CN101758923A - Composite material box-shaped rib and manufacturing method thereof - Google Patents
Composite material box-shaped rib and manufacturing method thereof Download PDFInfo
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- CN101758923A CN101758923A CN200810236474A CN200810236474A CN101758923A CN 101758923 A CN101758923 A CN 101758923A CN 200810236474 A CN200810236474 A CN 200810236474A CN 200810236474 A CN200810236474 A CN 200810236474A CN 101758923 A CN101758923 A CN 101758923A
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- box
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- paving
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a composite material box-shaped rib and a manufacturing method thereof. The composite material box-shaped rib comprises two sandwich layers (2) and covering skin (1) and is in a shape of closed box; a supporting rib of a box is formed between the two sandwich layers through a paving layer (3); and the covering skin (1) is in a paving layer structure made of carbon fiber material. The shape of the sandwich layers (2) of the box-shaped rib is determined according to the requirement of the structural configuration. In the invention, the annually coating, paving and attaching, combination and compaction of pre-impregnated material and the curing and forming through an autoclave are used; a conventional autoclave curing and shaping method is adopted without manufacturing a large amount of combined forming core die; and by a process method of non-allowance processing and annual coating and attaching, the production flow of parts are reduced and multi-step curing is changed into one-step curing forming. The formed box-shaped rib structure has higher tensile, bending, shearing and torsion resisting performances and can meet the bearing requirement of an operating joint and a connecting joint as well as meet the requirement of stronger mechanical loading performance.
Description
One, technical field:
The present invention relates to the design and the manufacturing technology field of non-metallic material, specifically is a kind of composite material box-shaped rib and preparation method thereof.
Two, background technology:
The sub-wing of new jetliner adopts the foam layer composite structure, and a plurality of ribs raising structural strengths are set.Generally speaking, " [" shape or " I " shape version are adopted in the cross section of airplane parts rib, but the internal-rib of this loom wing uses as point of connection when design, on this rib, require carrying bigger bend, cut, torsion, it is general that " rib rigidity, the intensity of [" shape or " I " shape version do not satisfy load bearing requirements.Designed the cross section is for this reason
The box rib of shape.Simultaneously because aircraft adopts overcritical wing, son cautiously face is the double curved surface structure, the costal margin up and down of box rib and middle pectoral plate angle part are less than 90 °, the mould molding difficulty is big, part is closed the position, angle and can't be realized the part demoulding, mould need be designed to array configuration, but it is little to be limited to accessory size, and composite die has difficulties equally.
Three, summary of the invention
Do not satisfy load bearing requirements for overcoming rigidity that exist in the prior art or structure and intensity, perhaps the mould molding difficulty is big, and part is closed the deficiency that the part demoulding can't be realized in the position, angle, the present invention proposes a kind of composite material box-shaped rib and preparation method thereof.
The present invention includes two laminboard layers and covering, be shaped as the osed top box-like, and forming useful shop, the box middle part layer brace rod that forms of box rib.Laminboard layer of the present invention adopts foamed materials to make, and covering is the shop layer structure that adopts carbon fiber to make.The shape of box rib laminboard layer is determined according to the requirement of construction profile.
Concrete manufacturing process of the present invention is:
The first step, the laminboard layer of making box rib.Laminboard layer is two, selects for use light material to make, its outer profile just as part.
Second step, the blanking of box rib covering.According to design size,, and carry out every layer mark to each layer of box rib covering prepreg cutting blanking.
In the 3rd step, on two foam sandwich laminates of box rib, finish the paving of ring bag and the compacting of prepreg separately respectively.In the paving, the compacting of per 1～3 layer of soft sack cold-draw of system; The angle of shop layer be 0 ° or ± 45 ° or 90 °, and staggered the laying.
In the 4th step, the both sides laminboard layer that paving is good is combined and is adopted conventional approach to vacuumize compacting and fixes; Finish the bag paving of prepreg ring and the compacting of three layers of outermosts.
In the 5th step, the box rib that paving is intact moves into and carries out pre-compacted and fixing in the closed type split die, sends into the solidification of hot-press tank moulding then.
The present invention adopts conventional solidification of hot-press tank forming method, need not to make the moulding core of a large amount of array configurations, the process of pasting by no surplus processing and ring covering reduces the component production flow process, the change hardens in several stages is one-step solidification moulding, the box rib structure of institute's moulding has higher tension, bending resistance, shearing resistance and antitorque mechanical property, can satisfy the load bearing requirements of handling joint and jointing place, also can satisfy the powerful requirement of learning load performance.
Four, description of drawings is spread layer
Accompanying drawing 1 is the 3D sterogram of box rib;
Accompanying drawing 2 is structural representations of box rib;
Accompanying drawing 3 is section-drawings of box rib;
Accompanying drawing 4 is box rib laminboard layer scheme drawings;
Accompanying drawing 5 is structural representations of box rib covering;
Accompanying drawing 6 is composite material box-shaped rib shop layer scheme drawing;
Accompanying drawing 7 is paving scheme drawings of a side box;
Accompanying drawing 8 is paving scheme drawings of opposite side box;
Accompanying drawing 9 is box combination back, both sides and three layers of prepreg ring of outermost layer bag paving scheme drawing;
Accompanying drawing 10 is manufacture craft diagram of circuits.
Wherein:
1. covering 2. laminboard layers 3. are spread layer
Five, the specific embodiment
Embodiment one
Present embodiment is the box rib of the sub-wing of wing flap of certain type machine.
Present embodiment comprises the covering 1 that two laminboard layers 2 and the paving of ring bag form, and is shaped as the osed top box-like, and the brace rod that useful shop layer 3 forms at the middle part of the box that forms box rib.The laminboard layer of present embodiment adopts foamed plastic to make, and covering is the shop layer structure made from carbon fibre initial rinse fabric.The shape of box rib laminboard layer is with the profile of the box rib of the sub-wing of wing flap.
The manufacturing process of present embodiment is:
The first step, the laminboard layer 2 of making box rib.Laminboard layer 2 is two, selects for use foamed plastic to make, its outer profile just as part.
Second step, 1 blanking of box rib covering.According to design size,, and carry out every layer mark to 1 each layer prepreg cutting blanking of box rib covering.
The 3rd step, the paving of laminboard layer 2, pellet combination and compacting.On two foam sandwich laminates 2 of box rib, finish prepreg paving separately respectively and formed shop layer 3, and compacting.In the paving of prepreg, implement paving earlier to laminboard layer 2 lateral surfaces, its paving number of plies is 15 layers; During paving,, to the lateral surface ring bag paving of two laminboard layers 2, finish the design number of plies at this position until paving respectively since two surfaces that laminboard layer is adjacent.Implement the paving to laminboard layer 2 medial surfaces again, its paving number of plies is 15 layers; During paving, since the upper surface of two laminboard layer 2 lateral surfaces, to the medial surface of two laminboard layers 2, promptly the design number of plies at this position is finished in two surface ring bag pavings that laminboard layer is adjacent until paving respectively.In the paving, the compacting of per 1～3 layer of soft sack cold-draw of system; The angle of shop layer 3 be 0 ° or ± 45 ° or 90 °, and staggered the laying.
In the 4th step, after finishing the shop layer of designing requirement respectively, the both sides laminboard layer 2 that paving is good is combined and is adopted conventional approach to vacuumize compacting and fixes; Finish the bag paving of prepreg ring and the compacting of three layers of outermosts.
In the 5th step, the box rib that paving is intact moves into and carries out pre-compacted and fixing in the closed type split die, sends into the solidification of hot-press tank moulding then.
Embodiment two
Present embodiment is the box rib of the sub-wing of wing flap of certain type machine.
Present embodiment comprises the covering 1 that two laminboard layers 2 and the paving of ring bag form, and is shaped as the osed top box-like, and the brace rod that useful shop layer 3 forms at the middle part of the box that forms box rib.The laminboard layer 2 of present embodiment adopts foamed plastic to make, and covering 1 is the shop layer structure made from the carbon fiber one-way band.The shape of box rib laminboard layer 2 is with the profile of the box rib of the sub-wing of wing flap.
The manufacturing process of present embodiment is:
The first step, the laminboard layer 2 of making box rib.Laminboard layer 2 is two, selects for use foamed materials to make, its outer profile just as part.
Second step, 1 blanking of box rib covering.According to design size,, and carry out every layer mark to 1 each layer prepreg cutting blanking of box rib covering.
The 3rd step, the paving of laminboard layer 2, pellet combination and compacting.On two foam sandwich laminates of box rib, finish prepreg paving separately respectively and formed shop layer 3, and compacting.In the paving of prepreg, implement paving earlier to laminboard layer 2 lateral surfaces, its paving number of plies is 10 layers; During paving,, to the lateral surface ring bag paving of two laminboard layers 2, finish the design number of plies at this position until paving respectively since two surfaces that laminboard layer is adjacent.Implement the paving to laminboard layer 2 medial surfaces again, its paving number of plies is 10 layers; During paving, since the upper surface of two laminboard layer 2 lateral surfaces, to the medial surface of two laminboard layers 2, promptly the design number of plies at this position is finished in two surface ring bag pavings that laminboard layer is adjacent until paving respectively.In the paving, the compacting of per 1～3 layer of soft sack cold-draw of system; The angle of shop layer 3 be 0 ° or ± 45 ° or 90 °, and staggered the laying.
In the 4th step, after finishing the shop layer of designing requirement respectively, the both sides laminboard layer 2 that paving is good is combined and is adopted conventional approach to vacuumize compacting and fixes; Finish the bag paving of prepreg ring and the compacting of three layers of outermosts.
In the 5th step, the box rib that paving is intact moves into and carries out pre-compacted and fixing in the closed type split die, sends into the solidification of hot-press tank moulding then.
Claims (2)
1. a composite material box-shaped rib comprises laminboard layer (2) and covering (1), and what it is characterized in that composite material box-shaped rib is shaped as the osed top box-like; Laminboard layer in the box rib (2) is two, and forms the brace rod of box between two laminboard layers by the shop layer; The covering of composite material box-shaped rib (1) is a carbon fiber prepreg shop layer structure.
2. method of making the described composite material box-shaped rib of claim 1 is characterized in that the concrete manufacturing process of this composite material box-shaped rib is:
The first step, the laminboard layer (2) of making box rib; Laminboard layer (2) is two, its outer profile just as part;
Second step, box rib covering (1) blanking, and carry out every layer mark;
The 3rd step, on two foam sandwich laminates of box rib, finish the ring bag paving of prepreg separately respectively, form shop layer (3), and compacting; In the paving, the compacting of per 1～3 layer of soft sack cold-draw of system; The angle of shop layer (3) be 0 ° or ± 45 ° or 90 °, and staggered the laying;
In the 4th step, the both sides laminboard layer that paving is good is combined and is vacuumized compacting and fixes; Finish the bag paving of prepreg ring and the compacting of three layers of outermosts;
In the 5th step, the box rib that paving is intact moves into and carries out pre-compacted and fixing in the closed type split die; Send into the solidification of hot-press tank moulding.
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| CN2008102364740A CN101758923B (en) | 2008-12-25 | 2008-12-25 | Composite material box-shaped rib and manufacturing method thereof |
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| CN2008102364740A CN101758923B (en) | 2008-12-25 | 2008-12-25 | Composite material box-shaped rib and manufacturing method thereof |
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| CN101758923A true CN101758923A (en) | 2010-06-30 |
| CN101758923B CN101758923B (en) | 2012-05-09 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013078649A1 (en) * | 2011-11-30 | 2013-06-06 | Airbus S.A.S. | Component having a box structure for an airplane airfoil |
| WO2013078646A1 (en) * | 2011-11-30 | 2013-06-06 | Airbus S.A.S. | Airplane component having a box structure |
| CN103264513A (en) * | 2013-05-30 | 2013-08-28 | 中国商用飞机有限责任公司 | Integrated co-curing forming technology method for composite material multi-beam box section |
| CN105143040A (en) * | 2013-04-18 | 2015-12-09 | 空中客车营运有限公司 | Braided composite spar |
| CN105666893A (en) * | 2014-11-17 | 2016-06-15 | 昌河飞机工业（集团）有限责任公司 | Laying and positioning method for prepreg slices |
| CN107541832A (en) * | 2017-08-30 | 2018-01-05 | 杭州碳谱新材料科技有限公司 | Aluminum matrix composite materials heald frame |
| CN108032988A (en) * | 2017-10-25 | 2018-05-15 | 北京航空航天大学 | A kind of fibre reinforced composites aircraft bay section connection structure and preparation method thereof |
| CN110481059A (en) * | 2019-09-24 | 2019-11-22 | 航天特种材料及工艺技术研究所 | A kind of composite material foam sandwich construction and its forming method |
| CN111002762A (en) * | 2019-12-31 | 2020-04-14 | 东莞艾可迅复合材料有限公司 | Hub decoration and manufacturing method thereof |
| CN114434824A (en) * | 2021-12-24 | 2022-05-06 | 中航通用飞机有限责任公司珠海复合材料科技分公司 | Forming method of integral special-shaped composite rib |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4084029A (en) * | 1977-07-25 | 1978-04-11 | The Boeing Company | Sine wave beam web and method of manufacture |
| CN2526258Y (en) * | 2001-10-24 | 2002-12-18 | 于耀庆 | Structure of aircraft wing of composite material |
| US7721995B2 (en) * | 2006-12-13 | 2010-05-25 | The Boeing Company | Rib support for wing panels |
-
2008
- 2008-12-25 CN CN2008102364740A patent/CN101758923B/en active Active
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013078646A1 (en) * | 2011-11-30 | 2013-06-06 | Airbus S.A.S. | Airplane component having a box structure |
| WO2013078649A1 (en) * | 2011-11-30 | 2013-06-06 | Airbus S.A.S. | Component having a box structure for an airplane airfoil |
| US9434466B2 (en) | 2011-11-30 | 2016-09-06 | Airbus Sas | Component having a box structure for an airplane airfoil |
| US10011345B2 (en) | 2013-04-18 | 2018-07-03 | Airbus Operations Limited | Braided composite spar |
| CN105143040A (en) * | 2013-04-18 | 2015-12-09 | 空中客车营运有限公司 | Braided composite spar |
| US10029779B2 (en) | 2013-04-18 | 2018-07-24 | Airbus Operations Limited | Winglet |
| US9896186B2 (en) | 2013-04-18 | 2018-02-20 | Airbus Operations Limited | Braided composite spar |
| US10023292B2 (en) | 2013-04-18 | 2018-07-17 | Airbus Operations Limited | Braided composite spar |
| CN103264513A (en) * | 2013-05-30 | 2013-08-28 | 中国商用飞机有限责任公司 | Integrated co-curing forming technology method for composite material multi-beam box section |
| CN103264513B (en) * | 2013-05-30 | 2015-10-21 | 中国商用飞机有限责任公司 | The overall co-curing moulding technique of composite many beams box section |
| CN105666893A (en) * | 2014-11-17 | 2016-06-15 | 昌河飞机工业（集团）有限责任公司 | Laying and positioning method for prepreg slices |
| CN107541832A (en) * | 2017-08-30 | 2018-01-05 | 杭州碳谱新材料科技有限公司 | Aluminum matrix composite materials heald frame |
| CN107541832B (en) * | 2017-08-30 | 2020-03-06 | 杭州碳谱新材料科技有限公司 | Carbon-aluminum composite material heald frame |
| CN108032988A (en) * | 2017-10-25 | 2018-05-15 | 北京航空航天大学 | A kind of fibre reinforced composites aircraft bay section connection structure and preparation method thereof |
| CN108032988B (en) * | 2017-10-25 | 2020-06-16 | 北京航空航天大学 | Fiber reinforced composite aircraft cabin connecting structure and preparation method thereof |
| CN110481059A (en) * | 2019-09-24 | 2019-11-22 | 航天特种材料及工艺技术研究所 | A kind of composite material foam sandwich construction and its forming method |
| CN110481059B (en) * | 2019-09-24 | 2021-06-18 | 航天特种材料及工艺技术研究所 | Composite material foam sandwich structure and forming method thereof |
| CN111002762A (en) * | 2019-12-31 | 2020-04-14 | 东莞艾可迅复合材料有限公司 | Hub decoration and manufacturing method thereof |
| CN111002762B (en) * | 2019-12-31 | 2024-02-06 | 东莞艾可迅复合材料有限公司 | Hub decoration and manufacturing method thereof |
| CN114434824A (en) * | 2021-12-24 | 2022-05-06 | 中航通用飞机有限责任公司珠海复合材料科技分公司 | Forming method of integral special-shaped composite rib |
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|---|---|
| CN101758923B (en) | 2012-05-09 |
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Owner name: FESHER AVIATION COMPONENTS (ZHENJIANG) CO., LTD. Free format text: FORMER OWNER: XI AN AIRCRAFT INDUSTRY GROUP CO., LTD. Effective date: 20150130 Owner name: XI AN AIRCRAFT INDUSTRY GROUP CO., LTD. Effective date: 20150130 |
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Free format text: CORRECT: ADDRESS; FROM: 710089 XI AN, SHAANXI PROVINCE TO: 212132 ZHENJIANG, JIANGSU PROVINCE |
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Effective date of registration: 20150130 Address after: Zhenjiang City, Jiangsu Province, Dagang District 212132 case of the main road No. 88 Patentee after: Fischer aviation components (Zhenjiang) Co., Ltd. Patentee after: Xi'an Aircraft Industry Group Co., Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: Xi'an Aircraft Industry Group Co., Ltd. |