CN117246506A - Intelligent deformation driving device for trailing edge of aeroplane wing - Google Patents
Intelligent deformation driving device for trailing edge of aeroplane wing Download PDFInfo
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- CN117246506A CN117246506A CN202311358636.9A CN202311358636A CN117246506A CN 117246506 A CN117246506 A CN 117246506A CN 202311358636 A CN202311358636 A CN 202311358636A CN 117246506 A CN117246506 A CN 117246506A
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- 238000009434 installation Methods 0.000 claims description 10
- 238000000034 method Methods 0.000 description 2
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- 230000007547 defect Effects 0.000 description 1
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Classifications
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to the field of aviation intelligent structures, in particular to an intelligent deformation driving device for the trailing edge of an aviation wing, which mainly comprises a fixed module assembly and a movable module assembly power device which are connected, wherein a first-stage power device drives 5 a first connecting rod mechanism 7 to operate so as to drive a second movable module 3 and the second movable module 3 to rotate around a shaft, and a second-stage power device 6 drives a second connecting rod mechanism 8 to operate so as to drive a tail movable module 4 to rotate around a shaft. The two-stage synchronous/asynchronous start-stop target is realized by setting the deflection angle of the two-stage connecting rod and controlling the rotating speed of the motor, and the trailing edge wing generates larger deformation after being driven by the two-stage power device.
Description
Technical Field
The invention relates to the field of aviation intelligent structures, in particular to an intelligent deformation driving device for an aviation wing trailing edge.
Background
Aircraft wings are the primary components that provide aircraft lift, and their external configuration has a tremendous impact on flight performance. With the continuous increase of the flying speed and the bearing capacity, the trailing edge of the aerofoil which can adaptively, smoothly and continuously change the geometric shape according to specific flying conditions becomes a research hot spot.
In recent years, two main approaches have been adopted for continuous smooth deformation of the trailing edge of the wing. Firstly, the intelligent material is used for the trailing edge of the wing, and the trailing edge deformation is realized by utilizing the characteristics of the material. The wing designed by the method has a simple structure and light weight, but the intelligent material has slow deformation response and cannot bear larger pneumatic load, and is difficult to match with flight requirements. Secondly, a single-stage driving mechanism is adopted to drive the trailing edge of the wing to deform, the deformation response is quick, but the deformation amplitude is small, and the flying requirement is difficult to meet.
Aiming at the defects of the method, the intelligent deformation driving device for the trailing edge of the wing is designed, the output torque of a motor is amplified through a two-stage multi-link mechanism to drive the trailing edge of the wing to deform in a target mode, and the driving mode can not only output larger deformation, but also effectively improve the instantaneity and the stability of the deformation of the trailing edge.
Disclosure of Invention
The purpose of the invention is that: the intelligent deformation driving device for the trailing edge of the aircraft wing is designed, and the device adopts a motor to drive a two-stage multi-link mechanism so as to drive the trailing edge of the wing to deform.
The intelligent deformation driving device for the trailing edge of the aeroplane wing comprises at least two driving units which are fixed at the rear end of the aeroplane wing and distributed along the spanwise direction, wherein each driving unit comprises a multi-stage module which is sequentially hinged backwards along the course, and the height of each stage module is gradually reduced backwards along the course; the module comprises a fixed module assembly arranged at the rear end of the wing truss, a tail movable module positioned at the tail end and at least one stage of movable module positioned between the fixed module assembly and the tail swing module;
a plurality of connecting rods are connected between each stage of movable module and the next stage of movable module to form a connecting rod mechanism for enabling the next stage of movable module to swing, an installation space is formed in the middle of each stage of movable module, and a power device for driving the connecting rod mechanism is installed in the installation space; the power plant includes a power source.
Preferably, the movable module comprises a first movable module assembly and a second movable module assembly which are hinged at the rear end of the fixed module assembly in sequence, wherein the power device comprises a first-stage power device arranged in the installation space of the first movable module assembly and a second-stage power device arranged in the installation space of the second movable module assembly;
the connecting rod comprises a first-stage connecting rod and a second-stage connecting rod,
the first-stage connecting rods are hinged to the side surfaces of the first movable module assembly and the second movable module assembly, the first movable module assembly, the second movable module assembly and the first-stage connecting rods form a first connecting rod mechanism, and the first-stage power device drives the first connecting rod mechanism to enable the second movable module assembly to swing relative to the first movable module assembly;
the second-stage connecting rods are hinged to the side faces of the second movable module assembly and the tail swing module, the second movable module assembly and the tail swing module are multiple in number, the second-stage connecting rods form a second connecting rod mechanism, and the second-stage power device drives the second connecting rod mechanism to enable the tail swing module to swing relative to the second movable module assembly.
Preferably, a long connecting rod is hinged between the fixed module assembly and the second movable module assembly, and the long connecting rod, the fixed module assembly, the first movable module assembly and the second movable module assembly form a third connecting rod mechanism.
Preferably, the plurality of connecting rods comprise a rocker arm, a first short rod, a triangular rocker arm, a second short rod, a connecting arm and a third short rod, wherein one end of the rocker arm is connected with the driving device, the other end of the rocker arm is hinged with the first short rod, one end of the triangular rocker arm is hinged on the movable module, the other end of the triangular rocker arm is respectively hinged with the first short rod and the second short rod, and the rocker arm, the first short rod, the triangular rocker arm and the movable module form a first plane four-bar mechanism;
the other end of the second short rod is hinged with a connecting arm, the middle of the connecting arm is hinged on the movable module, the other end of the connecting arm is hinged with a third short rod, the triangular rocker arm, the second short rod, the connecting arm and the movable module form a second plane four-bar mechanism,
the connecting arm, the movable module, the third short rod and the movable module at the next stage of the movable module form a third plane four-rod mechanism.
Preferably, the movable modules are provided with skins on the surfaces, and the skins between adjacent movable modules are overlapped with each other.
Preferably, the movement pattern between the drive units comprises synchronous movement or differential movement.
The advantages of the present application include:
a) The invention adopts the two-stage power device to drive the integral deformation of the trailing edge of the wing, and has larger deformation amplitude and higher bearing capacity;
b) The motor is used as a power source, and the real-time deformation of the trailing edge of the wing is easier to control and better in stability.
Drawings
FIG. 1 is a schematic illustration of an intelligent deformation actuator for an aircraft wing trailing edge according to a preferred embodiment of the present application;
FIG. 2 is a schematic view of a connecting rod according to a preferred embodiment of the present application.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The purpose of the invention is that: the intelligent deformation driving device for the trailing edge of the aircraft wing is designed, and the device adopts a motor to drive a two-stage multi-link mechanism so as to drive the trailing edge of the wing to deform.
The intelligent deformation driving device for the trailing edge of the aeroplane wing comprises at least two driving units which are fixed at the rear end of the aeroplane wing and distributed along the spanwise direction, wherein each driving unit comprises a multi-stage module which is sequentially hinged backwards along the course, and the height of each stage module is gradually reduced backwards along the course; the module comprises a fixed module assembly 1 arranged at the rear end of the wing truss, a tail movable module 4 positioned at the tail end, and at least one stage of movable module positioned between the fixed module assembly 1 and the tail swing module 4;
a plurality of connecting rods are connected between each stage of movable module and the next stage of movable module to form a connecting rod mechanism for enabling the next stage of movable module to swing, an installation space is formed in the middle of each stage of movable module, and a power device for driving the connecting rod mechanism is installed in the installation space; the power plant includes a power source.
Preferably, the movable module comprises a first movable module assembly 2 and a second movable module assembly 3 which are hinged at the rear end of the fixed module assembly 1 in sequence, wherein the power device comprises a first-stage power device 5 arranged in the installation space of the first movable module assembly 2 and a second-stage power device 6 arranged in the installation space of the second movable module assembly 3;
the connecting rod comprises a first-stage connecting rod and a second-stage connecting rod,
the first-stage connecting rods are hinged to the side surfaces of the first movable module assembly 2 and the second movable module assembly 3, the first movable module assembly 2, the second movable module assembly 3 and the first-stage connecting rods form a first connecting rod mechanism 7, and the first-stage power device 5 drives the first connecting rod mechanism 7 to enable the second movable module assembly 3 to swing relative to the first movable module assembly 2;
the second-stage connecting rods are hinged to the side faces of the second movable module assembly 3 and the tail swing module 4, the second movable module assembly 3 and the tail swing module 4 form a second connecting rod mechanism 8, and the second-stage power device 6 drives the second connecting rod mechanism 8 to enable the tail swing module 4 to swing relative to the second movable module assembly 3.
As shown in fig. 1, the left end of the first movable module assembly 2 is connected with the fixed module assembly 1, the right end is connected with the tail swing module 4 by virtue of a pin shaft, and the right end is connected with the first power device 5 by virtue of bolts and rotating shafts respectively;
the left end of the tail swing module 4 is connected with the first movable module assembly 2, and the right end of the tail swing module 4 is connected with the tail swing module by a pin shaft.
Preferably, a long connecting rod 9 is hinged between the fixed module assembly 1 and the second movable module assembly 3, and the long connecting rod 9, the fixed module assembly 1, the first movable module assembly 2 and the second movable module assembly 3 form a third connecting rod mechanism for amplifying the output torque and transmitting power of the first power device 5 and reducing the formation of the second movable module assembly 3, and meanwhile, the first movable module assembly 2 can be driven to move by the movement of the second movable module assembly 3.
Preferably, the plurality of connecting rods include a rocker arm 101, a first short rod 102, a triangular rocker arm 103, a second short rod 104, a connecting arm 105 and a third short rod 106, wherein one end of the rocker arm 101 is connected with the driving device, the other end of the rocker arm is hinged with the first short rod 102, one end of the triangular rocker arm 103 is hinged with the movable module, the other end of the triangular rocker arm is respectively hinged with the first short rod 102 and the second short rod 104, and the rocker arm 101, the first short rod 103, the triangular rocker arm 103 and the movable module form a first plane four-bar mechanism;
the other end of the second short rod 104 is hinged with a connecting arm 105, the middle of the connecting arm 105 is hinged on the movable module, the other end of the connecting arm 105 is hinged with a third short rod 106, the triangular rocker 103, the second short rod 104, the connecting arm 105 and the movable module form a second plane four-bar mechanism,
the connecting arm 105, the movable module, the third short bar 106, and the movable module next to the movable module form a third planar four-bar mechanism.
Preferably, the movable modules are provided with skins on the surfaces, and the skins between adjacent movable modules are overlapped with each other.
Preferably, the movement pattern between the drive units comprises synchronous movement or differential movement.
The specific implementation mode is as follows:
the first link mechanism 7 is driven 5 by the first-stage power device to rotate, so that the second movable module 3 and the second movable module 3 are driven to rotate around the shaft, and meanwhile, the second link mechanism 8 is driven by the second-stage power device 6 to rotate around the shaft, so that the tail movable module 4 is driven to rotate around the shaft. The two-stage synchronous/asynchronous start-stop target is realized by setting the deflection angle of the two-stage connecting rod and controlling the rotating speed of the motor, and the trailing edge wing generates larger deformation after being driven by the two-stage power device.
The advantages of the present application include:
the invention adopts a two-stage power device to drive the trailing edge of the wing to integrally deform, so that the deformation amplitude is larger and the bearing capacity is higher;
and b, a motor is used as a power source, so that the real-time deformation of the trailing edge of the wing is easier to control and the stability is better.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The intelligent deformation driving device for the trailing edge of the aeroplane wing is characterized by comprising at least two driving units which are fixed at the rear end of the aeroplane wing and distributed along the spanwise direction, wherein each driving unit comprises a plurality of stages of modules which are sequentially hinged backwards along the course, and the height of each stage of modules is gradually reduced backwards along the course; the module comprises a fixed module assembly (1) arranged at the rear end of the wing truss, a tail movable module (4) positioned at the tail end, and at least one stage of movable module positioned between the fixed module assembly (1) and the tail swing module (4);
the movable modules at each stage are connected with the movable modules at the next stage to form a connecting rod mechanism for enabling the movable modules at the next stage to swing, the middle parts of the movable modules at each stage form a mounting space, and a power device for driving the connecting rod mechanism is arranged in the mounting space.
2. The intelligent deformation driving device for the trailing edge of the aeroplane wing according to claim 1, wherein the movable module comprises a first movable module assembly (2) and a second movable module assembly (3) which are hinged at the rear end of the fixed module assembly (1) in sequence, wherein the power device comprises a first-stage power device (5) installed in the installation space of the first movable module assembly (2) and a second-stage power device (6) installed in the installation space of the second movable module assembly (3);
the connecting rod comprises a first-stage connecting rod and a second-stage connecting rod,
the first-stage connecting rods are hinged to the side surfaces of the first movable module assembly (2) and the second movable module assembly (3), the first movable module assembly (2), the second movable module assembly (3) and the first-stage connecting rods form a first connecting rod mechanism (7), and the first-stage power device (5) drives the first connecting rod mechanism (7) to enable the second movable module assembly (3) to swing relative to the first movable module assembly (2);
the second-stage connecting rods are hinged to the side faces of the second movable module assembly (3) and the tail swing module (4), the second movable module assembly (3) and the tail swing module (4) are multiple the second-stage connecting rods form a second connecting rod mechanism (8), and the second-stage power device (6) drives the second connecting rod mechanism (8) to enable the tail swing module (4) to swing relative to the second movable module assembly (3).
3. Intelligent deformation drive for an aircraft wing trailing edge according to claim 2, characterized in that a long link (9) is hinged between the fixed module assembly (1) and the second movable module assembly (3), the long link (9), the fixed module assembly (1), the first movable module assembly (2) and the second movable module assembly (3) forming a third link mechanism.
4. The intelligent deformation driving device for an aircraft wing trailing edge according to claim 1, wherein the plurality of links includes a rocker arm (101), a first short bar (102), a triangular rocker arm (103), a second short bar (104), a connecting arm (105) and a third short bar (106), wherein one end of the rocker arm (101) is connected with the driving device, the other end is hinged with the first short bar (102), one end of the triangular rocker arm (103) is hinged with the movable module, the other end is respectively hinged with the first short bar (102) and the second short bar (104), and the rocker arm (101), the first short bar (103), the triangular rocker arm (103) and the movable module form a first plane four-bar mechanism;
the other end of the second short rod (104) is hinged with a connecting arm (105), the middle of the connecting arm (105) is hinged on the movable module, the other end of the connecting arm (105) is hinged with a third short rod (106), the triangular rocker arm (103), the second short rod (104), the connecting arm (105) and the movable module form a second plane four-rod mechanism,
the connecting arm (105), the movable module, the third short rod (106) and the movable module at the next stage of the movable module form a third plane four-rod mechanism.
5. An intelligent deformation driving device for an aircraft wing trailing edge according to claim 1 wherein the movable modules are surface mounted with skins and wherein the skins between adjacent movable modules overlap.
6. The intelligent morphing drive for an aircraft wing trailing edge of claim 1, wherein the manner of movement between the drive units comprises synchronous movement or differential movement.
7. The intelligent deformation drive for an aircraft wing trailing edge of claim 1, wherein the power means comprises a power source.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311358636.9A CN117246506A (en) | 2023-10-19 | 2023-10-19 | Intelligent deformation driving device for trailing edge of aeroplane wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311358636.9A CN117246506A (en) | 2023-10-19 | 2023-10-19 | Intelligent deformation driving device for trailing edge of aeroplane wing |
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| CN117246506A true CN117246506A (en) | 2023-12-19 |
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| CN202311358636.9A Pending CN117246506A (en) | 2023-10-19 | 2023-10-19 | Intelligent deformation driving device for trailing edge of aeroplane wing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119467034A (en) * | 2025-01-14 | 2025-02-18 | 上海风雷阀门集团有限公司 | Automatic disconnect-type jigger device |
-
2023
- 2023-10-19 CN CN202311358636.9A patent/CN117246506A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119467034A (en) * | 2025-01-14 | 2025-02-18 | 上海风雷阀门集团有限公司 | Automatic disconnect-type jigger device |
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