CN115384757B - Flaperon actuating mechanism and wing structure - Google Patents
Flaperon actuating mechanism and wing structure Download PDFInfo
- Publication number
- CN115384757B CN115384757B CN202211342853.4A CN202211342853A CN115384757B CN 115384757 B CN115384757 B CN 115384757B CN 202211342853 A CN202211342853 A CN 202211342853A CN 115384757 B CN115384757 B CN 115384757B
- Authority
- CN
- China
- Prior art keywords
- flaperon
- spoiler
- connecting rod
- flap
- hinged
- 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/04—Adjustable control surfaces or members, e.g. rudders with compound dependent movements
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
-
- 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
- B64C2009/143—Adjustable control surfaces or members, e.g. rudders forming slots comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps
-
- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/80—Technologies aiming to reduce greenhouse gasses emissions common to all road transportation technologies
- Y02T10/82—Elements for improving aerodynamics
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
- Transmission Devices (AREA)
Abstract
The application discloses flap actuation mechanism and wing structure, this flap actuation mechanism includes: the spoiler comprises a fixed bracket, a spoiler, a flaperon and a connecting rod assembly; the spoiler comprises a fixed support, a spoiler, a flap, a wing rear beam, a spoiler and a spoiler, wherein the fixed support is used for being installed on the wing rear beam, and the spoiler is positioned above the flap; the first end of the spoiler is hinged with the upper end of the fixed support, and the first end of the flap wing is hinged with the lower end of the fixed support; two ends of the connecting rod assembly are respectively hinged with the second end of the spoiler and the second end of the flaperon, so that the flaperon can drive the spoiler to synchronously rotate in a fixed axis mode through the connecting rod assembly when the flaperon rotates in a fixed axis mode. The application solves the problems that in the related art, the naturally formed seam between the deflected flaperon and the fixed trailing edge of the wing can influence the lift increasing effect of the flaperon, and the flaperon has a complex actuating mechanism structure, poor reliability and high maintenance cost, and is difficult to apply to high-frequency and long-time flight.
Description
Technical Field
The application relates to the technical field of wing structures, in particular to a flaperon actuating mechanism and a wing structure.
Background
The flaperon of the airplane can be used as a flap and can also be used as an aileron. And as flaps when the flaperons on both sides of the wing are deflected downward, and as ailerons when the flaperons on both sides of the wing are deflected in opposite directions.
Traditional flaperons generally make simple fixed-axis deflection motions. When the flaperon deflects, a seam is formed between the flaperon and the upper wing surface of the wing trailing edge, and for the seam, the common practice at home and abroad is that the deflected flaperon and the wing fixed trailing edge naturally form the seam. The naturally formed slot can influence the airflow at the trailing edge of the wing, and further influence the high lift effect of the flaperon.
Moreover, the flap of the airplane has very high actuation frequency, and a single flying frame needs to perform at least hundreds of actuations, so that high requirements are put on the reliability of an actuation mechanism. The flaperon actuating mechanism in the related art is only suitable for the field of unmanned aerial vehicles with small flying times and flying time, has complex actuating mechanism structure, poor reliability (blocking risk exists), high maintenance cost and is difficult to be applied to airplanes flying at high frequency and for long time.
Disclosure of Invention
The main purpose of the present application is to provide an actuation mechanism for flaperons and a wing structure, so as to solve the problem that a naturally formed seam between the deflected flaperons and the fixed trailing edge of the wing in the related art may affect the lift-increasing effect of the flaperons, and the actuation mechanism for flaperons is complex in structure, poor in reliability, high in maintenance cost, and difficult to apply to high-frequency and long-time flight.
In order to achieve the above object, the present application provides a flap actuating mechanism including: the spoiler comprises a fixed bracket, a spoiler, a flaperon and a connecting rod assembly; wherein, the first and the second end of the pipe are connected with each other,
the fixed support is used for being installed on a rear wing beam, and the spoiler is located above the flaperon;
the first end of the spoiler is hinged with the upper end of the fixed support, and the first end of the flap wing is hinged with the lower end of the fixed support;
two ends of the connecting rod assembly are respectively hinged with the second end of the spoiler and the second end of the flaperon, so that the flaperon can drive the spoiler to synchronously rotate in a fixed axis mode through the connecting rod assembly when the flaperon rotates in a fixed axis mode.
Further, the connecting rod assembly comprises at least one driving connecting rod, and two ends of the driving connecting rod are respectively hinged with the second end of the spoiler and the second end of the flaperon.
Further, the connecting rod assembly comprises an adapter, a spoiler connecting rod and a flaperon connecting rod;
the adapter is hinged to the middle of the fixed support, the upper end of the spoiler connecting rod is hinged to the second end of the spoiler, the right end of the flap connecting rod is hinged to the flap, and the lower end of the spoiler connecting rod and the left end of the flap connecting rod are hinged to the adapter through the same rotating shaft.
Further, the connecting rod assembly comprises an adapter, a spoiler connecting rod and a flaperon connecting rod;
the adapter is hinged to the middle part of the fixed support, the upper end of the spoiler connecting rod is hinged to the second end of the spoiler, and the lower end of the spoiler connecting rod is hinged to the lower end of the adapter;
the left end of the flaperon connecting rod is hinged with the upper end of the adapter, and the right end of the flaperon connecting rod is hinged with the flaperon.
Furthermore, the spoiler connecting rod and the flaperon connecting rod are arranged to be in special-shaped structures.
Furthermore, the spoiler connecting rod is arranged to be S-shaped, and the flaperon connecting rod is arranged to be arc-shaped.
Furthermore, the spoiler connecting rod comprises a first arc-shaped portion and a second arc-shaped portion which are distributed up and down, the radian of the first arc-shaped portion is larger than that of the second arc-shaped portion, the first arc-shaped portion is of a structure protruding towards the fixed support, and the flaperon corresponds to the first arc-shaped portion.
Further, when the flaperon is at the initial position of rotation, one end of the spoiler far away from the fixed bracket is lapped on the upper end of the flaperon.
Furthermore, the lower end of the spoiler connecting rod and the left end of the flaperon connecting rod are respectively positioned at two sides of the adaptor.
Furthermore, the adaptor is triangular, the vertex of the middle of the adaptor is hinged to the fixed support, and the vertexes of the two ends of the adaptor are respectively hinged to the spoiler connecting rod and the flaperon connecting rod.
According to another aspect of the present application, there is provided a wing structure including the flap actuating mechanism described above.
In the embodiment of the application, the fixing bracket, the spoiler, the flaperon and the connecting rod assembly are arranged; the spoiler comprises a fixed support, a spoiler, a wing rear beam, a spoiler and a flap, wherein the fixed support is used for being installed on the wing rear beam, and the spoiler is positioned above the flaperon; the first end of the spoiler is hinged with the upper end of the fixed support, and the first end of the flap wing is hinged with the lower end of the fixed support; the two ends of the connecting rod assembly are respectively hinged with the second end of the spoiler and the second end of the flaperon, so that the flaperon can drive the spoiler to synchronously rotate in a fixed axis mode through the connecting rod assembly when rotating in the fixed axis mode, the purpose that the spoiler driven by the connecting rod assembly is added above the flaperon is achieved, when the flaperon is used as a flap, the spoiler improves airflow at the rear edge of a wing, when the flaperon is used as a flap, the connecting rod assembly achieves the purpose of achieving the cooperative action of the flaperon and the spoiler, the technical effect that the lifting effect of the flaperon is obviously improved compared with that of the traditional flaperon is achieved, the efficiency of the flaperon is improved, the connecting rod assembly is adopted as a transmission structure, compared with the traditional guide rail adopted as the transmission structure, the technical effect of higher reliability and better maintenance economy is achieved, and the problem that the lifting effect of the flaperon is influenced by a naturally formed between the deflected flaperon and the wing fixed rear edge of the flaperon in the related technology is solved, and the actuating mechanism structure of the flaperon is complex, poor in reliability, high in maintenance cost and high-frequency flight time.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:
FIG. 1 is a schematic structural diagram according to an embodiment of the present application;
FIG. 2 is a schematic structural view of a flaperon deflected by 0 ° according to an embodiment of the present application;
FIG. 3 is a schematic view of a 25 deflection of the flaperon according to an embodiment of the present application;
FIG. 4 is a schematic view of a flap deflected 30 according to an embodiment of the present application;
FIG. 5 is a schematic view of a flap deflected 50 according to an embodiment of the present application;
the spoiler driving mechanism comprises a fixing support 1, a spoiler 2, a flaperon 3, a flaperon connecting rod 4, an adapter 5, a spoiler connecting rod 6, a connecting rod assembly 14 and a driving connecting rod 15.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used.
In this application, the terms "upper", "lower", "inside", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
Furthermore, the terms "disposed," "provided," "connected," "secured," and the like are to be construed broadly. For example, "connected" may be a fixed connection, a detachable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In addition, the term "plurality" shall mean two as well as more than two.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Traditional flaperons generally make simple fixed-axis deflection motions. When the flaperon deflects, a seam is formed between the flaperon and the upper wing surface of the wing trailing edge, and for the seam, the common practice at home and abroad is that the deflected flaperon and the wing fixed trailing edge naturally form the seam. The naturally formed slot can influence the airflow at the trailing edge of the wing, and further influence the high lift effect of the flaperon.
Moreover, the flap of the airplane has very high actuation frequency, and a single flying frame needs to perform at least hundreds of actuations, so that high requirements are put on the reliability of an actuation mechanism. The flaperon actuating mechanism in the related art is only suitable for the field of unmanned aerial vehicles with small flying times and flying time, has complex actuating mechanism structure, poor reliability (blocking risk exists), high maintenance cost and is difficult to be applied to airplanes flying at high frequency and for long time.
To solve the above technical problem, as shown in fig. 1 to 5, an embodiment of the present application provides a flaperon actuating mechanism, including: the spoiler comprises a fixed bracket 1, a spoiler 2, a flaperon 3 and a connecting rod assembly 14; wherein the content of the first and second substances,
the fixed support 1 is used for being installed on a rear wing beam, and the spoiler 2 is positioned above the flaperon 3;
the first end of the spoiler 2 is hinged with the upper end of the fixed support 1 through a rotating shaft 7, and the first end of the flaperon 3 is hinged with the lower end of the fixed support 1 through a rotating shaft 10;
one end of the connecting rod assembly 14 is hinged with the second end of the spoiler 2, and the other end of the connecting rod assembly 14 is hinged with the second end of the flap 3, so that the flap 3 can drive the spoiler 2 to synchronously rotate in a fixed axis manner through the connecting rod assembly 14 when rotating in a fixed axis manner.
In the embodiment, the relative position relationship between the flaperon 3 and the spoiler 2 at different angles obtained by aerodynamic analysis is taken as a design target, considering that the actuating mechanism is positioned at the trailing edge of the wing, the size of the actuating mechanism is relatively thin, the whole actuating mechanism is difficult to be completely placed in the wing, and considering the interference of attachments on the surface of the wing on the wing comprehensively, the exposed part of the actuating mechanism is positioned below the wing, and the rest part of the actuating mechanism is embedded into the wing. The flaperon 3 in the mechanism is powered by a steering engine to achieve the purpose of deflecting the flaperon 3.
In the embodiment, the left side plane of the fixed support 1 is installed on the wing back beam through a bolt and is used as a fixed part of the whole actuating mechanism, the upper contour of the fixed support is positioned in the wing skin, and the lower contour of the fixed support extends out of the wing lower skin. The spoiler 2 is hinged at the upper end of the fixed support 1 through a rotating shaft 7, the flaperon 3 is hinged at the lower end of the fixed support 1 through a rotating shaft 10, and the spoiler 2 is positioned above the flaperon 3.
The flaperon 3 is an integrated structure of a flaperon bracket and a flaperon end rib. The steering engine is installed between the front and rear beams in the wing, and the flaperon 3 is pushed to rotate through the steering engine, so that the actuation of the whole flaperon actuating mechanism is realized. In the embodiment, the spoiler 2 and the flaperon 3 can rotate around the corresponding hinge shaft in a fixed axis manner, the flaperon 3 as a driving link can be actively driven to rotate by a steering engine, and the flaperon 3 is connected with the spoiler 2 through the connecting rod assembly 14, so that the flaperon 3 can drive the spoiler 2 to synchronously rotate in a fixed axis manner through the connecting rod assembly 14 when rotating in a fixed axis manner.
According to actual conditions, the rotation angle of the flap 3 can be different from the rotation angle of the spoiler 2, the rotation angle of the flap 3 is larger than the rotation angle of the spoiler 2 in practical applications, and the specific rotation angle can be realized by adjusting the structure and position of the link assembly 14, the connection position of the flap 3 and the fixed bracket 1, and the connection position of the spoiler 2 and the fixed bracket 1 according to requirements. In the embodiment, because the spoiler 2 is located above the flaperon 3, the air flow at the trailing edge of the wing can be improved by the spoiler 2 in the rotation process of the flaperon 3, the lift increasing effect is obviously improved compared with the traditional flaperon 3, and the efficiency of the flaperon 3 is improved. In the actuating process, the flaperon 3 is used as a prime mover to drive the spoiler 2 to move through the connecting rod assembly 14, and the guide rail structure has higher reliability and better maintenance economy compared with the traditional guide rail structure.
The structure of the link assembly 14 affects the rotation angles of the spoiler 2 and the flaperon 3, and when the link assembly 14 is applied to an environment with a small rotation angle of the spoiler 2 and the flaperon 3, as shown in fig. 1, the link assembly 14 may be configured as a simple single-rod structure, that is, the link assembly 14 includes a driving link 15, the driving link 15 may be a straight rod structure, and two ends of the driving link 15 are respectively hinged to the second end of the spoiler 2 and the second end of the flaperon 3 through rotating shafts.
When the actuating mechanism is applied to an environment with a relatively large rotation angle of the spoiler 2 and the flaperon 3, the structure of the link assembly 14 needs to be further adjusted relative to the above embodiment, specifically, the link assembly 14 in this embodiment includes an adaptor 5, a spoiler link 6 and a flaperon link 4;
the adaptor 5 is hinged to the middle of the fixed support 1, the upper end of the spoiler connecting rod 6 is hinged to the second end of the spoiler 2, the right end of the flap connecting rod 4 is hinged to the flap 3, and the lower end of the spoiler connecting rod 6 and the left end of the flap connecting rod 4 are hinged to the adaptor 5 through the same rotating shaft.
The adaptor 5 serving as a middle connector is hinged to the middle of the fixed support 1 through a rotating shaft, the flaperon connecting rod 4 and the spoiler connecting rod 6 are both hinged to the adaptor 5 and located at the same position on the adaptor 5, and the flaperon 3 can drive the flaperon connecting rod 4 to synchronously rotate when driven to rotate in a fixed axis mode, so that the adaptor 5 and the spoiler connecting rod are driven to move and the spoiler 2 is driven to rotate in the fixed axis mode. In order to avoid interference of the spoiler connecting rod 6 and the flaperon connecting rod 4 in the motion process, the spoiler connecting rod 6 and the flaperon connecting rod 4 are designed to be special-shaped structures of non-straight rods according to the motion process, and the spoiler connecting rod 6 and the flaperon connecting rod 4 can be in various forms as long as the motion process is not interfered with each other.
In order to increase the range of use of the flaperon 3 and the spoiler 2, and therefore to make the range of rotation angles of the flaperon 3 and the spoiler 2 as large as possible, the present embodiment is further improved on the basis of the link assembly 14 as shown in fig. 2 to 5. Specifically, the link assembly 14 in this embodiment also includes an adaptor 5, a spoiler link 6, and a flaperon link 4;
the adaptor 5 is hinged to the middle part of the fixed support 1 through a rotating shaft 12, the upper end of the spoiler connecting rod 6 is hinged to the second end of the spoiler 2 through a rotating shaft 8, and the lower end of the spoiler connecting rod 6 is hinged to the lower end of the adaptor 5 through a rotating shaft 11;
the left end of the flaperon connecting rod 4 is hinged with the upper end of the adaptor 5 through a rotating shaft 13, and the right end of the flaperon connecting rod 4 is hinged with the flaperon 3 through a rotating shaft 9.
The difference between the connecting rod assembly 14 in this embodiment and the connecting rod assembly 14 in the previous embodiment is that the spoiler connecting rod 6 and the flap connecting rod 4 are no longer hinged at the same position of the adaptor 5, but rather the spoiler connecting rod 6 is hinged at the lower end of the adaptor 5, while the flap connecting rod 4 is hinged at the upper end of the adaptor 5, both of which can be hinged by means of a rotating shaft. In the embodiment, the flaperon 3 can drive the flaperon connecting rod 4 to synchronously rotate when driven to rotate in a fixed axis manner, so that the adaptor 5 is driven to rotate, and the adaptor 5 controls the turbulent flow connecting rod to act and drives the turbulent flow plate 2 to rotate in a fixed axis manner. In order to avoid interference between the spoiler connecting rod 6 and the flaperon connecting rod 4 in the movement process, the spoiler connecting rod and the flaperon connecting rod are both arranged to be in special-shaped structures. Specifically, the spoiler connecting rod 6 is set to be S-shaped, the flaperon connecting rod 4 is set to be arc-shaped, and the lower end of the spoiler connecting rod 6 and the left end of the flaperon connecting rod 4 are respectively positioned at two sides of the adaptor 5.
In the embodiment, the installation positions of the spoiler connecting rod 6 and the flaperon connecting rod 4 on the adapter 5 are adjusted, so that the rotation angles of the spoiler 2 and the flaperon 3 can be larger, the flap can be applied to more use environments, and the flap is more flexible to use.
As shown in fig. 2 to 5, when the actuating mechanism in this embodiment employs the above-mentioned link assembly 14, the rotation angles of the flaperon 3 and the spoiler 2 are: the initial position of the flap 3 body of the motive power part is set as 0 degree, when the flap 3 body rotates anticlockwise by 25 degrees around the rotating shaft from the initial position, the flap connecting rod 4 drives the adapter 5 to rotate anticlockwise by 34.7 degrees around the rotating shaft, and at the moment, the adapter 5 drives the spoiler 2 to rotate anticlockwise by 18 degrees around the rotating shaft through the spoiler connecting rod 6; when the flaperon 3 body rotates clockwise 30 degrees around the rotating shaft from the initial position, the adaptor 5 is driven by the flaperon connecting rod 4 to rotate clockwise 27 degrees around the rotating shaft, and at the moment, the adaptor 5 drives the spoiler 2 to rotate clockwise 5 degrees around the rotating shaft by the spoiler connecting rod 6; when the flaperon 3 body rotates clockwise 50 degrees around the rotating shaft from the initial position, the adaptor 5 is driven by the flaperon connecting rod 4 to rotate clockwise 18.3 degrees around the rotating shaft, and at the moment, the adaptor 5 drives the spoiler 2 to rotate clockwise 4.6 degrees around the rotating shaft by the spoiler connecting rod 6.
In order to ensure that interference does not exist between the spoiler connecting rod 6 and the flaperon connecting rod 4 and stable transmission of the spoiler connecting rod 6 and the flaperon connecting rod 4 is ensured, the special-shaped structures of the spoiler connecting rod 6 and the flaperon connecting rod 4 are further designed in the embodiment. Specifically, spoiler connecting rod 6 includes first arc portion and the second arc portion that distributes from top to bottom, and the radian of first arc portion is greater than the radian of second arc portion, and first arc portion is towards fixed bolster 1 convex structure, and flaperon 3 corresponds with first arc portion, and first arc portion can provide more spaces for the rotation of flaperon 3, and the arc of flaperon connecting rod 4 is towards the convex arc of top, can be at the rotatory in-process stable transmission of realization power of flaperon 3.
When the flaperon 3 is at the initial position of rotation, the end of the spoiler 2 away from the fixed bracket 1 is lapped on the upper end of the flaperon 3, thereby facilitating the flow of the air flow. In order to facilitate the adaptor 5 to drive the spoiler 2 to act, the adaptor 5 is triangular in this embodiment, a middle vertex of the adaptor 5 is hinged to the fixed bracket 1, and vertices at two ends of the adaptor 5 are hinged to the spoiler connecting rod 6 and the flaperon connecting rod 4 respectively.
According to another aspect of the present application, there is provided a wing structure including the flap actuating mechanism described above.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (5)
1. A flaperon actuation mechanism, comprising: the spoiler comprises a fixed support, spoilers, flaperons and connecting rod assemblies; wherein the content of the first and second substances,
the fixed support is used for being installed on a rear wing beam, and the spoiler is located above the flaperon;
the first end of the spoiler is hinged with the upper end of the fixed support, and the first end of the flap wing is hinged with the lower end of the fixed support;
two ends of the connecting rod assembly are respectively hinged with the second end of the spoiler and the second end of the flap, so that the flap can drive the spoiler to synchronously rotate in a fixed axis manner through the connecting rod assembly when the flap rotates in a fixed axis manner;
the connecting rod assembly comprises an adapter, a spoiler connecting rod and a flaperon connecting rod;
the adapter is hinged to the middle part of the fixed support, the upper end of the spoiler connecting rod is hinged to the second end of the spoiler, and the lower end of the spoiler connecting rod is hinged to the lower end of the adapter;
the left end of the flaperon connecting rod is hinged with the upper end of the adapter, and the right end of the flaperon connecting rod is hinged with the flaperon;
the spoiler connecting rod is arranged to be S-shaped, and the flap connecting rod is arranged to be arc-shaped;
the spoiler connecting rod comprises a first arc-shaped portion and a second arc-shaped portion which are distributed up and down, the radian of the first arc-shaped portion is larger than that of the second arc-shaped portion, the first arc-shaped portion faces towards the protruding structure of the fixed support, and the flaperon corresponds to the first arc-shaped portion.
2. The flaperon actuation mechanism of claim 1, characterized in that: when the flaperon is at the initial rotation position, one end of the spoiler, which is far away from the fixed bracket, is lapped at the upper end of the flaperon.
3. The flaperon actuation mechanism of claim 2, wherein: the lower end of the spoiler connecting rod and the left end of the flaperon connecting rod are respectively positioned at two sides of the adaptor.
4. The flaperon actuation mechanism of claim 3, wherein: the rotation angles of the flaperon and the spoiler are as follows: the initial position of the flap body of the motive power part is set to be 0 degree, when the flap body rotates anticlockwise by 25 degrees around the rotating shaft from the initial position, the flap connecting rod drives the adaptor to rotate anticlockwise by 34.7 degrees around the rotating shaft, and at the moment, the adaptor 5 drives the spoiler to rotate anticlockwise by 18 degrees around the rotating shaft through the spoiler connecting rod;
when the flaperon body rotates clockwise by 30 degrees around the rotating shaft from the initial position, the switching piece is driven by the flaperon connecting rod to rotate clockwise by 27 degrees around the rotating shaft, and at the moment, the switching piece drives the spoiler to rotate clockwise by 5 degrees around the rotating shaft by the spoiler connecting rod;
when the flaperon body rotates clockwise by 50 degrees around the rotating shaft from the initial position, the connecting rod of the flaperon drives the adapter to rotate clockwise by 18.3 degrees around the rotating shaft, and at the moment, the adapter drives the spoiler to rotate clockwise by 4.6 degrees around the rotating shaft through the connecting rod of the spoiler.
5. A wing structure, comprising the flaperon actuation mechanism of any of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211342853.4A CN115384757B (en) | 2022-10-31 | 2022-10-31 | Flaperon actuating mechanism and wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211342853.4A CN115384757B (en) | 2022-10-31 | 2022-10-31 | Flaperon actuating mechanism and wing structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115384757A CN115384757A (en) | 2022-11-25 |
| CN115384757B true CN115384757B (en) | 2023-01-24 |
Family
ID=84114926
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211342853.4A Active CN115384757B (en) | 2022-10-31 | 2022-10-31 | Flaperon actuating mechanism and wing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115384757B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115892448A (en) * | 2023-03-13 | 2023-04-04 | 北京启时智航科技有限公司 | Flaperon structure, wing and aircraft |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3921942A (en) * | 1974-07-01 | 1975-11-25 | Gen Dynamics Corp | Rudder boundary layer control device |
| US4120470A (en) * | 1976-09-28 | 1978-10-17 | The Boeing Company | Efficient trailing edge system for an aircraft wing |
| GB2003098A (en) * | 1977-07-07 | 1979-03-07 | British Aircraft Corp Ltd | Aircraft wings |
| US4720066A (en) * | 1985-08-29 | 1988-01-19 | Mbb Gmbh | Flap/spoiler combination |
| US5094412A (en) * | 1989-10-13 | 1992-03-10 | Bell Helicopter Textron Inc. | Flaperon system for tilt rotor wings |
| FR2756540A1 (en) * | 1996-11-29 | 1998-06-05 | Samsung Aerospace Ind | Aircraft wing design |
| WO2002017917A1 (en) * | 2000-08-29 | 2002-03-07 | The University Of Mississippi | Manzamines for treatment of drug resistant infection |
| JP2008529871A (en) * | 2005-02-04 | 2008-08-07 | ザ・ボーイング・カンパニー | System and method for controlling aircraft flaps and spoilers |
| CN102642616A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane high lift device with fixed double slotted flaps |
| EP2509857A1 (en) * | 2009-12-08 | 2012-10-17 | Airbus Operations Limited | Control surface assembly |
| CN105620723A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Flaperon |
| CN109895992A (en) * | 2017-12-07 | 2019-06-18 | 波音公司 | It is designed as the predeformation plane spoiler and sagging plate with the wing flap sealing under deflection state |
| CN113135283A (en) * | 2021-04-18 | 2021-07-20 | 西北工业大学 | Small-size high-precision fullerene flap actuating mechanism |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9016637B2 (en) * | 2012-02-10 | 2015-04-28 | The Boeing Company | High-positioned 3-position variable camber krueger |
| US9108715B2 (en) * | 2012-05-29 | 2015-08-18 | The Boeing Company | Rotary actuated high lift gapped aileron |
| US9580168B2 (en) * | 2014-12-19 | 2017-02-28 | The Boeing Company | Cove lip door slaved to trailing edge control device |
-
2022
- 2022-10-31 CN CN202211342853.4A patent/CN115384757B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3921942A (en) * | 1974-07-01 | 1975-11-25 | Gen Dynamics Corp | Rudder boundary layer control device |
| US4120470A (en) * | 1976-09-28 | 1978-10-17 | The Boeing Company | Efficient trailing edge system for an aircraft wing |
| GB2003098A (en) * | 1977-07-07 | 1979-03-07 | British Aircraft Corp Ltd | Aircraft wings |
| US4720066A (en) * | 1985-08-29 | 1988-01-19 | Mbb Gmbh | Flap/spoiler combination |
| US5094412A (en) * | 1989-10-13 | 1992-03-10 | Bell Helicopter Textron Inc. | Flaperon system for tilt rotor wings |
| FR2756540A1 (en) * | 1996-11-29 | 1998-06-05 | Samsung Aerospace Ind | Aircraft wing design |
| WO2002017917A1 (en) * | 2000-08-29 | 2002-03-07 | The University Of Mississippi | Manzamines for treatment of drug resistant infection |
| JP2008529871A (en) * | 2005-02-04 | 2008-08-07 | ザ・ボーイング・カンパニー | System and method for controlling aircraft flaps and spoilers |
| EP2509857A1 (en) * | 2009-12-08 | 2012-10-17 | Airbus Operations Limited | Control surface assembly |
| CN102642616A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane high lift device with fixed double slotted flaps |
| CN105620723A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Flaperon |
| CN109895992A (en) * | 2017-12-07 | 2019-06-18 | 波音公司 | It is designed as the predeformation plane spoiler and sagging plate with the wing flap sealing under deflection state |
| CN113135283A (en) * | 2021-04-18 | 2021-07-20 | 西北工业大学 | Small-size high-precision fullerene flap actuating mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115384757A (en) | 2022-11-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8408499B2 (en) | Aircraft | |
| EP2738087B1 (en) | Hinged panel operation systems and methods | |
| KR101125870B1 (en) | The tiltrotor aircraft | |
| US7028948B2 (en) | Apparatus for increase of aircraft lift and maneuverability | |
| CA2857892C (en) | Adaptive trailing edge actuator system and method | |
| US11505304B2 (en) | Aircraft spoiler actuation systems and related methods | |
| CN115384757B (en) | Flaperon actuating mechanism and wing structure | |
| BR102013024993A2 (en) | Hinged launched wingtip | |
| CA2788274C (en) | Active gurney flap | |
| KR20120091296A (en) | A compound motion structure | |
| CN117227965A (en) | Variable camber airfoil structure with deformation feedback | |
| CN108045556B (en) | Airplane flaperon motion mechanism | |
| CN111731469B (en) | Airfoil surface linkage device and aircraft | |
| CN212074400U (en) | Tilting rotor aircraft horizontal tail and horizontal tail tilting mechanism | |
| CN210942221U (en) | Structure for aerial combination of aircraft and aircraft adopting structure | |
| CN204433037U (en) | The servo-actuated seal structure of a kind of vehicle rudder leading edge | |
| CN117262212B (en) | Tilt rotor and aircraft | |
| CN217456332U (en) | Deformable wing device, wing and flight equipment | |
| CN220701377U (en) | Tail rudder linkage device of composite wing unmanned aerial vehicle | |
| CN114572380B (en) | Flexible trailing edge wing based on rigid-flexible coupling mechanism | |
| CN220549200U (en) | Aircraft aileron manipulation structure and fixed wing aircraft | |
| CN109353489A (en) | A kind of multi-functional flap configurations of unmanned plane | |
| CN218703884U (en) | Bionic flapping wing aircraft | |
| CN115892448A (en) | Flaperon structure, wing and aircraft | |
| CN111332457B (en) | Driving structure for wing and aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |