming technique of unmanned aerial vehicle body | |
| CN106042503B (en) | A kind of preparation method of Ultralight sandwich structure composite material | |
| CN105216345B (en) | RTM global formation orthogonal stiffenerses structure member (cover)s and its manufacture method | |
| CN107175837B (en) | A kind of honeycomb cladding spicing forming type method | |
| CN103552256A (en) | Autoclave integrated-forming method for composite double-surface-ribbed wallboard | |
| CN110239112A (en) | A kind of processing method of composite material shape for hat Material Stiffened Panel | |
| CN103862764A (en) | Method for preparing honeycomb interlayer structure composite material by adopting liquid formation technology | |
| CN104589663A (en) | Forming method for latticed composite material bearing cylinder applicable to satellite | |
| CN105128358A (en) | Manufacturing method for wind power blade | |
| CN109562578A (en) | The manufacturing method of composite material structure and composite material structure | |
| CN106273547A (en) | One has cabin cover and Ω stringer deep camber unmanned plane wallboard manufacturing process | |
| CN110815854A (en) | Manufacturing method and application of flexible tool for molding longitudinal and transverse T-shaped reinforcing rib workpieces | |
| CN108943766A (en) | Co-bonding forming process for T-shaped reinforced wall plate made of composite material | |
| CN110356018A (en) | A kind of unmanned plane integrated machine head-shield co-curing manufacture mold and process | |
| CN105856585B (en) | A kind of rocket large scale lightweight protection cap integral forming method | |
| CN105150557A (en) | Method for manufacturing self-made auxiliary tooling for forming of large-curvature heteromorphic C-shaped frame type part | |
| CN101758923A (en) | Composite material box-shaped rib and manufacturing method thereof | |
| CN109838321A (en) | A kind of solid propellant rocket rear head insulating structure and forming method | |
| CN110281547A (en) | A method of realizing deep camber Ω type Material Stiffened Panel co-curing | |
| CN105479778A (en) | Flexible pressure pad for hot press molding of parts with complex profiles | |
| CN105082565A (en) | Automatic lay-up forming method of I-shaped beam made from composite materials |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |