CN110498036B - Empennage wall plate connecting structure, empennage and airplane - Google Patents
Empennage wall plate connecting structure, empennage and airplane Download PDFInfo
- Publication number
- CN110498036B CN110498036B CN201910726930.8A CN201910726930A CN110498036B CN 110498036 B CN110498036 B CN 110498036B CN 201910726930 A CN201910726930 A CN 201910726930A CN 110498036 B CN110498036 B CN 110498036B
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- wall plate
- main box
- box section
- rear edge
- connecting piece
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
A tail wing wall plate connecting structure, a tail wing and an airplane are provided, wherein the tail wing wall plate connecting structure comprises a main box section wall plate, a rear edge cabin wall plate, a main box section beam and a connecting piece; the main box section wall plate is connected with the main box section beam, and the rear edge cabin wall plate is connected with the connecting piece; the main box section beam is connected with the connecting piece to connect the main box section wall plate with the rear edge cabin wall plate. The main box section beam is connected with the connecting piece to realize indirect connection of the main box section wallboard and the rear edge bulkhead plate, so that the flatness of the pneumatic surface of the main box section wallboard and the rear edge bulkhead plate after connection can be ensured without structural glue modification, and the step requirement of a connection area of the main box section wallboard and the rear edge bulkhead plate can be ensured without sinking the main box section wallboard or using a gasket, a sacrificial layer and the like.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a tail wing wall plate connecting structure, a tail wing with the structure and an airplane with the structure.
Background
The problem of connection between a main box section wallboard and a rear edge bulkhead needs to be solved between the main bearing box section and the rear edge. As shown in fig. 1, the main box wall is typically thicker than the trailing edge wall, and extends beyond the main box spar web surface a distance toward the trailing edge compartment. The thickness of the wall plate of the extended main box section is reduced through ply drop, and sinking is formed. The main box section wall panel overlaps the trailing edge wall panel in its recessed area using fasteners. The height of the main box wall required to be sunk is related to the thickness of the trailing edge wall, and a gasket or a sacrificial layer may be required to compensate for manufacturing/assembly deviation so as to control the outer profile step of the connecting area of the main box wall and the trailing edge wall. In addition, to ensure the aerodynamic shape requirements of the wall connection area, the ply drop area of the outer profile needs to be trimmed with structural glue after assembly.
In this arrangement, the reduced thickness undercut feature of the main box section wall panel adds complexity to the wall panel construction features, and correspondingly increases the difficulty of design and manufacture. In addition, deviation in the depressed position of the main box section wall panel may cause the rear edge wall panel to interfere with the fitting of the main box section wall panel, thereby increasing the difficulty of fitting the joint region. In addition, the scheme needs to adopt a sacrificial layer mode to compensate manufacturing/assembling deviation so as to control the outer profile step, further increases the complexity of design, manufacture and assembly, and improves the time and economic cost. After assembly, the layer drop zone of the outer molded surface of the main box section wall plate needs to be repaired by using structural adhesive, so that the pneumatic appearance requirement of the wall plate connecting zone is ensured, and the assembly steps are increased.
Disclosure of Invention
The invention aims to provide a tail wing wall plate connecting structure which is low in structural complexity, easy to control the outer appearance and simple to assemble.
In order to solve the problems, the invention provides a tail wing wall plate connecting structure which comprises a main box section wall plate, a rear edge cabin wall plate, a main box section beam and a connecting piece, wherein the main box section wall plate is arranged on the main box section beam;
the main box section wall plate is connected with the main box section beam, and the rear edge cabin wall plate is connected with the connecting piece;
the main box section beam is connected with the connecting piece to connect the main box section wall plate with the rear edge cabin wall plate.
Furthermore, the main box section wall plate is detachably connected with the main box section beam through a fastener; and/or the trailing edge bulkhead plate is detachably connected with the connecting piece through a fastener; and/or the main box section beam is detachably connected with the connecting piece through a fastener.
Furthermore, the main box section beam comprises a first wall plate connecting part and a first connecting part which are connected with each other, the first wall plate connecting part is connected with the main box section wall plate, and the first connecting part is connected with the connecting piece.
Further, the first wall plate connecting part and the first connecting part are arranged at a preset angle.
Further, the main box section beam is made of carbon fiber reinforced composite materials.
Further, the connecting piece comprises a second wall plate connecting portion and a second connecting portion, wherein the second wall plate connecting portion and the second connecting portion are connected with each other, the second wall plate connecting portion is connected with the trailing edge cabin wall plate, and the second connecting portion is connected with the main box section beam.
Further, the second wall plate connecting part and the second connecting part are arranged at a preset angle.
Further, the connecting piece is made of carbon fiber reinforced composite materials or metal materials.
The invention also provides the empennage which is provided with the empennage wall plate connecting structure in any technical scheme.
The invention also provides an airplane which is provided with the empennage in the technical scheme.
The empennage wall plate connecting structure, the wing and the airplane have the beneficial effects that: the main box section beam is connected with the connecting piece to realize indirect connection of the main box section wallboard and the rear edge bulkhead plate, so that the flatness of the pneumatic surface of the connected main box section wallboard and the rear edge bulkhead plate can be ensured without structural glue modification, and the step requirement of a connecting area of the main box section wallboard and the rear edge bulkhead plate can be ensured without sinking the main box section wallboard (the sunken structure is difficult to manufacture) or using a gasket, a sacrificial layer and the like.
Drawings
FIG. 1 is a schematic view of a prior art empennage panel attachment configuration of the background art;
fig. 2 is a schematic view of the connection structure of the tail panel of the present invention.
Reference numerals:
1. a main box section wallboard 2, a rear edge cabin wallboard 3, a main box section beam 4 and a connecting piece;
31. a first wall plate connecting part 32, a first connecting part 33 and a connecting part;
41. a second wall plate connecting part 42 and a second joint part.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
First embodiment
Fig. 2 is a schematic view of the connection structure of the tail panel of the present invention.
A tail wing wall plate connecting structure comprises a main box section wall plate 1, a rear edge cabin wall plate 2, a main box section beam 3 and a connecting piece 4; the main box section wall plate 1 is connected with the main box section beam 3, and the rear edge bulkhead plate 2 is connected with the connecting piece 4; the main box section beams 3 are connected with the connecting pieces 4 for connecting the main box section wall panels 1 with the trailing edge bulkhead panel 2.
In order to connect the main box section wall plate 1 and the rear edge bulkhead plate 2 and to realize the smooth surface of the joint, the joint of the main box section wall plate 1 and the rear edge bulkhead plate 2 needs to be set to be a sunken structure to be thinned, the rear edge bulkhead plate 2 is lapped on the sunken structure, and the main box section wall plate and the rear edge bulkhead plate are connected through a fastener in the prior art. However, this construction requires structural glue modification or the use of shims/sacrificial layers to ensure the aerodynamic profile is flat. In this embodiment, the main box girder 3 is connected with the connecting member 4 to indirectly connect the main box wallboard 1 and the rear edge bulkhead 2, so that the connection between the main box wallboard 1 and the rear edge bulkhead can be realized, a sunken structure does not need to be arranged on the main box wallboard 1, the complexity of the structural characteristics of the main box wallboard is not increased, and the manufacturing difficulty is reduced.
For convenience of disassembly, in practical application, the main box wall plate 1 is detachably connected with the main box beam 3 through a fastener; and/or the trailing edge bulkhead plate 2 is detachably connected with the connecting piece 4 through a fastener; and/or the main box section beam 3 is detachably connected with the connecting piece 4 through a fastener.
Specifically, the main box section girder 3 includes a first wall plate connection portion 31, a first joining portion 32, and a connecting portion 33, and the first wall plate connection portion 31, the first joining portion 32, and the connecting portion 33 are all plate-shaped structures and have one end and the other end which are oppositely disposed. One end of the first wall plate connecting portion 31 is connected with one end of the first connecting portion 32, the other end of the first connecting portion 32 is connected with one end of the connecting portion 33, the first wall plate connecting portion 31 and the first connecting portion 32 are arranged at a preset angle, the first connecting portion 32 and the connecting portion 33 are arranged at a preset angle, and the first wall plate connecting portion 31 and the connecting portion 33 are located on the same side of the first connecting portion 32; the main box section beam 3 as a whole assumes a C-shape. Because the surface of the empennage of the airplane is a streamline curved surface, the preset angle can be an acute angle, a right angle or an obtuse angle.
In the art, the first wall plate connection portion 31 is also called a flange strip, and the first joint portion 32 is also called a web.
Specifically, the connecting member 4 includes a second wall plate connecting portion 41 and a second joining portion 42, and the second wall plate connecting portion 41 and the second joining portion 42 are both plate-shaped structures and have one end and the other end that are disposed opposite to each other. One end of the second wall plate connecting portion 41 is connected to one end of the second coupling portion 42 and is disposed at a predetermined angle; the main box section beam 3 as a whole takes on an L-shape. Because the surface of the empennage of the airplane is a streamline curved surface, the preset angle can be an acute angle, a right angle or an obtuse angle.
The first panel connecting portion 31 is connected to the main box section panel 1 by a fastener, the second panel connecting portion 41 is connected to the trailing edge bulkhead panel 2 by a fastener, and the first joining portion 32 is connected to the second joining portion 42 by a fastener. In particular, when the panel is installed, the first panel connecting portion 31 and the second panel connecting portion 41 are located in the same plane, and the first joining portion 32 and the second joining portion 42 are closely attached to each other, so that the main box section panel 1 and the trailing edge deck panel 2 are located in the same plane.
In a preferred embodiment, the connecting piece 4 is made of a carbon fibre-reinforced composite material.
In a further preferred embodiment, the connecting element 4 is made of a metallic material, such as an aluminium alloy.
When the installation is carried out, the outer surface of the main box wall panel 1 is aligned with the rear edge bulkhead panel 2 through a mold, and the rear edge bulkhead panel 2 is connected with the main box girder 3 through an L-shaped connecting piece 4 through a fastener.
In the embodiment, the main box section skin does not extend out of the web surface of the girder and does not sink, the connection between the trailing edge bulkhead plate 2 and the main box section wallboard 1 is realized by using the L-shaped connecting piece 4, and the appearance surface step difference between the wallboard is controlled by adjusting the position of the L-shaped angle bar.
In a preferred embodiment, the main box wall panels 1, the trailing edge bulkhead panels 2 and the main box girders 3 are made of composite material, such as carbon fiber reinforced composite material, so that the tail wall panel connection structure can be referred to as a composite tail wall panel connection structure.
Second embodiment
A tail provided with the tail panel connection structure of the first embodiment.
Third embodiment
An aircraft provided with a tail wing as described in the second embodiment.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (9)
1. An empennage wall plate connecting structure is characterized in that: the combined type combined box girder comprises a main box section wall plate (1), a rear edge cabin wall plate (2), a main box section beam (3) and a connecting piece (4);
the main box section wall plate (1) is connected with the main box section beam (3), and the rear edge cabin wall plate (2) is connected with the connecting piece (4);
the main box section beam (3) is connected with the connecting piece (4) to connect the main box section wall plate (1) with the rear edge bulkhead plate (2);
the main box section beam (3) comprises a first wall plate connecting part (31) and a first joint part (32) which are connected with each other, the connecting piece (4) comprises a second wall plate connecting part (41) and a second joint part (42) which are connected with each other, the second wall plate connecting part (41) is connected with the rear edge cabin wall plate (2), and the second joint part (42) is connected with the main box section beam (3);
the connecting piece (4) is L-shaped, the second wall plate connecting portion (41) is connected with the rear edge cabin wall plate (2), the first connecting portion (32) is tightly attached to the second connecting portion (42), so that the first wall plate connecting portion (31) and the second wall plate connecting portion (41) are located in the same plane, and the step difference formed by the outer appearance surfaces of the rear edge cabin wall plate (2) and the main box section wall plate (1) is controlled through position adjustment of the L-shaped connecting piece (4).
2. A fin panel connection structure according to claim 1, wherein: the main box section wall plate (1) is detachably connected with the main box section beam (3) through a fastener; and/or
The rear edge bulkhead plate (2) is detachably connected with the connecting piece (4) through a fastener; and/or
The main box section beam (3) is detachably connected with the connecting piece (4) through a fastener.
3. A fin panel connection structure according to claim 1, wherein: the first wall plate connecting part (31) is connected with the main box section wall plate (1), and the first joint part (32) is connected with the connecting piece (4).
4. A fin panel connection structure according to claim 3, wherein: the first wall plate connecting portion (31) and the first engagement portion (32) are arranged at a predetermined angle.
5. A fin panel connection structure as claimed in any one of claims 1 to 4, wherein: the main box section beam (3) is made of carbon fiber reinforced composite materials.
6. A fin panel connection structure according to claim 1, wherein: the second wall plate connecting portion (41) is disposed at a predetermined angle to the second coupling portion (42).
7. A fin panel connection structure according to claim 1, wherein: the connecting piece (4) is made of carbon fiber reinforced composite materials or metal materials.
8. A tail fin, characterized by: a fin panel connection structure according to claim 1.
9. An aircraft, characterized by: provided with a tail as claimed in claim 8.
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 CN110498036A (en) | 2019-11-26 |
| CN110498036B true CN110498036B (en) | 2021-08-17 |
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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 |
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| Country | Link |
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| CN (1) | CN110498036B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (3)
| 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 |
| US9272769B2 (en) * | 2012-11-13 | 2016-03-01 | The Boeing Company | Joint for composite wings |
| ES2764122T3 (en) * | 2016-12-02 | 2020-06-02 | Airbus Operations Sl | Integration of the leading edge of an aircraft stabilizer with the torsion box and the fuselage |
-
2019
- 2019-08-07 CN CN201910726930.8A patent/CN110498036B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| Publication number | Publication date |
|---|---|
| CN110498036A (en) | 2019-11-26 |
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