CN218892684U - Aircraft and control surface hinge structure thereof - Google Patents
Aircraft and control surface hinge structure thereof Download PDFInfo
- Publication number
- CN218892684U CN218892684U CN202222816701.5U CN202222816701U CN218892684U CN 218892684 U CN218892684 U CN 218892684U CN 202222816701 U CN202222816701 U CN 202222816701U CN 218892684 U CN218892684 U CN 218892684U
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- Prior art keywords
- stabilizer
- hinge
- control surface
- movable
- movable surface
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- 239000003381 stabilizer Substances 0.000 claims abstract description 62
- 238000009434 installation Methods 0.000 abstract description 15
- 239000002131 composite material Substances 0.000 abstract description 6
- 230000000694 effects Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The application relates to the technical field of aircrafts and discloses an aircraft and a control surface hinge structure thereof. The aircraft control surface hinge structure comprises a stabilizer hinge and a movable surface hinge which are oppositely arranged, wherein the stabilizer hinge comprises a stabilizer connecting part connected with an aircraft body, the movable surface hinge comprises a movable surface connecting part connected with a control surface, the stabilizer connecting part is sleeved with the movable surface connecting part to be connected and can rotate and stretch in the width direction of the control surface, and the stabilizer connecting part and the movable surface connecting part can generate relative movement in the length direction of the control surface. The stabilizer hinge and the movable surface hinge can move left and right, so that the installation precision of the control surface and the fuselage during the matching installation is relaxed, and the problem of assembly installation caused by the production dimensional error of the composite material wing is avoided.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to an aircraft and a control surface hinge structure thereof.
Background
At present, most parts of an aircraft are produced by composite materials, and extremely accurate design precision of the composite materials cannot be guaranteed due to the special properties of the composite materials, so that design redundancy on a part connecting hinge is small, and assembly installation is often caused by dimensional errors in part production. For example, the hinge between the fuselage and the control surface may not be assembled properly due to dimensional errors, so it is highly desirable to find a hinge with design redundancy for connecting the fuselage and the control surface.
Disclosure of Invention
The utility model aims at providing an aircraft and control surface hinge structure thereof, this application stabilizer hinge can control the activity with the movable surface hinge, has relaxed the installation accuracy when control surface and fuselage are to joining in marriage the installation, avoids leading to the subassembly installation to go wrong because of combined material wing production size error.
In order to solve the technical problem, the application provides an aircraft control surface hinge structure, including stabilizer hinge and the movable surface hinge of relative setting, stabilizer hinge include with the stabilizer connecting portion that aircraft fuselage is connected, the movable surface hinge include with the movable surface connecting portion that the control surface is connected, stabilizer connecting portion with movable surface connecting portion cover is established and is connected and can rotate relatively, wherein stabilizer connecting portion with movable surface connecting portion can be in the control surface length direction produces relative activity.
Preferably, the movable surface connecting part comprises a pair of movable surface supporting arms and a connecting rod connected with the pair of movable surface supporting arms, the stabilizer connecting part comprises a supporting arm, a sleeve hole is formed in the end portion of the supporting arm, and the stabilizer supporting arm is sleeved on the connecting rod through the sleeve hole.
Preferably, the stabilizer support arm can slide on the connecting rod along the length direction of the control surface.
Preferably, the joint bearing is arranged in the sleeve hole, the joint bearing comprises an inner spherical surface part and an outer spherical surface part, the outer spherical surface part is connected with the stabilizer support arm, the inner spherical surface part is sleeved and connected on the connecting rod, and the inner spherical surface part and the outer spherical surface part can rotate at any angle.
Preferably, the knuckle bearing is in interference connection with the sleeved hole.
Preferably, a buffer piece sleeved on the connecting rod is further arranged between the knuckle bearing and the pair of movable surface supporting arms.
Preferably, the stabilizer connecting portion is connected to a stabilizer mounting seat, the stabilizer mounting seat is connected to the aircraft fuselage, the movable surface connecting portion is connected to a movable surface mounting seat, and the movable surface mounting seat is connected to the control surface.
Preferably, the stabilizer mounting seat and the movable surface mounting seat are respectively provided with a plurality of mounting holes.
Preferably, the connecting rod is a fastening bolt, and an internal thread is provided in a connecting through hole of at least one of the pair of movable surface supporting arms 201.
The stabilizer hinge and the movable surface hinge can move left and right, so that the installation precision of the control surface and the fuselage during the matching installation is relaxed, and the problem of assembly installation caused by the production dimensional error of the composite material wing is avoided.
Drawings
FIG. 1 is a schematic view of a connection structure between an aircraft fuselage and a control surface according to an embodiment of the present application;
FIG. 2 shows an enlarged view of the position A in FIG. 1;
FIG. 3 is a schematic view of a control surface hinge structure according to an embodiment of the present disclosure;
FIG. 4 is an exploded view of a control surface hinge structure according to an embodiment of the present disclosure;
FIG. 5 is a schematic view of a joint bearing according to an embodiment of the present application;
fig. 6 shows a cross-sectional view of a knuckle bearing in accordance with an embodiment of the present application.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, embodiments of the present utility model will be described in detail below with reference to the accompanying drawings. However, those of ordinary skill in the art will understand that in various embodiments of the present utility model, numerous technical details have been set forth in order to provide a better understanding of the present application. However, the technical solutions claimed in the claims of the present application can be realized without these technical details and various changes and modifications based on the following embodiments.
Throughout the specification and claims, unless the context requires otherwise, the word "comprise" and variations such as "comprises" and "comprising" will be understood to be open-ended, meaning of inclusion, i.e. to be interpreted to mean "including, but not limited to.
The following detailed description of various embodiments of the present utility model will be provided in connection with the accompanying drawings to provide a clearer understanding of the objects, features and advantages of the present utility model. It should be understood that the embodiments shown in the drawings are not intended to limit the scope of the utility model, but rather are merely illustrative of the true spirit of the utility model.
Reference throughout this specification to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment. Thus, appearances of the phrases "in one embodiment" or "in an embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
As used in this specification and the appended claims, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. It should be noted that the term "or" is generally employed in its sense including "and/or" unless the context clearly dictates otherwise.
In the following description, for the purposes of clarity of presentation of the structure and manner of operation of the present utility model, the description will be made with the aid of directional terms, but such terms as "forward," "rearward," "left," "right," "outward," "inner," "outward," "inward," "upper," "lower," etc. are to be construed as convenience, and are not to be limiting.
The first embodiment of the application provides an aircraft control surface hinge structure, which comprises a stabilizer hinge 1 and a movable surface hinge 2, wherein the stabilizer hinge 1 and the movable surface hinge 2 are oppositely arranged. The stabilizer hinge 1 comprises a stabilizer connecting part 10 connected with the aircraft body 3, the movable surface hinge 2 comprises a movable surface connecting part 20 connected with the control surface 4, the stabilizer connecting part 10 is sleeved with the movable surface connecting part 20 and can rotate and stretch in the width direction of the control surface 4, and the stabilizer connecting part 10 and the movable surface connecting part 20 can relatively move in the length direction of the control surface 4.
Specifically, as shown in fig. 1 to 4, the stabilizer hinge 1 includes a stabilizer link 10 and a stabilizer mount 11, the stabilizer link 10 is connected to the stabilizer mount 11, and the stabilizer mount 11 is connected to the aircraft fuselage 3. The movable surface hinge 2 comprises a movable surface connecting part 20 and a movable surface mounting seat 21, wherein the movable surface connecting part 20 is connected to the movable surface mounting seat 21, and the movable surface mounting seat 21 is connected to the control surface 4.
The movable surface connecting section 20 includes a pair of movable surface support arms 201 and a connecting rod 202, and the connecting rod 202 connects the two movable surface support arms 201. The connecting rod 202 is preferably a fastening bolt, and the ends of the pair of movable surface supporting arms 201 are provided with connecting through holes, wherein the connecting through holes of at least one movable surface supporting arm 201 are preferably provided with internal threads, and the fastening bolts can be mutually connected through the internal threads. The stabilizer connecting part 10 comprises a stabilizer supporting arm 101, a sleeve hole 102 is arranged at the end 101 of the stabilizer supporting arm, the stabilizer supporting arm 101 is sleeved on a connecting rod 202 through the sleeve hole 102, and the stabilizer supporting arm 101 can rotate around the connecting rod 202 and a movable surface supporting arm 201 relatively, so that the stabilizer connecting part 10 and the movable surface connecting part 20 can rotate and stretch in the width direction of the control surface 4. The width of the stabilizer support arm 10 in the direction of the length of the control surface is smaller than the distance between the two movable surface support arms 201, so that the stabilizer support arm 101 can slide or swing on the connecting rod 202 along the direction of the length of the control surface.
Further, as shown in fig. 5 and 6, a joint bearing 103 is disposed in the sleeve hole 102, the joint bearing 103 includes an inner spherical surface portion 103a and an outer spherical surface portion 103b, the outer spherical surface portion 103b is connected with the stabilizer support arm 101, the inner spherical surface portion 103a is sleeved on the connecting rod 202, and the inner spherical surface portion 103a and the outer spherical surface portion 103b can rotate at any angle. So that the stabilizer support arm 101 can more conveniently perform the movement on the connection rod 202 of the movable surface connection part 20.
Further, a buffer member 104 sleeved on the connecting rod 202 is further arranged between the joint bearing 103 and the pair of movable surface supporting arms 20, and the buffer member 104 is preferably a gasket so as to prevent friction between the joint bearing 103 and the two movable surface supporting arms 201.
In addition, a plurality of mounting holes 5 are respectively arranged on the stabilizer mounting seat 11 and the movable surface mounting seat 22 for respectively fixing the stabilizer mounting seat 11 and the movable surface mounting seat 22 to the machine body and the control surface.
The stabilizer hinge and the movable surface hinge can move left and right, so that the installation precision of the control surface and the fuselage during the matching installation is relaxed, and the problem of assembly installation caused by the production dimensional error of the composite material wing is avoided.
The second embodiment of the application provides an aircraft, and the aircraft includes control surface 4, and a plurality of aircraft control surface hinge structures of connecting aircraft fuselage 3 and control surface 4, and the aircraft control surface hinge structure of this application aircraft because of stabilizer hinge and movable surface hinge can control the activity, has relaxed the control surface and the installation accuracy when fuselage is mated and is installed, avoids leading to the subassembly installation to appear problem because of combined material wing production size error
The foregoing embodiments are merely illustrative of the principles of the present application and their effectiveness, and are not intended to limit the application. Modifications and variations may be made to the above-described embodiments by those of ordinary skill in the art without departing from the spirit and scope of the present application. Accordingly, it is intended that all equivalent modifications and variations which may be accomplished by persons skilled in the art without departing from the spirit and technical spirit of the disclosure be covered by the claims of this application.
Claims (10)
1. A control surface hinge structure for an aircraft, the aircraft including a fuselage, comprising: the stabilizer hinge (1) and the movable surface hinge (2) are oppositely arranged, the stabilizer hinge (1) comprises a stabilizer connecting portion (10) connected with the machine body (3), the movable surface hinge (2) comprises a movable surface connecting portion (20) connected with the control surface (4), the stabilizer connecting portion (10) is sleeved with the movable surface connecting portion (20) to be connected and can rotate and stretch in the width direction of the control surface (4), and the stabilizer connecting portion (10) and the movable surface connecting portion (20) can move relatively in the length direction of the control surface (4).
2. The rudder surface hinge structure according to claim 1, wherein the movable surface connecting portion (20) includes a pair of movable surface supporting arms (201) and a connecting rod (202) connecting the pair of movable surface supporting arms (201), the stabilizer connecting portion (10) includes a stabilizer supporting arm (101), a sleeve hole (102) is provided at an end portion of the stabilizer supporting arm (101), and the stabilizer supporting arm (101) is sleeved on the connecting rod (202) through the sleeve hole (102).
3. The rudder surface hinge structure according to claim 2, characterized in that the stabilizer support arm (101) is slidable on the connecting rod (202) in the rudder surface length direction.
4. The control surface hinge structure according to claim 2, wherein a joint bearing (103) is disposed in the sleeve hole (102), the joint bearing (103) includes an inner spherical surface portion (103 a) and an outer spherical surface portion (103 b), the outer spherical surface portion (103 b) is connected with the stabilizer support arm (101), the inner spherical surface portion (103 a) is sleeved and connected to the connecting rod (202), and the inner spherical surface portion (103 a) and the outer spherical surface portion (103 b) can rotate at any angle.
5. The control surface hinge structure according to claim 4, characterized in that the knuckle bearing (103) is interference-connected in the sleeved hole (102).
6. The control surface hinge structure according to claim 4, wherein a buffer member (104) sleeved on the connecting rod (202) is further provided between the knuckle bearing (103) and the pair of movable surface supporting arms (201).
7. The rudder surface hinge structure according to claim 1, wherein the stabilizer connecting portion 10 is connected to a stabilizer mounting seat (11), the stabilizer mounting seat (11) is connected to the aircraft fuselage (3), the movable surface connecting portion (20) is connected to a movable surface mounting seat (21), and the movable surface mounting seat (21) is connected to the rudder surface (4).
8. The control surface hinge structure according to claim 7, wherein a plurality of mounting holes (5) are respectively provided on the stabilizer mounting seat (11) and the movable surface mounting seat (21).
9. The control surface hinge structure according to claim 2, wherein the connecting rod (202) is a fastening bolt, and an internal thread is provided in a connecting through hole of at least one of the pair of movable surface supporting arms (201).
10. An aircraft characterized by comprising a control surface (4) and a plurality of control surface hinge structures according to any one of claims 1-9 connecting the aircraft fuselage (3) and the control surface (4).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222816701.5U CN218892684U (en) | 2022-10-25 | 2022-10-25 | Aircraft and control surface hinge structure thereof |
| PCT/CN2023/121452 WO2024087990A1 (en) | 2022-10-25 | 2023-09-26 | Aircraft and control surface hinge structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222816701.5U CN218892684U (en) | 2022-10-25 | 2022-10-25 | Aircraft and control surface hinge structure thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218892684U true CN218892684U (en) | 2023-04-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222816701.5U Active CN218892684U (en) | 2022-10-25 | 2022-10-25 | Aircraft and control surface hinge structure thereof |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN218892684U (en) |
| WO (1) | WO2024087990A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024087990A1 (en) * | 2022-10-25 | 2024-05-02 | 峰飞航空科技(昆山)有限公司 | Aircraft and control surface hinge structure thereof |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2923460B1 (en) * | 2007-11-12 | 2010-05-14 | Snecma | ASSEMBLING A SUSPENSION MEMBER OF A TURBOMOTEUR |
| CN204775995U (en) * | 2015-06-23 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Elevator actuator antihunting control structure |
| CN206063785U (en) * | 2016-08-26 | 2017-04-05 | 汕头市欧兰斯模型科技有限公司 | A kind of articulated link mechanism and aircraft of aircraft |
| CN108082449B (en) * | 2018-03-06 | 2022-06-10 | 中航通飞华南飞机工业有限公司 | Large aircraft control surface suspension structure |
| CN112173072A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Control surface control mechanism of high-speed helicopter |
| CN217348211U (en) * | 2022-05-18 | 2022-09-02 | 中航沈飞民用飞机有限责任公司 | Hinge clamping and connecting device |
| CN218892684U (en) * | 2022-10-25 | 2023-04-21 | 峰飞航空科技(昆山)有限公司 | Aircraft and control surface hinge structure thereof |
-
2022
- 2022-10-25 CN CN202222816701.5U patent/CN218892684U/en active Active
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2023
- 2023-09-26 WO PCT/CN2023/121452 patent/WO2024087990A1/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024087990A1 (en) * | 2022-10-25 | 2024-05-02 | 峰飞航空科技(昆山)有限公司 | Aircraft and control surface hinge structure thereof |
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| Publication number | Publication date |
|---|---|
| WO2024087990A1 (en) | 2024-05-02 |
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