CN211568287U - Aircraft and wing panel thereof - Google Patents
Aircraft and wing panel thereof Download PDFInfo
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- CN211568287U CN211568287U CN201922247047.9U CN201922247047U CN211568287U CN 211568287 U CN211568287 U CN 211568287U CN 201922247047 U CN201922247047 U CN 201922247047U CN 211568287 U CN211568287 U CN 211568287U
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- airfoil
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- fin
- metal joint
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Abstract
An embodiment of the utility model provides an aircraft and fin thereof. The wing panel includes: a metal joint and a composite airfoil body; the metal joint is provided with a first connecting part and a second connecting part, and is connected with the fuselage of the aircraft through the first connecting part and fixedly connected with the composite material wing panel body through the second connecting part; the second connecting part is of a fork-shaped structure. The utility model discloses a fin light in weight, with low costs, intensity rigidity is high, and the reliability is high.
Description
Technical Field
The utility model relates to an aviation, space flight vehicle's fin technical field especially indicates an aircraft and fin thereof.
Background
The wing piece of aircraft guarantees that the aircraft can safe and reliable flight, and the wing piece of traditional aircraft has following problem: the metal fin and the solid composite material are heavy in weight and high in cost, the joint of the joint and the composite material fin is extremely easy to damage, and particularly, the joint and the composite material fin connecting nail is extremely easy to damage under the condition that the total thickness of the fin is only ten millimeters, so that the reliability is low.
SUMMERY OF THE UTILITY MODEL
The utility model provides an aircraft and fin thereof, light in weight, with low costs, intensity rigidity is high, and the reliability is high.
In order to solve the above technical problem, an embodiment of the present invention provides the following solutions:
an airfoil for an aircraft, comprising: a metal joint and a composite airfoil body;
the metal joint is provided with a first connecting part and a second connecting part, and is connected with the fuselage of the aircraft through the first connecting part and fixedly connected with the composite material wing panel body through the second connecting part; the second connecting part is of a fork-shaped structure.
Optionally, the fork structure is provided with a plurality of threaded connection holes, the composite material fin body is provided with a plurality of threaded connection holes at positions corresponding to the fork structure, bolts are inserted into the threaded connection holes on the composite material fin body and the threaded connection holes on the fork structure, and the metal joint is fixedly connected with the composite material fin body.
Optionally, the bolt is inserted into the threaded connection hole on the upper surface of the composite material wing body, and the threaded connection hole inserted into the lower surface of the composite material wing body is staggered with the bolt.
Optionally, the composite material airfoil body is a complex flat constant-section curved profile structure.
Optionally, the composite material vane body is a hollow structure.
Optionally, the hollow structure is a closed hollow structure.
Optionally, the hollow structure is provided with reinforcing ribs and/or foam material.
Optionally, the composite material vane body is a carbon fiber composite material vane body.
Optionally, the carbon fiber composite airfoil body includes: the carbon cloth comprises 0-degree fibers of a middle rib, a first layer of mixed woven carbon cloth outside the 0-degree fibers of the middle rib and a second layer of mixed woven carbon cloth outside the first layer of mixed woven carbon cloth.
An embodiment of the utility model provides an aircraft is still provided, include: fuselage and with fuselage fixed connection's fin, its characterized in that, the fin is as above the fin of aircraft, at least one connecting hole has on the first connecting portion of the metal joint of fin, the metal joint pass through on the first connecting portion at least one connecting hole with fuselage fixed connection.
The above technical scheme of the utility model at least include following beneficial effect:
the above technical scheme of the utility model, metal joint adopts metal material, fin body to adopt combined material's structure, has guaranteed integrality, the aerodynamic performance of airfoil, does benefit to again and improves holistic reliability. Meanwhile, the number of parts is reduced, the structure weight is reduced, the structure cost is reduced, the assembly process is improved, and the production period is shortened.
Drawings
FIG. 1 is an assembly view of a wing panel of the aircraft of the present invention;
figure 2 is a metal joint of a wing of the aircraft of the invention;
FIG. 3 is a composite airfoil body for an aircraft according to the present invention;
FIG. 4 is a composite airfoil body cross-section of the airfoil of the aircraft of the present invention;
figure 5 is a schematic view of the fiber orientation of the airfoil composite airfoil body of the aircraft of the present invention.
Description of reference numerals:
1-metal joint, 11-first connection; 12-a second connection;
2-a composite airfoil body; 21-middle rib 0 degree fiber; 22-a first layer of mixed woven carbon cloth; 23-second layer mixed weaving carbon cloth; 24-the outer side of the second layer of mixed woven carbon cloth is inwards 2 mm; a 25-N region.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1-5, an embodiment of the present invention provides a wing panel of an aircraft, comprising: a metal joint 1 and a composite material fin body 2;
the metal joint 1 is provided with a first connecting part 11 and a second connecting part 12, the metal joint 1 is connected with the fuselage of an aircraft through the first connecting part 11, and is fixedly connected with the composite material fin body 2 through the second connecting part 12; the second connecting part is of a fork-shaped structure.
In the embodiment of the present invention, the composite material fin body 2 is a complex flat uniform section curved profile structure. The composite material wing panel body 2 is connected with the metal joint 1, the structure is very thin, and the overall aerodynamic shape of the wing cannot be changed after the integral assembly. The maximum thickness of the composite material wing body 2 is in the middle of the wing surface, the thickness is ten millimeters, the lowest thickness is at the wing tip, and the thickness is several millimeters. The whole wing plate is designed by adopting an ultrathin streamline aerodynamic appearance, is subjected to transverse aerodynamic load of more than 3000N, has very strict requirements on product weight, and simultaneously requires large rigidity, high strength and light weight.
The utility model discloses an in an optional embodiment, metal joint 1 the Y-shaped structure is last to have a plurality of threaded connection holes, composite material fin body 2 with the position that the Y-shaped structure corresponds has a plurality of threaded connection holes, inserts through the bolt threaded connection hole on the composite material fin body 2 and threaded connection hole on the Y-shaped structure, metal joint 1 with composite material fin body 2 fixed connection. The connection strength and rigidity can be ensured, and the continuous transition of the structural rigidity can be ensured.
Optionally, the bolts are inserted into the threaded connection holes on the upper surface of the composite material fin body 2, and are arranged in a staggered manner with the threaded connection holes on the lower surface of the composite material fin body 2. During concrete connection, screws are screwed from the upper side and the lower side to the middle of the composite material wing piece body 2, the upper screw holes and the lower screw holes are arranged in a staggered mode, and under the condition that the appearance of the ultrathin wing piece is basically free of protrusions, fibers needing to be broken through the screw holes in one side cannot form a coherent problem, so that the product has enough connection strength and rigidity.
In an optional embodiment of the present invention, the composite material fin body 2 is a hollow structure. And a closed hollow structure is formed by adding a blocking piece on the right side for gluing and blocking. And reinforcing ribs and/or foam materials are arranged in the hollow structure. The composite material fin body 2 adopts a pultrusion process and hollow filling foam, so that the weight is effectively reduced on the premise of ensuring high rigidity.
In an optional embodiment of the present invention, the composite material fin body 2 is a carbon fiber composite material fin body. As shown in FIG. 5, the carbon fiber composite airfoil body includes: the carbon cloth comprises a middle rib 0-degree fiber 21, a first layer of mixed woven carbon cloth 22 outside the middle rib 0-degree fiber and a second layer of mixed woven carbon cloth 23 outside the first layer of mixed woven carbon cloth. The fiber direction of the composite material wing panel body 2 adopts a pultrusion profile molding manufacturing process, and the middle part is divided into an inner part, a middle part and an outer part which are respectively blended with the mixed woven carbon cloth during pultrusion manufacturing. Preferably, the layering mode adopts: the middle rib is 0 degree fiber 21, the first layer is mixed and weaved with carbon cloth 22, the second layer is mixed and weaved with carbon cloth 23, the position 24 of the outer side of the second layer is 2mm inwards, and the N area 25.
The above embodiment of the utility model provides an in, the fin comprises metal joint 1 and carbon-fibre composite fin body 2, simple structure. The metal joint 1 is a high-strength metal reinforcing structure and is provided with a threaded connecting hole, and during assembly, the connecting position of the metal joint 1 and the composite material fin body 2 is a fork-shaped structure, so that the connection strength and rigidity and the continuous transition of the structural rigidity are ensured; the screws are screwed from the upper side and the lower side to the middle of the composite material wing piece body 2, the upper screw holes and the lower screw holes are arranged in a staggered mode, and under the condition that the appearance of the ultrathin wing piece is basically free of protrusions, fibers needing to be broken through the screw holes in the single side cannot form a coherent problem, so that the product has enough connection strength and rigidity. The composite airfoil body 2 is a complex flat constant section curved profile structure, a cross-sectional view of which is shown in FIG. 4. The maximum thickness of the composite material wing body 2 is in the middle of the wing surface, the thickness is ten millimeters, the lowest thickness is at the wing tip, and the thickness is several millimeters. The composite material fin body 2 is internally of a hollow structure, a reinforcing rib is arranged in the middle of the hollow structure, foam is filled in the square hollow structure for reinforcement, and the weight is effectively reduced on the premise of ensuring large rigidity. The hollow structure at the front end of the composite material wing body 2 is sealed by gluing a plug sheet.
The wing piece of the embodiment of the utility model has the advantages of high rigidity, high strength and light weight; the connection mode is reliable; the production process of the pultruded profile is adopted, the middle part of the pultruded profile is divided into an inner part, a middle part and an outer part which are respectively blended with the mixed woven carbon cloth during the pultruded profile, the product performance is effectively enhanced, the product is manufactured according to the required length, the production cost is reduced by more than 80% compared with the traditional structure, and the production period is shortened by more than 50%.
An embodiment of the utility model provides an aircraft is still provided, include: fuselage and with fuselage fixed connection's fin, the fin is as above the fin of aircraft, at least one connecting hole has on the first connecting portion of the metal joint 1 of fin, metal joint 1 passes through on the first connecting portion at least one connecting hole with fuselage fixed connection.
The metal joint 1 is connected with the composite material wing panel body 2 through a plurality of bolts, the metal joint 1 is fixed with the machine body through 1 large metal circular hole surface, the small metal circular holes are in auxiliary connection, and the small metal circular holes simultaneously play a certain leveling function and meet the pneumatic requirement of the composite material wing surface.
The foregoing is a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the principle of the present invention, and these improvements and decorations should also be regarded as the protection scope of the present invention.
Claims (10)
1. An airfoil for an aircraft, comprising: a metal joint (1) and a composite material fin body (2);
the metal joint (1) is provided with a first connecting part (11) and a second connecting part (12), the metal joint (1) is connected with the fuselage of an aircraft through the first connecting part (11), and is fixedly connected with the composite material wing panel body (2) through the second connecting part (12); the second connecting part is of a fork-shaped structure.
2. The aircraft wing according to claim 1, characterized in that said fork structure has a plurality of threaded connection holes, said composite wing body (2) has a plurality of threaded connection holes in correspondence of said fork structure, said metal joint (1) is fixedly connected to said composite wing body (2) by means of bolts inserted in said threaded connection holes in said composite wing body (2) and in said threaded connection holes in said fork structure.
3. The airfoil of the aircraft according to claim 2, characterized in that the threaded connection holes for the bolts inserted into the upper surface of the composite airfoil body (2) are staggered with respect to the threaded connection holes for the bolts inserted into the lower surface of the composite airfoil body (2).
4. The airfoil of the aircraft according to claim 1, characterized in that the composite airfoil body (2) is a complex flat constant-section curved profile structure.
5. The airfoil of the aircraft according to claim 1, characterized in that the composite airfoil body (2) is a hollow structure.
6. The airfoil of the aircraft according to claim 5, wherein the hollow structure is a closed hollow structure.
7. The airfoil of the aircraft according to claim 6, characterized in that reinforcing ribs and/or foam material are provided in the hollow structure.
8. The airfoil of the aircraft according to claim 1, characterized in that the composite airfoil body (2) is a carbon fiber composite airfoil body.
9. The airfoil of the aircraft as claimed in claim 8, wherein the carbon fiber composite airfoil body comprises: the carbon cloth comprises 0-degree fibers of a middle rib, a first layer of mixed woven carbon cloth outside the 0-degree fibers of the middle rib and a second layer of mixed woven carbon cloth outside the first layer of mixed woven carbon cloth.
10. An aircraft, comprising: fuselage and with fuselage fixed connection's fin, characterized in that, the fin is according to the fin of the aircraft of any one of claims 1 to 9, have at least one connecting hole on the first connecting portion of the metal joint (1) of fin, metal joint (1) through at least one connecting hole on the first connecting portion with fuselage fixed connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922247047.9U CN211568287U (en) | 2019-12-16 | 2019-12-16 | Aircraft and wing panel thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922247047.9U CN211568287U (en) | 2019-12-16 | 2019-12-16 | Aircraft and wing panel thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211568287U true CN211568287U (en) | 2020-09-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922247047.9U Active CN211568287U (en) | 2019-12-16 | 2019-12-16 | Aircraft and wing panel thereof |
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| CN (1) | CN211568287U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112478124A (en) * | 2020-11-24 | 2021-03-12 | 航天特种材料及工艺技术研究所 | High-bearing airfoil joint load transmission structure |
| CN116858036A (en) * | 2023-09-04 | 2023-10-10 | 北京爱思达航天科技有限公司 | Ultrathin light composite material flying wing and preparation method thereof |
| CN117073467A (en) * | 2023-09-04 | 2023-11-17 | 北京爱思达航天科技有限公司 | Light composite material flying wing capable of carrying devices and preparation method thereof |
-
2019
- 2019-12-16 CN CN201922247047.9U patent/CN211568287U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112478124A (en) * | 2020-11-24 | 2021-03-12 | 航天特种材料及工艺技术研究所 | High-bearing airfoil joint load transmission structure |
| CN116858036A (en) * | 2023-09-04 | 2023-10-10 | 北京爱思达航天科技有限公司 | Ultrathin light composite material flying wing and preparation method thereof |
| CN117073467A (en) * | 2023-09-04 | 2023-11-17 | 北京爱思达航天科技有限公司 | Light composite material flying wing capable of carrying devices and preparation method thereof |
| CN116858036B (en) * | 2023-09-04 | 2023-12-29 | 北京爱思达航天科技有限公司 | Ultrathin light composite material flying wing and preparation method thereof |
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