CN110498036A - A kind of empennage panel joining structure, empennage and aircraft - Google Patents
A kind of empennage panel joining structure, empennage and aircraft Download PDFInfo
- Publication number
- CN110498036A CN110498036A CN201910726930.8A CN201910726930A CN110498036A CN 110498036 A CN110498036 A CN 110498036A CN 201910726930 A CN201910726930 A CN 201910726930A CN 110498036 A CN110498036 A CN 110498036A
- Authority
- CN
- China
- Prior art keywords
- main box
- siding
- box section
- empennage
- connector
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
A kind of empennage panel joining structure, empennage and aircraft, the empennage panel joining structure include main box section siding, rear bulkhead plate, main box Duan Liang and connector；The main box section siding is connect with the main box section beam, and the rear bulkhead plate is connect with the connector；The main box Duan Liang is connect the main box section siding to be connect with the rear bulkhead plate with the connector.Pass through main box Duan Liang and the main box section siding of connection realization of connector and being indirectly connected with for rear bulkhead plate, the smooth of aerodynamic surface after main box section siding connect with rear bulkhead plate can be ensured that without using structure glue correction of the flank shape and by main box section siding is sagging or the use modes such as gasket, sacrificial layer it is ensured that the scale requirement of main box section siding and rear bulkhead plate bonding pad.
Description
Technical field
The present invention relates to technical field of aerospace, specifically a kind of empennage panel joining structure, and it is provided with this structure
Empennage and aircraft.
Background technique
Between primary load bearing box section and rear, need to solve the connectivity problem of main box section siding and rear bulkhead plate.Such as Fig. 1
Shown, main box section siding is usually bigger than rear wall panel thickness, and main box section siding exceeds main box section soffit of girder plate face certain distance, backward
Edge cabin direction extends.The main box section siding stretched out is successively decreased by laying realizes that thickness is thinned, and is formed and is sunk.Main box section siding is at it
Bogging down area is overlapped with rear siding using fastener.Main box section siding needs sagging height and rear wall panel thickness phase
It closes, while may need to make up manufacture/assembling deviation by the way of gasket or sacrificial layer, to control main box section siding with after
The outer mold surface scale of edge siding bonding pad.In addition, the pneumatic external form requirement in order to guarantee siding bonding pad, the laying of outer mold surface are passed
Subtract area to need to use structure glue repairing type after mounting.
In this scheme, the thinned undercut nature of main box section siding increases the complexity of wallboard construction feature, phase
Increase design, the difficulty of manufacture with answering.In addition, the deviation of main box section siding collapsed position may cause rear siding and main box
Section siding Assembly Interference, to increase bonding pad assembly difficulty.In addition, this scheme needs to make up system by the way of sacrificial layer
Make/assembling deviation to control outer mold surface scale, further increase the complexity of design, manufacture, assembly, improve time and warp
Ji cost.After assembly, the laying of main box section siding outer mold surface successively decreases area need to be using structure glue repairing type, to guarantee siding bonding pad
Pneumatic external form requirement, increases installation step.
Summary of the invention
The object of the present invention is to provide a kind of complex degree of structure, and low, outer mold surface control is easy, assembles simple empennage wall
Board connecting structure.
To solve the above problems, the present invention provides a kind of empennage panel joining structure, including main box section siding, rear cabin
Siding, main box Duan Liang and connector；
The main box section siding is connect with the main box section beam, and the rear bulkhead plate is connect with the connector；
The main box Duan Liang is connect the main box section siding to be connect with the rear bulkhead plate with the connector.
Further, the main box section siding is detachably connected with the main box Duan Liang by fastener；And/or it is described after
Edge bulkhead plate is detachably connected with the connector by fastener；And/or the main box Duan Liang and the connector pass through tightly
Firmware is detachably connected.
Further, the main box Duan Liang includes the first siding interconnecting piece interconnected and the first convergence part, and described
One siding interconnecting piece is connect with the main box section siding, and first convergence part is connect with the connector.
Further, the first siding interconnecting piece is set at a predetermined angle with first convergence part.
Further, the main box Duan Liang is made of carbon fibre reinforced composite.
Further, the connector includes the second siding interconnecting piece interconnected and the second convergence part, and described second
Siding interconnecting piece is connect with the rear bulkhead plate, and second convergence part is connect with the main box section beam.
Further, the second siding interconnecting piece is set at a predetermined angle with second convergence part.
Further, the connector is made of carbon fibre reinforced composite or metal material.
The present invention also provides a kind of empennage, it is provided with the empennage siding connection knot as described in any of the above-described technical solution
Structure.
Invention further provides a kind of aircrafts, are provided with empennage as described in the above technical scheme.
The beneficial effect of a kind of empennage panel joining structure of the present invention, wing and aircraft is: by main box Duan Liang with connect
The main box section siding of connection realization of part and being indirectly connected with for rear bulkhead plate can ensure that main box section without using structure glue correction of the flank shape
Aerodynamic surface is smooth after siding is connect with rear bulkhead plate, and does not need (sagging structure manufacture that main box section siding sink
It is more difficult) or using modes such as gasket, sacrificial layers it is ensured that main box section siding and the scale of rear bulkhead plate bonding pad are wanted
It asks.
Detailed description of the invention
Fig. 1 is empennage panel joining structure schematic diagram in the prior art involved in background technique；
Fig. 2 is empennage panel joining structure schematic diagram in the present invention.
Appended drawing reference:
1, main box section siding, 2, rear bulkhead plate, 3, main box Duan Liang, 4, connector；
31, the first siding interconnecting piece, the 32, first convergence part, 33, joins；
41, the second siding interconnecting piece, the 42, second convergence part.
Specific embodiment
In order to make the objectives, technical solutions and advantages of the present invention clearer, With reference to embodiment and join
According to attached drawing, the present invention is described in more detail.It should be understood that these descriptions are merely illustrative, and it is not intended to limit this hair
Bright range.In addition, in the following description, descriptions of well-known structures and technologies are omitted, to avoid this is unnecessarily obscured
The concept of invention.
First embodiment
Fig. 2 is empennage panel joining structure schematic diagram in the present invention.
A kind of empennage panel joining structure, including main box section siding 1, rear bulkhead plate 2, main box section beam 3 and connector 4；
The main box section siding 1 is connect with the main box section beam 3, and the rear bulkhead plate 2 is connect with the connector 4；The main box
Section beam 3 is connect the main box section siding 1 to be connect with the rear bulkhead plate 2 with the connector 4.
In the prior art in order to which main box section siding 1 to be connect with rear bulkhead plate 2, and junction surfacing, it needs
Main box section siding 1 is arranged to a sagging structure with 2 junction of rear bulkhead plate, keeps its thinning, rear bulkhead plate 2 is overlapped on
At structure of sinking, and the two is connected by fastener, two junction surfacings after connection may be implemented in this way.But this
Kind structure Structure of need glue repairing type, or need to guarantee that pneumatic outer mold surface is smooth using gasket/sacrificial layer.In the present embodiment,
Both it is connect by main box section beam 3 with connector 4 and realizes that main box section siding 1, rear bulkhead plate 2 are indirectly connected with, be both able to achieve
Connection, and do not need on main box section siding 1 be arranged sink structure, do not increase the complicated journey of main box section wallboard construction feature
Degree, while reducing manufacture difficulty.
For convenient disassembly, in practical applications, the main box section siding 1 can by fastener with the main box section beam 3
Dismantling connection；And/or the rear bulkhead plate 2 is detachably connected with the connector 4 by fastener；And/or the main box
Section beam 3 is detachably connected with the connector 4 by fastener.
Specifically, main box section beam 3 includes the first siding interconnecting piece 31, the first convergence part 32 and joins 33, the first siding
Interconnecting piece 31, the first convergence part 32 and joins 33 are plate structure, all there is the one end being oppositely arranged and the other end.First
One end of siding interconnecting piece 31 is connect with one end of the first convergence part 32, the other end of the first convergence part 32 and the one of joins 33
End connection, the first siding interconnecting piece 31 is set at a predetermined angle with the first convergence part 32, the first convergence part 32 and joins 33 at
Predetermined angle setting, and the first siding interconnecting piece 31 and joins 33 are located at the ipsilateral of the first convergence part 32；Main box section beam 3 is whole
C-shaped is presented.Since aircraft tail surface is fairshaped curved surface, predetermined angle may be acute angle, right angle, it is also possible to blunt
Angle.
In the art, the first siding interconnecting piece 31 is also known as beam edge strip, and the first convergence part 32 is also known as web.
Specifically, connector 4 includes the second siding interconnecting piece 41 and the second convergence part 42, the second siding interconnecting piece 41 and the
Two convergence parts 42 are plate structure, all there is the one end being oppositely arranged and the other end.One end of second siding interconnecting piece 41 with
One end of second convergence part 42 connects, and is set at a predetermined angle；Main box section beam 3 is whole to be presented L shape.Due to aircraft tail surface
It is fairshaped curved surface, therefore predetermined angle may be acute angle, right angle, it is also possible to obtuse angle.
First siding interconnecting piece 31 is connect with main box section siding 1 by fastener, the second siding interconnecting piece 41 and rear cabin
Siding 2 is connected by fastener, and the first convergence part 32 is connect with the second convergence part 42 by fastener.In specific installation, the
One siding interconnecting piece 31 is in the same plane with the second siding interconnecting piece 41, and the first convergence part 32 and the second convergence part 42 are close
Fitting, can be such that main box section siding 1 is in the same plane with rear bulkhead plate 2 in this way.
In a preferred embodiment, connector 4 is made of carbon fibre reinforced composite.
Have in preferred embodiment separately, connector 4 is made of metal material, such as aluminium alloy.
During installation, main 1 outer surface of box section siding is aligned with rear bulkhead plate 2 by mold, then with L shape connector 4
Rear bulkhead plate 2 is connect with main box section beam 3 by fastener.
In the present embodiment, main box section covering do not stretch out soffit of girder plate face and also do not do it is sagging, use L-type connector 4 realize
Rear bulkhead plate 2 and main box section siding 1 connect, and the outer mold surface scale between siding is controlled by the position adjustment of L-type angle section.
In a preferred embodiment, main box section siding 1, rear bulkhead plate 2 and main box section beam 3 are all made of composite material
It is made, such as carbon fibre reinforced composite, therefore empennage panel joining structure is properly termed as the connection of composite material empennage siding
Structure.
Second embodiment
A kind of empennage is provided with empennage panel joining structure as described in the first embodiment.
Third embodiment
A kind of aircraft is arranged just like empennage described in second embodiment.
It should be understood that above-mentioned specific embodiment of the invention is used only for exemplary illustration or explains of the invention
Principle, but not to limit the present invention.Therefore, that is done without departing from the spirit and scope of the present invention is any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.In addition, appended claims purport of the present invention
Covering the whole variations fallen into attached claim scope and boundary or this range and the equivalent form on boundary and is repairing
Change example.
Claims (10)
1. a kind of empennage panel joining structure, it is characterised in that: including main box section siding (1), rear bulkhead plate (2), main box section
Beam (3) and connector (4)；
The main box section siding (1) connect with the main box Duan Liang (3), and the rear bulkhead plate (2) and the connector (4) are even
It connects；
The main box Duan Liang (3) is connect to by the main box section siding (1) and the rear bulkhead plate with the connector (4)
(2) it connects.
2. empennage panel joining structure as described in claim 1, it is characterised in that: the main box section siding (1) and the master
Box Duan Liang (3) is detachably connected by fastener；And/or
The rear bulkhead plate (2) is detachably connected with the connector (4) by fastener；And/or
The main box Duan Liang (3) is detachably connected with the connector (4) by fastener.
3. empennage panel joining structure as described in claim 1, it is characterised in that: the main box Duan Liang (3) includes mutually interconnecting
The the first siding interconnecting piece (31) connect and the first convergence part (32), the first siding interconnecting piece (31) and the main box section siding
(1) it connects, first convergence part (32) connect with the connector (4).
4. empennage panel joining structure as claimed in claim 3, it is characterised in that: the first siding interconnecting piece (31) and institute
The first convergence part (32) is stated to be set at a predetermined angle.
5. such as the described in any item empennage panel joining structures of Claims 1-4, it is characterised in that: the main box Duan Liang (3) by
Carbon fibre reinforced composite is made.
6. such as the described in any item empennage panel joining structures of Claims 1-4, it is characterised in that: the connector (4) includes
Second siding interconnecting piece (41) interconnected and the second convergence part (42), the second siding interconnecting piece (41) and the rear
Bulkhead plate (2) connection, second convergence part (42) connect with the main box Duan Liang (3).
7. empennage panel joining structure as claimed in claim 6, it is characterised in that: the second siding interconnecting piece (41) and institute
The second convergence part (42) is stated to be set at a predetermined angle.
8. empennage panel joining structure as claimed in claim 6, it is characterised in that: the connector (4) is by fibre reinforced
Composite material or metal material are made.
9. a kind of empennage, it is characterised in that: be provided with empennage panel joining structure as claimed in any one of claims 1 to 8.
10. a kind of aircraft, it is characterised in that: be provided with empennage as claimed in claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910726930.8A CN110498036B (en) | 2019-08-07 | 2019-08-07 | Empennage wall plate connecting structure, empennage and airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910726930.8A CN110498036B (en) | 2019-08-07 | 2019-08-07 | Empennage wall plate connecting structure, empennage and airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110498036A true CN110498036A (en) | 2019-11-26 |
| CN110498036B CN110498036B (en) | 2021-08-17 |
Family
ID=68588087
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910726930.8A Active CN110498036B (en) | 2019-08-07 | 2019-08-07 | Empennage wall plate connecting structure, empennage and airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110498036B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008103735A2 (en) * | 2007-02-22 | 2008-08-28 | Snow Aviation International, Inc. | Aircraft, and retrofit components therefor |
| CN103803054A (en) * | 2012-11-13 | 2014-05-21 | 波音公司 | Joint for composite wings |
| CN205675228U (en) * | 2016-06-13 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | Docking structure on spar flange for a kind of aerofoil covering |
| US20180155006A1 (en) * | 2016-12-02 | 2018-06-07 | Airbus Operations, S.L. | Aircraft stabilizer leading edge integration with torsion box and fuselage |
-
2019
- 2019-08-07 CN CN201910726930.8A patent/CN110498036B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008103735A2 (en) * | 2007-02-22 | 2008-08-28 | Snow Aviation International, Inc. | Aircraft, and retrofit components therefor |
| CN103803054A (en) * | 2012-11-13 | 2014-05-21 | 波音公司 | Joint for composite wings |
| CN205675228U (en) * | 2016-06-13 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | Docking structure on spar flange for a kind of aerofoil covering |
| US20180155006A1 (en) * | 2016-12-02 | 2018-06-07 | Airbus Operations, S.L. | Aircraft stabilizer leading edge integration with torsion box and fuselage |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110498036B (en) | 2021-08-17 |
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