CN216003092U - Thermoplastic composite material wing oil tank box section and wing - Google Patents
Thermoplastic composite material wing oil tank box section and wing Download PDFInfo
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- CN216003092U CN216003092U CN202121914607.2U CN202121914607U CN216003092U CN 216003092 U CN216003092 U CN 216003092U CN 202121914607 U CN202121914607 U CN 202121914607U CN 216003092 U CN216003092 U CN 216003092U
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Abstract
The utility model provides a thermoplasticity combined material wing tank box section and wing, relates to aircraft tank box section design technical field, includes: the wallboard units are oppositely arranged and comprise skins and stringers, and the stringers are arranged on the inner sides of the skins; a copper net is further arranged on the outer side of the wall plate unit; the beam units are arranged between the wall plate units and comprise beam edge strips and beam web plates, and the beam edge strips are respectively and vertically arranged at the upper ends and the lower ends of the beam web plates; a rib unit comprising a rib web and a rib cap, the rib web being disposed along the inside profile of the stringer and the web; the rib edge strip is disposed perpendicularly at the rib web edge. The utility model has simple structure, does not use a fastener to connect parts, does not need to drill holes, improves the assembly efficiency and reduces the risk of part defects; and a reinforced copper net is not used, so that the structural weight is reduced, and the lightning protection requirement is met.
Description
Technical Field
The utility model relates to the technical field of design of aircraft oil tank sections, in particular to a thermoplastic composite material wing oil tank section and a wing.
Background
The main box section of the large civil aircraft wing mainly acts to bear and transfer wing bending moment and shearing force caused by aerodynamic load. The main composition structure comprises an upper reinforced wall plate, a lower reinforced wall plate, a front beam, a rear beam and ribs arranged along the spanwise direction. The carbon fiber reinforced composite material has the properties of high specific strength, high specific stiffness, designability, fatigue resistance, corrosion resistance, less maintenance and the like, and is widely applied to the most advanced international large civil aircraft. At present, carbon fiber reinforced thermosetting resin matrix composite materials (hereinafter referred to as thermosetting composite materials) are widely adopted in the main structure of the wing box of the advanced large civil aircraft. In the main box section structure of a B787 airplane and an airbus A350xwb wing, the upper and lower wall plates, the front and rear beam structures are made of thermosetting composite materials, and the wing ribs are made of metal structures; in the tail box section, the wall plate, the beam and the rib structure are all made of thermosetting composite materials.
The existing thermosetting composite material wing box section has the following defects:
1. the wall plates are connected with the beams, the wall plates are connected with the ribs, the beams and the ribs and the like, and the wall plates are still connected by fasteners, so that the accessory procedures such as drilling, packaging and the like are brought, the assembly procedures are increased, the risk of introducing part defects is increased, and the assembly efficiency is reduced;
2. in the oil tank area of the main box section of the wing, all fasteners connected with the outside of the box section need to use a special bushing fastener, the fastener is expensive in manufacturing cost and is tens of times of common high-locking fasteners, and the assembly cost is greatly improved;
3. in order to keep the oil tank area in a sealed state, all possible passages between the oil tank and the outside need to be sealed, common sealing operations comprise joint face sealing, fillet sealing and the like, the assembly procedures are increased, and the assembly efficiency is reduced;
4. in order to meet the lightning protection requirement, the reinforcing copper mesh is laid on the wall plate in the fastener area, so that the structural weight is increased, and the deformation state of the wall plate after solidification is greatly influenced;
5. the thermosetting composite material has poor toughness and poor impact resistance.
SUMMERY OF THE UTILITY MODEL
In view of the above, the utility model provides a thermoplastic composite material wing oil tank box section and a wing, which have simple structures, do not use fasteners to connect parts, do not need drilling, improve the assembly efficiency and reduce the risk of part defects; a lining bolt is not used, so that the manufacturing cost is reduced, and the lightning protection requirement is met; a reinforced copper mesh is not used, so that the structural weight is reduced, and the lightning protection requirement is met; and no sealant is used, so that the sealing requirement is met, and the assembly procedures are reduced.
In order to achieve the purpose, the utility model adopts the technical scheme that:
according to a first aspect of the present invention there is provided a thermoplastic composite wing tank box section comprising:
the wallboard units are oppositely arranged and comprise skins and stringers, and the stringers are arranged on the inner sides of the skins; a copper net is further arranged on the outer side of the wall plate unit;
the beam units are arranged between the wall plate units and comprise beam edge strips and beam web plates, and the beam edge strips are respectively and vertically arranged at the upper ends and the lower ends of the beam web plates;
a rib unit comprising a rib web and a rib cap, the rib web being disposed along the inside profile of the stringer and the web; the rib edge strip is disposed perpendicularly at the rib web edge.
Furthermore, the beam unit is arranged on two sides of the wallboard unit, and the beam web plate is perpendicular to the skin.
Further, the stringer is Z-shaped in cross section and comprises a stringer web and a stringer tape;
the stringer webs are arranged perpendicular to the skin;
the stringer flanges are respectively and vertically arranged at two ends of the stringer web;
a plurality of stringers are co-directionally aligned along the interior side of the skin.
Further, the rib strips comprise transverse rib strips and longitudinal rib strips;
the transverse rib strip is arranged in parallel with the skin;
the longitudinal rib strips are arranged in parallel with the web.
Further, the inner side of the skin and the outer side of the bottom surface of the stringer, the inner side of the skin and the outer side of the girder edge strip, the inner side of the bottom surface of the stringer and the outer side of the transverse rib strip, and the inner side of the web plate and the outer side of the longitudinal rib strip are fixedly connected with each other.
Further, the ends of the beam flange strips, the rib flange strips and the stringer flange strips are all provided with oblique angles, and the oblique angles are 30-35 degrees.
Further, the density of the copper mesh is 60-70 g/m2。
According to a second aspect of the utility model, there is provided a thermoplastic composite wing applying the aforementioned thermoplastic composite wing tank box.
Compared with the prior art, the thermoplastic composite material wing oil tank box section and the wing have the following advantages:
1. the wall plate and the beam edge strip, the wall plate and the rib edge strip and the rib and the beam are welded in a seamless mode;
2. the spar cap is not mechanically connected with the wall plate, so that drilling and bushing bolts are not needed, the assembly cost is improved, and the manufacturing cost is reduced;
3. because the wing oil tank is not penetrated through by a fastener at the position, a reinforced copper mesh is not required to be laid on the outer side of the wall plate at the position, the structural weight can be saved, and the lightning protection requirement can be met;
4. the edge of the beam edge strip and the edge of the rib edge strip are designed by adopting an oblique angle with extremely slow gradient, so that the local rigidity is slowly changed, and the debonding risk is reduced.
Drawings
The accompanying drawings are included to provide a further understanding of the utility model, and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model and not to limit the utility model.
In the drawings:
FIG. 1 is a schematic overall view of a thermoplastic composite wing tank box in an embodiment of the utility model.
Wherein, 1-skin; 2-a web; 3-a beam edge strip; 4-rib webs; 5-a rib strip; 6-stringer; 7-skin and stringer weld interface; 8-stringer to rib fillet weld interface; 9-the beam flange strip and skin weld interface; 10-web and rib welding interface; 11-copper mesh; 12-chamfering the beam edge strip; 13-chamfering the stringer tape; and 14-chamfering rib edge strips.
Detailed Description
Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the utility model, as detailed in the appended claims.
The terms first, second and the like in the description and in the claims of the present invention are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the utility model described herein are, for example, capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
A plurality, including two or more.
And/or, it should be understood that, as used herein, the term "and/or" is merely one type of association that describes an associated object, meaning that three types of relationships may exist. For example, a and/or B, may represent: a exists alone, A and B exist simultaneously, and B exists alone.
A thermoplastic composite wing tank box section comprising:
the wall plate units are oppositely arranged and used for bearing and transmitting pneumatic load;
the beam units are arranged between the wall plate units and used for supporting the wall plate units;
and the rib units are arranged along the inner profiles of the wall plate units and the beam units and are used for supporting the wall plate units and forming a space box type structure with the beam units.
Preferably, the panel unit comprises a skin and stringers, the stringers being located inboard of the skin;
the beam units are respectively arranged at the left side and the right side of the wallboard unit and comprise beam edge strips and a beam web plate, and the beam edge strips are respectively and vertically arranged at the upper end and the lower end of the beam web plate;
the rib elements include a rib web disposed along the inside profile of the stringers and web and a rib flange disposed perpendicularly at the rib web edge.
Preferably, the stringer is Z-shaped in cross-section and includes a stringer web and a stringer tape;
the stringer web is perpendicular to the skin;
the stringer flanges are respectively vertically arranged at two ends of the stringer web;
a plurality of stringers are co-directionally aligned along the interior side of the skin.
Preferably, the rib strips comprise transverse rib strips and longitudinal rib strips;
the transverse rib strip is arranged in parallel with the skin;
the longitudinal ribs are arranged parallel to the web.
Preferably, the inner side of the skin is fixedly connected with the outer side of the bottom surface of the stringer, the inner side of the skin is fixedly connected with the outer side of the girder edge strip, the inner side of the bottom surface of the stringer is fixedly connected with the outer side of the transverse rib edge strip, and the inner side of the web plate is fixedly connected with the outer side of the longitudinal rib edge strip in a thermoplastic welding mode.
Preferably, the ends of the beam flanges, the rib flanges and the stringer flanges are provided with bevels, the bevels being from 30 to 35 °.
Preferably, the outer side of the wallboard unit is also provided with a copper net for protecting against lightning stroke, and the density of the copper net is 60-70 g/m2。
Example (b):
the specific scheme of the utility model is shown in figure 1, the composite material wing box section adopts a double-beam multi-rib structure, and parts of each component are made of thermoplastic composite materials. The skin 1 adopts an automatic fiber-laying in-situ forming process, the stringers 6 adopt a Z-shaped structure and are suitable for a continuous compression molding process, the web plates 2 and the edge strips 3 adopt an automatic fiber-laying in-situ forming process, and the rib web plates 4 and the rib edge strips 5 adopt a compression molding process.
Wherein two skins 1 are oppositely arranged, stringers 6 are arranged on the inner sides of the skins 1 and are used for transmitting the pneumatic load transmitted by the skins 1 to the wing ribs in the form of the load of a multi-fulcrum beam, and the Z-shaped structure isThe stringer 6 has higher bending rigidity and high structural efficiency, and is simple to manufacture compared with an I-shaped stringer with the same higher bending rigidity; the two beam webs 2 are respectively fixed on two sides in the skin 1 through beam edge strips 3 to play a supporting role; the rib web 4 is arranged along the inner profiles of the stringers 6 and the web 2 and is fixed thereto by the rib flanges 5; meanwhile, the outer side of the skin 1 is also provided with a density of 60g/m2And the copper mesh 11 is used for protecting against lightning stroke.
Compared with the traditional main box section of the wing made of the thermosetting composite material, the parts involved in the utility model are made of the thermoplastic composite material, so that the parts can be repeatedly melted and solidified, and the interface between the parts can be self-bonded under the action of local heating and pressure. There are many processes for achieving heating and pressurizing of the interface between parts, which are collectively referred to as thermoplastic composite welding processes.
The utility model adopts a thermoplastic welding process to connect a skin and stringer welding interface 7, a stringer and rib strip welding interface 8, a beam flange strip and skin welding interface 9 and a beam web and rib strip welding interface 10. By adopting thermoplastic welding connection, under the condition of meeting the strength requirement, the application of fasteners can be reduced or avoided on a large scale at the connection interface of each part, the drilling of composite materials is reduced, and the assembly process is simplified; after the fasteners are reduced to be connected, the use amount of the bolts along with the bushings is greatly reduced, the component cost can be greatly reduced, and meanwhile, the lightning protection risk is also greatly reduced. Meanwhile, the welding process greatly reduces the interfaces between the parts, only a few positions in the box section need to be sealed, the use of the sealant is greatly reduced, the assembly process is simplified, and the structural weight is reduced. Due to the large-scale reduction of the fasteners, the use of the reinforced copper mesh is greatly reduced, and the weight of the structure can be reduced; meanwhile, the thermoplastic composite material improves the shock resistance of the main box section of the wing and reduces the structural weight.
In addition, in order to increase the welding area, improve the bearing level of the connection area between parts and reduce stress concentration, the edge of the edge strip is designed to be inclined angle with extremely slow gradient so as to slowly change the local rigidity and reduce the debonding risk, wherein the beam edge strip inclined chamfer angle 12, the stringer edge strip inclined chamfer angle 13 and the rib edge strip inclined chamfer angle 14 are preferably 32.5 degrees.
While the present invention has been described with reference to the embodiments shown in the drawings, the present invention is not limited to the embodiments, which are illustrative rather than restrictive, and it will be apparent to those skilled in the art that many more modifications and variations can be made without departing from the spirit of the utility model and the scope of the appended claims.
Claims (8)
1. A thermoplastic composite wing tank box section comprising:
the wallboard units are oppositely arranged and comprise skins and stringers, and the stringers are arranged on the inner sides of the skins; a copper net is further arranged on the outer side of the wall plate unit;
the beam units are arranged between the wall plate units and comprise beam edge strips and beam web plates, and the beam edge strips are respectively and vertically arranged at the upper ends and the lower ends of the beam web plates;
a rib unit comprising a rib web and a rib cap, the rib web being disposed along the inside profile of the stringer and the web; the rib edge strip is disposed perpendicularly at the rib web edge.
2. A thermoplastic composite wing tank box section according to claim 1, wherein the spar elements are disposed on either side of the wall panel elements and the spar webs are perpendicular to the skin.
3. The thermoplastic composite wing tank box of claim 1, wherein the stringer is Z-shaped in cross-section and includes a stringer web and a stringer tape;
the stringer webs are arranged perpendicular to the skin;
the stringer flanges are respectively and vertically arranged at two ends of the stringer web;
a plurality of stringers are co-directionally aligned along the interior side of the skin.
4. A thermoplastic composite wing tank box section according to claim 1, wherein the ribbing comprises a transverse ribbing and a longitudinal ribbing;
the transverse rib strip is arranged in parallel with the skin;
the longitudinal rib strips are arranged in parallel with the web.
5. A thermoplastic composite wing tank box section according to claim 4, wherein the inner skin side and the outer stringer base side, the inner stringer base side and the outer transverse rib side, and the inner spar web side and the outer longitudinal rib side are all fixedly connected to each other.
6. A thermoplastic composite wing tank box section according to claim 3, wherein the ends of the spar cap, the rib cap and the stringer cap are each provided with a bevel angle of 30 ° to 35 °.
7. The thermoplastic composite wing tank box section of claim 1, wherein the copper mesh has a density of 60-70 g/m2。
8. A thermoplastic composite airfoil characterized in that it employs a thermoplastic composite airfoil fuel tank box section as claimed in any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121914607.2U CN216003092U (en) | 2021-08-16 | 2021-08-16 | Thermoplastic composite material wing oil tank box section and wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121914607.2U CN216003092U (en) | 2021-08-16 | 2021-08-16 | Thermoplastic composite material wing oil tank box section and wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216003092U true CN216003092U (en) | 2022-03-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121914607.2U Active CN216003092U (en) | 2021-08-16 | 2021-08-16 | Thermoplastic composite material wing oil tank box section and wing |
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| Country | Link |
|---|---|
| CN (1) | CN216003092U (en) |
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- 2021-08-16 CN CN202121914607.2U patent/CN216003092U/en active Active
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