CN203666969U - Bonded aerofoil architecture - Google Patents
Bonded aerofoil architecture Download PDFInfo
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- CN203666969U CN203666969U CN201320736584.XU CN201320736584U CN203666969U CN 203666969 U CN203666969 U CN 203666969U CN 201320736584 U CN201320736584 U CN 201320736584U CN 203666969 U CN203666969 U CN 203666969U
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- rib
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- front wall
- crossbeam
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Abstract
The utility model provides a bonded aerofoil architecture. The architecture comprises a framework structure formed by a front wall, a back wall and wing ribs in a combining manner, a beam, purlins and a carbon tube, wherein the wing ribs are arranged on two sides, the framework structure is provided with a cavity, the front wall and the back wall are mutually parallel, and the wing ribs on the two sides are mutually parallel; the beam which is parallel to the back wall is fixed in the framework structure, and the two ends of the beam are respectively fixed on the wing ribs on the two sides; the plurality of wing ribs are respectively arranged in the framework structure, one end of each wing rib is arranged on the front wall, the other end of each wing rib passes through the back wall, and the wing ribs which pass through the beam are perpendicular to the beam; the plurality of purlins are respectively fixed on the upper surfaces and the lower surfaces of the wing ribs, and the purlins are parallel to the beam; the carbon tube is positioned in the middle of the wing ribs, passes through the wing rib on one side and a plurality of wing ribs in the framework structure, and is parallel to a wing spar. The architecture has the advantages and positive effects that because the technical scheme is adopted, the structure of an airplane aerofoil is stable, the weight of the aerofoil is lightened, the bonding degree is high, and the flying performance of an airplane is improved.
Description
Technical field
The invention relates to model aircraft and association area, relates in particular to a kind of bonding wing framework.
Background technology
Existing wing framework is simple, basic is that unsaturated material and wooden white glue with vinyl are bonding, the wing framework produced is like this perishable, degree of adhesion is low, easily come off and easily make wing weight increase, be unfavorable for the requirement of integrated airplane weight-saving, cause the quality of product to reduce, reduced the airworthiness of aircraft.
Summary of the invention
For solving the problems of the technologies described above, the technical scheme that the invention adopts is: a kind of bonding wing framework is provided, comprises:
Rear wall (6), front wall (4) and rib (3), rib (3) combination of described front wall, rear wall and both sides surrounds the framed structure with cavity, and front wall and rear wall parallel to each other, both sides rib is parallel to each other;
One crossbeam (1), described crossbeam is parallel to rear wall (6) and is fixed in framed structure, and two ends are separately fixed on the rib of both sides;
Some ribs (3) are arranged at respectively in framed structure, and it is upper that described rib one end is arranged on front wall (4), and the other end is through rear wall (6), and rib is through crossbeam (1) vertical with it;
Described rib upper and lower surface is fixed with respectively many stringers (2), and described stringer (2) is parallel with crossbeam (1);
One carbon pipe (5), described carbon pipe is positioned at the middle part of rib, and through the rib in one side flank rib and many framed structures, described carbon pipe is parallel with spar.
Further; Described rib is positioned at framed structure Outboard Sections and has multiple rib bifurcateds (7), and described rib bifurcated is fixed on rib and with rib and forms certain angle.
Further; Be placed on the rib (3) of framed structure and there is engraved structure.
Further; All fixed parts all bond fixing by structural adhesive.
Further; Described stringer (2) is paulownia wood material.
Further; Described crossbeam, rib, front wall and Hou Qiang are cork wood material.
Advantage and good effect that the invention has are: owing to adopting above technical scheme, cause the stabilized structure of aircraft wing, alleviate the weight of wing, improve withstanding corrosion degree, degree of adhesion is strong, has improved the performance of aircraft flight.
Brief description of the drawings
Fig. 1 is a kind of bonding wing configuration diagram
In figure:
1, crossbeam 2, stringer 3, rib 4, front wall 5, carbon pipe 6, rear wall 7, rib bifurcated
Detailed description of the invention
As shown in Figure 1: a kind of bonding wing framework, comprising:
One crossbeam 1, described crossbeam is parallel to rear wall 6 and is fixed in framed structure, and two ends are separately fixed on the rib of both sides;
Some ribs 3 are arranged at respectively in framed structure, and described rib one end is arranged on front wall 4, and the other end is through rear wall 6, and rib is through crossbeam 1 vertical with it;
Described rib upper and lower surface is fixed with respectively many stringers 2, and described stringer 2 is parallel with crossbeam 1; To covering, it arrives supporting role to stringer.
One carbon pipe 5, described carbon pipe 5 is positioned at the middle part of rib 3, and through the rib in one side flank rib and many framed structures, described carbon pipe is parallel with spar.Carbon pipe is played a supporting role, and can make in the corresponding mechanism of fuselage insertion carbon pipe, fuselage to be connected with wing.
Further; Described rib is positioned at framed structure Outboard Sections and has multiple rib bifurcateds 7, and described rib bifurcated is fixed on rib and with rib and forms certain angle.Angle is generally 30 °-75 ° rib bifurcated supporting roles in edge for covering.
Further; Be placed on the rib 3 of framed structure and there is engraved structure.Can on actv. brace foundation, reduce the weight of wing structure.
Further; All fixed parts all bond fixing by structural adhesive.Degree of adhesion is improved.
Further; Described stringer 2 is paulownia wood material.Material is light and tough, not bent do not stick up indeformable.
Further; Described crossbeam, rib, front wall and Hou Qiang are cork wood material.Proportion is little, and has good elasticity.
Specific works process:
First produce the constituent elements of the each cage structure of wing with paulownia wooden frame, cork wood, then by rear wall 6, front wall 4 and rib 3 use structural adhesive combinations surround the framed structure with cavity, then crossbeam 1 use structural adhesive is fixed on the rib of both sides, then in the middle of all the other rib 3 one end being bonded at respectively on front wall, pass crossbeam, the other end is through rear wall, thereby rib 3 is arranged in framed structure, rib one end is fixed on front wall 4, the other end is through rear wall 6, and rib is through crossbeam 1 vertical with it; Rib bifurcated 7 is sticked on the rib in framed structure outside, and form certain angle with rib, angle the best is
between 30 °-75 °then stringer 2 is pasted in rib upper and lower surface, the rib finally carbon pipe 5 being passed in avris rib and many framed structures, and carbon pipe is parallel with spar, can make the corresponding mechanism of fuselage insert in carbon pipe fuselage is connected with wing.
Above the embodiment of the invention is had been described in detail, but described content is only for the preferred embodiment of the invention, can not be considered to for limiting practical range of the present invention.All equalization variation and improvement etc. of doing according to the invention scope, within all should still belonging to this patent covering scope.
Claims (6)
1. a bonding wing framework, is characterized in that: comprising:
Rear wall (6), front wall (4) and rib (3), rib (3) combination of described front wall, rear wall and both sides surrounds the framed structure with cavity, and front wall and rear wall parallel to each other, both sides rib is parallel to each other;
One crossbeam (1), described crossbeam is parallel to rear wall (6) and is fixed in framed structure, and two ends are separately fixed on the rib of both sides;
Some ribs (3) are arranged at respectively in framed structure, and it is upper that described rib one end is arranged on front wall (4), and the other end is through rear wall (6), and rib is through crossbeam (1) vertical with it;
Described rib upper and lower surface is fixed with respectively many stringers (2), and described stringer (2) is parallel with crossbeam (1);
One carbon pipe (5), described carbon pipe is positioned at the middle part of rib, and through the rib in one side flank rib and many framed structures, described carbon pipe is parallel with spar.
2. a kind of bonding wing framework according to claim 1, it is characterized in that: described rib is positioned at framed structure Outboard Sections and has multiple rib bifurcateds (7), described rib bifurcated is fixed on rib and with rib and forms certain angle, and angle is generally 30 °-75 °.
3. a kind of bonding wing framework according to claim 1, is characterized in that: described in be placed on the rib (3) of framed structure and there is engraved structure.
4. a kind of bonding wing framework according to claim 1, is characterized in that: all fixed parts all bond fixing by structural adhesive.
5. a kind of bonding wing framework according to claim 1, is characterized in that: described stringer (2) is paulownia wood material.
6. a kind of bonding wing framework according to claim 1, is characterized in that: described crossbeam, rib, front wall and Hou Qiang are cork wood material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320736584.XU CN203666969U (en) | 2013-11-20 | 2013-11-20 | Bonded aerofoil architecture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320736584.XU CN203666969U (en) | 2013-11-20 | 2013-11-20 | Bonded aerofoil architecture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203666969U true CN203666969U (en) | 2014-06-25 |
Family
ID=50963289
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320736584.XU Expired - Fee Related CN203666969U (en) | 2013-11-20 | 2013-11-20 | Bonded aerofoil architecture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203666969U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644771A (en) * | 2015-12-29 | 2016-06-08 | 中恒天信（天津）航空科技有限公司 | Inside bearing structure of unmanned aerial vehicle wing |
| CN110386244A (en) * | 2018-04-20 | 2019-10-29 | 北京京东尚科信息技术有限公司 | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it |
| WO2021128674A1 (en) * | 2019-12-27 | 2021-07-01 | 南京祖航航空科技有限公司 | High-strength wing structure |
-
2013
- 2013-11-20 CN CN201320736584.XU patent/CN203666969U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644771A (en) * | 2015-12-29 | 2016-06-08 | 中恒天信（天津）航空科技有限公司 | Inside bearing structure of unmanned aerial vehicle wing |
| CN110386244A (en) * | 2018-04-20 | 2019-10-29 | 北京京东尚科信息技术有限公司 | Unmanned plane wing skeleton and unmanned plane wing, unmanned plane comprising it |
| WO2021128674A1 (en) * | 2019-12-27 | 2021-07-01 | 南京祖航航空科技有限公司 | High-strength wing structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140625 Termination date: 20151120 |
|
| EXPY | Termination of patent right or utility model |