CN216186003U - Control surface and aircraft - Google Patents
Control surface and aircraft Download PDFInfo
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- CN216186003U CN216186003U CN202120327300.6U CN202120327300U CN216186003U CN 216186003 U CN216186003 U CN 216186003U CN 202120327300 U CN202120327300 U CN 202120327300U CN 216186003 U CN216186003 U CN 216186003U
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Abstract
The utility model discloses an control surface and an airplane, wherein the control surface comprises a control body, a first fixed shaft and a second fixed shaft; the first fixed shaft is arranged at the first end of the rudder body, the second fixed shaft is arranged at the second end of the rudder body, and the axle centers of the first fixed shaft and the second fixed shaft are consistent; the rudder body is movably secured to a control surface mount by the first and second fixed shafts. The control surface and the airplane realize the connection of the control surface and the vertical tail wing through the first fixed shaft and the second fixed shaft, the number of metal joints is reduced, the important control function of the control surface as the control surface is met, and the structural efficiency is improved; openings on the vertical fin skin and the control surface skin are avoided, and the pneumatic efficiency is improved; and has the advantages of convenient disassembly and assembly, light weight and the like.
Description
Technical Field
The utility model relates to the technical field of aviation, in particular to a control surface and an airplane.
Background
The aircraft control surface is a steerable wing surface part in the wing and tail structure of the aircraft and is used for controlling the yaw, pitch and roll motions of the aircraft. For example, in aircraft, a rudder, typically mounted at the rear of a vertical tail wing, is used by the pilot to effect yaw steering about the vertical axis, such as to change the horizontal direction of the nose, along with elevators and ailerons to control pitch and roll movements of the aircraft.
The control surface structure of the traditional navigation aircraft is usually in a hinge connection mode, and is respectively formed by connecting a single lug joint arranged on a vertical tail beam and a double lug joint connected to the control surface beam through bolts, 4-6 metal machining parts are generally needed, and after assembly, the control surface structure rotates around the joints to achieve the purpose of deflection. In order to meet the installation and maintenance requirements of the control surface structure, an overhaul port and an installation port need to be formed in the skin at the front edge of the control surface, and the opening damages the surface of the control surface structure and influences the aerodynamic efficiency of the control surface. Meanwhile, in order to maintain and overhaul the control surface joint arranged on the vertical tail beam, a cover cap needs to be arranged on the control surface skin, so that the pneumatic efficiency is reduced, and the number of fasteners of the whole machine and the weight of the whole machine are increased. In addition, the traditional control surface needs to arrange the position of the control surface beam to the front edge position of the control surface as much as possible, so that the metal machining joint is as small as possible, and the weight of metal parts is reduced. This, in turn, results in the beams of the control surfaces not being arranged at the location of maximum thickness of the control surfaces, making the beams less load-bearing efficient.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a control surface and an airplane, which avoid openings on a wing surface skin and a control surface skin, realize the installation of the control surface and improve the aerodynamic efficiency.
In order to achieve the aim, the utility model discloses an operating surface which comprises a rudder body, a first fixed shaft and a second fixed shaft;
the first fixed shaft is arranged at the first end of the rudder body, the second fixed shaft is arranged at the second end of the rudder body, and the axle centers of the first fixed shaft and the second fixed shaft are consistent;
the rudder body is movably secured to a control surface mount by the first and second fixed shafts.
Optionally, the control surface mounting member is provided with a first fixing hole and a second fixing hole corresponding to the first fixing shaft and the second fixing shaft, respectively.
Optionally, the control surface mount comprises a vertical tail, a horizontal tail, a wing aileron mounting structure and a wing flap mounting structure.
Optionally, the rudder body is of an L-shaped structure, and a groove is formed at a corner of the L-shaped structure;
the first fixed shaft is arranged in the groove, and the second fixed shaft is arranged at one end, far away from the groove, of the rudder body.
Optionally, the rudder body comprises a first skin, a second skin, a first rib plate and a second rib plate;
the first skin and the second skin are both of L-shaped structures, and the edge of the first skin is connected with the edge of the second skin to form the rudder body;
the first rib plate is used for connecting the first skin and the second skin so as to form a mounting surface of the first fixing shaft in the groove;
the second rib plate is used for connecting the first skin and the second skin so as to form a mounting surface of the second fixing shaft at one end, far away from the groove, of the rudder body.
Optionally, a first fixing portion is disposed at a first end of the first fixing shaft, and the first fixing portion is fixed to the inner side of the first rib plate;
the first ribbed plate is provided with a through hole, and the second end of the first fixing shaft penetrates through the through hole to the outer side of the first ribbed plate.
Optionally, a second fixing portion is disposed at a first end of the second fixing shaft, and the second fixing portion is fixed to an outer side of the second rib plate.
Optionally, the first fixing portion is fixed to the inner side of the first rib plate by gluing.
Optionally, the second fixing portion is fixed to an outer side of the second rib by a screw.
The utility model also discloses an aircraft comprising any one of the control surfaces described above.
By adopting the technical scheme, the control surface and the airplane have the following beneficial effects:
the control surface and the airplane realize the connection of the control surface and the airplane body structure through the first fixed shaft and the second fixed shaft, the number of metal joints is reduced, the important control function of the control surface as the control surface is met, and the structural efficiency is improved; openings on the vertical fin skin and the control surface skin are avoided, and the pneumatic efficiency is improved; and has the advantages of convenient disassembly and assembly, light weight and the like.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic illustration of an alternative control surface in accordance with an embodiment of the present disclosure;
FIG. 2 is an exploded view of an alternative control surface in accordance with an embodiment of the present application;
FIG. 3 is a schematic view of an alternative first stationary shaft assembly according to an embodiment of the present application;
FIG. 4 is a schematic view of an alternative second stationary shaft assembly according to an embodiment of the present application;
FIG. 5 is a schematic view of an alternative embodiment of the present invention showing the connection of a first stationary shaft to a vertical tail;
FIG. 6 is a schematic view of an alternative second stationary shaft to vertical tail according to an embodiment of the present invention;
fig. 7 is a schematic view of an alternative control surface applied to a vertical tail according to an embodiment of the present invention.
The following is a supplementary description of the drawings:
1-a rudder body; 101-a first skin; 102-a second skin; 103-a first rib; 104-a second rib; 2-a first fixed shaft; 201-a first fixed part; 3-a second fixed shaft; 301-a second stationary part; 4-a groove; 5-vertical tail; 501-a first fixing hole; 502-a second fixation hole; 503-a third rib; 504-fourth rib; 505-a fixed base; 6-control surface steering engine.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is to be understood that the described embodiments are merely exemplary of the utility model, and not restrictive of the full scope of the utility model. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic may be included in at least one implementation of the utility model. In the description of the present invention, it is to be understood that the terms "upper", "lower", "top", "bottom", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. Moreover, the terms "first," "second," and the like 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 capable of operation in sequences other than those illustrated or described herein.
Referring to fig. 1 and 2, fig. 1 is a schematic view of an alternative control surface according to an embodiment of the present application, and in fig. 1, a rudder body 1, a first fixed shaft 2 and a second fixed shaft 3 are included; the first fixed shaft 2 is arranged at the first end of the rudder body 1, the second fixed shaft 3 is arranged at the second end of the rudder body 1, and the axes of the first fixed shaft 2 and the second fixed shaft 3 are consistent; the rudder body 1 is movably fixed to the control surface mount by the first and second fixed shafts 2 and 3.
As an alternative embodiment, the control surface mounting member may be provided with first and second fixing holes 501 and 502 corresponding to the first and second fixing shafts 2 and 3, respectively, shown in fig. 1.
As an alternative embodiment, the control surface mount includes a vertical tail, a horizontal tail, a wing aileron mounting structure, and a wing flap mounting structure.
As an alternative embodiment, the rudder body 1 shown in fig. 1 is an L-shaped structure, and a groove 4 is provided at a corner of the L-shaped structure; the first fixed shaft 2 is arranged in the groove 4, and the second fixed shaft 3 is arranged at one end of the rudder body 1 far away from the groove 4.
As an alternative embodiment, the rudder body 1 shown in fig. 1 includes a first skin 101, a second skin 102, a first rib 103, and a second rib 104 (shown in conjunction with fig. 2); wherein the first rib 103 is used for connecting the first skin 101 and the second skin 102 to form a mounting surface of the first fixing shaft 2 at the groove 4; the second rib 104 is used for connecting one end of the first skin 101 and one end of the second skin 102 to form a mounting surface of the second fixing shaft 3 at one end of the rudder body 1 far away from the groove 4; the first skin 101 and the second skin 102 are both L-shaped structures, and the edge of the first skin 101 and the edge of the second skin 102 are sequentially connected to form the rudder body 1 shown in fig. 1.
In a specific implementation, a foam core (not shown in the figure) is further arranged between the first skin 101 and the second skin 102, the foam core is manufactured by cutting, laying prepreg or fabric, and foam according to a designed scheme, then heating and curing, trimming and cutting edges after curing to manufacture a required part, the first skin 101 and the second skin 102 both adopt composite fiber materials, and are wrapped on the surface of the foam core to form the rudder body 1, wherein a flanging structure is arranged on the first skin 101 and/or the second skin 102, and the connection between the first skin 101 and the second skin 102 is realized by coating an adhesive on the flanging structure.
As an alternative embodiment, as shown in fig. 3, the first end of the first fixing shaft 2 is provided with a first fixing portion 201, and the first fixing portion 201 is used for fixing the first end of the first fixing shaft 2 to the inner side of the first rib plate 103; first ribbed plate 103 is provided with a through hole, the second end of first fixed axle 2 passes through the through hole to the outside of first ribbed plate 103, and the position of first fixed axle 2 corresponds to groove 4.
In a specific implementation, the first fixing portion 201 and the first rib plate 103 can be connected by gluing, and the structure of the second fixing shaft 3 can be similar to that of the first fixing shaft 2, that is, the first end of the second fixing shaft 3 is glued to the inner side of the second rib plate 104 by arranging a fixing portion, and the second end of the second fixing shaft 3 passes through a preset hole on the second rib plate 104 to the outer side of the second rib plate 104.
As an alternative embodiment, in order to improve the connection strength of the second fixing shaft 3 and avoid the second fixing shaft 3 from falling off due to excessive force during the installation process, the second fixing shaft 3 shown in fig. 1 adopts the structure shown in fig. 4, the first end of the second fixing shaft 3 is provided with a second fixing portion 301, and the second fixing portion 301 is fixed to the outer side of the second rib 104.
Specifically, the second fixing portion 301 is fixed to the outer side of the second rib 104 by a screw manner.
Fig. 5 to 7 illustrate the application of the control surface of the embodiment of the present application to the vertical tail wing, as shown in fig. 5, a first fixing hole 501 corresponding to the first fixing shaft 2 is formed on a third rib 503 on the vertical tail wing, when mounting, the first fixing shaft 2 is inserted into the first fixing hole 501, and then a cotter pin is inserted into the groove 4 to lock the extending end of the first fixing shaft 2; as shown in fig. 6, a fixing base 505 is provided on the outer side of the fourth rib 504 on the vertical rear wing, a second fixing hole 502 corresponding to the second fixing shaft 3 is provided on the fixing base 505, after the first fixing shaft 2 is installed, the second fixing shaft 3 is inserted into the second fixing hole and inserted into the second fixing hole 502, and then a cotter pin is inserted to lock the second fixing shaft 3, thereby completing the installation of the control surface on the vertical rear wing.
In a specific implementation, the installation of the control surface steering engine 6 is further included before the installation of the control surface, as shown in fig. 6, the control surface steering engine 6 is fixed on the inner side of the fourth rib plate 504; the vertical tail after installation of the control surface is shown in figure 7.
Embodiments of the present application also provide an aircraft including any of the control surfaces described above.
The control surface and the airplane have the following beneficial effects:
the control surface and the airplane of the embodiment of the application realize the connection of the control surface and the airplane body structure through the first fixed shaft and the second fixed shaft, so that the number of metal joints is reduced, the important control function of the control surface is met, and the structure efficiency is improved; openings on the wing surface skin and the control surface skin are avoided, and the pneumatic efficiency is improved; and has the advantages of convenient disassembly and assembly, light weight and the like.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A control surface is characterized by comprising a rudder body (1), a first fixed shaft (2) and a second fixed shaft (3);
the first fixed shaft (2) is arranged at the first end of the rudder body (1), the second fixed shaft (3) is arranged at the second end of the rudder body (1), and the axle centers of the first fixed shaft (2) and the second fixed shaft (3) are consistent;
the rudder body (1) is movably fixed to a control surface mounting member by the first fixed shaft (2) and the second fixed shaft (3).
2. Control surface according to claim 1, characterized in that the mounting is provided with a first and a second fixing hole corresponding to the first and second fixing axis (2, 3), respectively.
3. The control surface of claim 2, wherein the control surface mount includes, but is not limited to, a vertical tail, a horizontal tail, a wing aileron mounting structure, and a wing flap mounting structure.
4. Control surface according to claim 1, characterized in that the rudder body (1) is an L-shaped structure, and that the corners of the L-shaped structure are provided with grooves (4);
the first fixing shaft (2) is arranged in the groove (4), and the second fixing shaft (3) is arranged at one end, far away from the groove (4), of the rudder body (1).
5. Control surface according to claim 4, characterized in that the rudder body (1) comprises a first skin (101), a second skin (102), a first rib (103) and a second rib (104);
the first skin (101) and the second skin (102) are both L-shaped structures, and the edge of the first skin (101) is connected with the edge of the second skin (102) to form the rudder body (1);
the first rib plate (103) is used for connecting the first skin (101) and the second skin (102) to form a mounting surface of the first fixing shaft (2) in the groove (4);
the second rib plate (104) is used for connecting the first skin (101) and the second skin (102) so as to form a mounting surface of the second fixing shaft (3) at one end of the rudder body (1) far away from the groove (4).
6. The control surface according to claim 5, characterized in that the first end of the first fixed shaft (2) is provided with a first fixing part (201), the first fixing part (201) being fixed to the inner side of the first rib (103);
the first ribbed plate (103) is provided with a through hole, and the second end of the first fixing shaft (2) penetrates through the through hole to the outer side of the first ribbed plate (103).
7. Control surface according to claim 6, characterized in that the first end of the second fixed axle (3) is provided with a second fixed part (301), which second fixed part (301) is fixed to the outside of the second rib (104).
8. Control surface according to claim 6, characterized in that the first fixing part (201) is fixed to the inner side of the first rib (103) by means of gluing.
9. Control surface according to claim 7, characterized in that the second fixing part (301) is fixed to the outside of the second rib (104) by means of a screw connection.
10. An aircraft comprising a control surface as claimed in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120327300.6U CN216186003U (en) | 2021-02-03 | 2021-02-03 | Control surface and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120327300.6U CN216186003U (en) | 2021-02-03 | 2021-02-03 | Control surface and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216186003U true CN216186003U (en) | 2022-04-05 |
Family
ID=80859277
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120327300.6U Active CN216186003U (en) | 2021-02-03 | 2021-02-03 | Control surface and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216186003U (en) |
-
2021
- 2021-02-03 CN CN202120327300.6U patent/CN216186003U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230706 Address after: Building 4, No. 200 Tianfu Fifth Street, Chengdu High tech Zone, China (Sichuan) Pilot Free Trade Zone, Chengdu City, Sichuan Province, 610000, 6th floor, Zone A Patentee after: Chengdu wofeitianyu Technology Co.,Ltd. Patentee after: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. Address before: 430090 No.100, Weihu Road, Shamao street, Hannan District, Wuhan City, Hubei Province Patentee before: Hubei Jili Taili Flying Car Co.,Ltd. Patentee before: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. |