CN102514708B - Integral central wing box made of composite materials - Google Patents
Integral central wing box made of composite materials Download PDFInfo
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- CN102514708B CN102514708B CN201110330249.5A CN201110330249A CN102514708B CN 102514708 B CN102514708 B CN 102514708B CN 201110330249 A CN201110330249 A CN 201110330249A CN 102514708 B CN102514708 B CN 102514708B
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- wing box
- central wing
- lower wall
- wainscot
- wall panels
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Abstract
The invention provides an integral central wing box made of composite materials, which comprises a front beam, an upper wall plate, a lower wall plate and a rear beam, wherein the upper wall plate is over against the lower wall plate; the front beam and the rear beam are arranged over against each other on both sides of the central wing box, and both ends of the front beam and the rear beam are respectively connected with the upper wall plate and the lower wall plate; and the central wing box is integrated from the upper wall plate, the lower wall plate, the front beam and the rear beam. According to the integral central wing box, the advanced performance of the structure is improved and the sealing safety of an oil tank is improved, and the process manufacturing and assembly difficulty is reduced, so that the cost is reduced.
Description
Technical field
The present invention relates to Aviation Composite Structure design, especially a kind of Integral central wing box made of composite materials.
Background technology
The development of current civil aircraft composite structure design is maked rapid progress, and the percentage composition that composite structure weight accounts for full machine structural weight has become one of important symbol weighing aircraft advance.Civil aircraft central wing box divides metal central wing box structure and two kinds, central wing box made of composite materials structure: metallic central wing box is generally combined by mechanical connection by front-axle beam, wainscot, lower wall panels and the back rest.Its central sill is generally made up of upper edge strip, web and lower edge strip, and wall panel skin combines because the size-constraints of metallic material mostly is polylith.
Existing central wing box made of composite materials is generally combined by front-axle beam 21, wainscot 11, lower wall panels 31 and the back rest 41, wherein front-axle beam 21, the back rest 41 and wainscot 11, each integral structure naturally of lower wall panels 31 covering, then each several part is assembled into central wing box again, reinforcement 51 is around installed, thus obtain central wing box structure, as shown in Figure 2.
The central wing box made of composite materials of existing unitized construction has following shortcoming: because be unitized construction, hoop fiber has disconnected and has been delivered to lower wall panels at front-axle beam by the shearing mainly through fastener during the external load of face; Need to use assembly jig to ensure central wing be box-packed to join accurately; Fitting process can introduce connecting bore, and damage can be brought to composite structure in mechanical connection hole, reduces the load-carrying capacity of composite structure; Assembly connection place is needed to seal.Above shortcoming can increase central wing box total weight, can increase central wing box assembly cost, increases technology difficulty.
In addition, central wing box belongs to large-sized composite material component, the unrelieved stress produced in forming process, the moderate finite deformation of component after the uncontrollable demoulding when not having external constraint.Therefore, for this kind of large scale technique for aircraft composite of central wing box component, must corresponding measure be taked, control the distortion after the demoulding, otherwise cannot assembly and use requirements be met.
Summary of the invention
In order to avoid the generation of above shortcoming, the present invention adopts a kind of Integral central wing box made of composite materials and manufacture method thereof, solves the typical problem existing for existing type central wing box.Improve the advance of central wing box structure, fuel tank sealing safety, reduce manufacture technics and assembly difficulty, thus reduce cost.
According to an aspect of the present invention, provide a kind of Integral central wing box made of composite materials, comprise: front-axle beam, wainscot, lower wall panels and the back rest, wherein wainscot and lower wall panels are oppositely arranged, front-axle beam and the back rest are oppositely arranged in central wing box both sides and respective both sides connect with wainscot and lower wall panels respectively, form overall central wing box.
Advantageously, the wainscot of central wing box and the surrounding of lower wall panels, front-axle beam and the back rest are provided with reinforcement.Advantageously, the material that Integral central wing box made of composite materials adopts is carbon fiber prepreg, the such as carbon fiber prepreg of T800 level.Here prepreg (Prepreg) is the abbreviation of pre impregnated material Preimpregnated Materials, being that matrix (Matrix) is immersed in the preimpregnation material that fiber (ReinforcedFiber) is made, is the intermediate materials of composite material structural member.
Manufacture shaping integral central wing box structural integrity dimensional accuracy through method of the present invention high, there is following advantage:
(1) hoop is that continuous fiber transmission ring is direct to load, improves central wing box course load-carrying capacity;
(2) because front-axle beam, the back rest, wainscot and the lower wall panels of not separating separately, mechanical connection is not needed to form central wing box, alleviate weight and the cost of mechanical connection fastener, avoid because the damage of mechanical connection pore area, improve the load-carrying capacity of central wing box self.
(3), in unnecessary face of carrying out bonding pad and the outer gland sealing of face, decrease the work capacity of sealing, alleviate weight and the cost of aquaseal.
(4) global formation ensure that dimensional accuracy when being connected with peripheral structure, assembly precision when not needing assembly jig to ensure that central wing box is connected with peripheral structure, reduces the dimensional accuracy that assembly cost improves central wing.
Accompanying drawing explanation
Fig. 1 is the Integral central wing box made of composite materials structural representation of one embodiment of the present invention;
Fig. 2 is existing central wing box made of composite materials structural representation.
Detailed description of the invention
The description of the preferred embodiments of the invention is provided below herein with reference to the accompanying drawings in detail.
Fig. 1 is the Integral central wing box made of composite materials structural representation of one embodiment of the present invention.According to Integral central wing box made of composite materials of the present invention, comprise: front-axle beam 2, wainscot 1, lower wall panels 3 and the back rest 4, wherein wainscot 1 and lower wall panels 3 are oppositely arranged, front-axle beam 2 and the back rest 4 are oppositely arranged in central wing box both sides and respective both ends connect with wainscot 1 and lower wall panels 3 respectively, wherein, central wing box by wainscot 1 and lower wall panels 3, front-axle beam 2 and the back rest 4 integrally formed.
Further, overall central wing box framing member also glueds joint and is connected with multiple reinforcement 5, and reinforcement 5 is arranged on the surrounding of wainscot 1 and lower wall panels 3, front-axle beam 2 and the back rest 4 and is gluedd joint with them by glued membrane or be mechanically connected and be fixed together.Reinforcement 5 can improve the rigidity of overall central wing box, and the stability after making overall central wing box shaping is better, improves the ability of resistance to deformation, prevent central wing box in forming process and shaping after distortion.Central wing box various piece (front-axle beam 2, wainscot 1, lower wall panels 3 and the back rest 4) all adopts carbon fiber prepreg, is the carbon fiber prepreg of T800 level in the present embodiment.The material of reinforcement 5 can be composite material, also can be metal.
Composite material (carbon fiber prepreg of T800 level) is laid in composite die, then by the central wing box laying of having laid together with composite die, enter curing oven under vacuum and carry out compacting (compacting can be carried out under normal temperature or heating), thus form the central wing box framing member of integration.After central wing box framing member is shaped, the auxiliary member of central wing box bottom (shaping longitudinal floor beam and front and rear beam reinforcement) is connected by glued membrane and navigates to through overcompaction but on the central wing box of no solidification, enter curing oven curing molding under vacuum.
Glued membrane is the adhesive of the epoxy systems that a kind of composite structure is commonly used, such as glued membrane FM300K, or PL7000, normal temperature glue EA9394.
Central wing box global formation scheme comparison conventional center wing box organization plan of the present invention has following advantage:
1, structure is simple, designability is strong
Global formation avoids combination and installs.Decrease the coordination problem of part design state, decrease the appearance of the coordination change problem in design afterwards.In full three dimensional design process, decrease the quantity of module, greatly reducing the work capacity of modeling.Because decrease number of parts, simplify the design of laying, make the design of laying more reasonable, overall laying is coordinated more, the unmatched problem of the Poisson's ratio that there will not be beam to be connected with covering.When adopting FiberSIM laying modeling, because be single piece, decrease the work capacity of laying modeling.
2, intensity is high
Global formation achieves the serialization of fiber, and entirety improves mechanical property and the functional requirement of parts.Reduce the fracture of hoop fiber, strengthen course load-carrying capacity; Reduce the mechanical connection of beam edge strip and wallboard, decrease fastener quantity, thus avoid and connect fastener openings in a large number, strengthen exhibition to load-carrying capacity; Employing integration is shaping, can improve 0 degree of laying percentum of beam edge strip, can avoid the weak link mechanical connection of composite material application like this, strengthen exhibition to load-carrying capacity.
3, good manufacturability
Only need after forming parts to carry out certain adding work to end portion, the machine after part forming that decreases adds repaiies type work capacity, decreases the layering in part edge district and the generation of damage; Decrease design and the assembly coordination of the assembly tooling of beam and wallboard; Global formation ensure that the conformability of central wing base portion scantling of structure.
4, to be functionally improved.
Central wing box is as the fuel tank of airliner, and seal request is very high, adopts global formation just to greatly reduce the work capacity of sealing.If central wing box main body structure have employed unit design, the shaping feature of comprehensive integral can make the more reasonable of central wing box structure design.
5, have a extensive future
Integral central wing box scheme of the present invention has numerous advantages, and loss of weight can reach about 10% compared with conventional scheme, successful, to guaranteeing that the safety of aircraft, traveling comfort, economy and reliability have extremely strong realistic meaning.
The invention is not restricted to above-mentioned embodiment, and can carry out in every way changing or improving based on purport of the present invention, and these changes and improvements do not depart from the scope of the present invention as required in claims.
Claims (2)
1. an Integral central wing box made of composite materials, comprise: front-axle beam (2), wainscot (1), lower wall panels (3) and the back rest (4), wherein said wainscot (1) and described lower wall panels (3) are oppositely arranged, described front-axle beam (2) and the described back rest (4) are oppositely arranged in described central wing box both sides and respective both sides connect with described wainscot (1) and described lower wall panels (3) respectively, it is characterized in that, described central wing box is by described front-axle beam (2), described wainscot (1), described lower wall panels (3) and the described back rest (4) integrally formed, the described wainscot (1) of described central wing box, described lower wall panels (3), the surrounding of described front-axle beam (2) and the described back rest (4) is provided with reinforcement (5), the described wainscot (1) of described central wing box, described lower wall panels (3), described front-axle beam (2) and the described back rest (4) and described reinforcement (5) glued joint and are connected.
2. Integral central wing box made of composite materials according to claim 1, is characterized in that, described central wing box is made up of carbon fiber prepreg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110330249.5A CN102514708B (en) | 2011-10-26 | 2011-10-26 | Integral central wing box made of composite materials |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110330249.5A CN102514708B (en) | 2011-10-26 | 2011-10-26 | Integral central wing box made of composite materials |
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| Publication Number | Publication Date |
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| CN102514708A CN102514708A (en) | 2012-06-27 |
| CN102514708B true CN102514708B (en) | 2015-03-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110330249.5A Active CN102514708B (en) | 2011-10-26 | 2011-10-26 | Integral central wing box made of composite materials |
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Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2993857B1 (en) * | 2012-07-26 | 2015-03-27 | Airbus Operations Sas | DEVICE FOR PROTECTING A LONGERON STRUCTURE BEFORE A CENTRAL AIRCRAFT WING BOX AND AT LEAST ONE EQUIPMENT LOCATED IN THE SAME |
| RU2532255C1 (en) * | 2013-06-05 | 2014-11-10 | Общество с ограниченной ответственностью "Научно-технологический испытательный центр АпАТэК-Дубна" | Torsion box of wing from composite |
| CN103625633A (en) * | 2013-08-23 | 2014-03-12 | 中国航空工业集团公司西安飞机设计研究所 | Main bearing pillar for composite aerofoil wing box |
| FR3015426B1 (en) * | 2013-12-20 | 2017-10-27 | Airbus Operations Sas | METHOD FOR PRODUCING A CENTRAL BOAT CASING |
| CN105627836B (en) * | 2016-02-18 | 2018-08-24 | 江西洪都航空工业集团有限责任公司 | A kind of combination beam type airfoil structure |
| CN106096090A (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Airfoil Testing fuel tank Optimization Design |
| CN106218861B (en) * | 2016-09-06 | 2018-10-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of aircraft wing |
| CN107571985B (en) * | 2017-08-25 | 2021-05-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Truss type ultra-light integral wing structure |
| CN108061637A (en) * | 2017-11-30 | 2018-05-22 | 中国商用飞机有限责任公司 | Wind tunnel test rectification part, pant device and its shaping and assembly method |
| CN111392028A (en) * | 2020-04-13 | 2020-07-10 | 中国商用飞机有限责任公司 | Stringer repair for wing stringers and method of repairing wing stringers |
| CN111731493B (en) * | 2020-06-18 | 2022-04-22 | 天津爱思达新材料科技有限公司 | Light diffusion structure of aircraft fuel tank hoisting position |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2526258Y (en) * | 2001-10-24 | 2002-12-18 | 于耀庆 | Structure of aircraft wing of composite material |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2936489B1 (en) * | 2008-09-30 | 2012-07-20 | Airbus France | AIRCRAFT CENTRAL TRONCON WITH WORKING VENTRAL CARENAGE |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2526258Y (en) * | 2001-10-24 | 2002-12-18 | 于耀庆 | Structure of aircraft wing of composite material |
Non-Patent Citations (3)
| Title |
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| CJ818中央翼盒复合材料结构设计及分析;马健等;《民用飞机设计与研究》;20090730;第77-80页 * |
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| CN102514708A (en) | 2012-06-27 |
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