CN214661458U - Aviation composite connection structural member with built-in adjusting locking mechanism - Google Patents
Aviation composite connection structural member with built-in adjusting locking mechanism Download PDFInfo
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- CN214661458U CN214661458U CN202022985594.XU CN202022985594U CN214661458U CN 214661458 U CN214661458 U CN 214661458U CN 202022985594 U CN202022985594 U CN 202022985594U CN 214661458 U CN214661458 U CN 214661458U
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- assembling cylinder
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- locking mechanism
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Abstract
The utility model belongs to the technical field of aviation structure connection technique and specifically relates to a built-in aviation composite connection knot component of adjusting locking mechanism, including first linking frame, second linking frame and accommodate motor. The utility model discloses an aviation composite connection structural member with a built-in adjusting locking mechanism, which is characterized in that an adjusting motor is arranged in a first assembling cylinder by a first connection frame and a second connection frame which are movably assembled through the assembling cylinder, and an internal thread guide cylinder in a second assembling cylinder is matched to extrude an internal locking ring, so that the first assembling cylinder and the second assembling cylinder are conveniently controlled to be separated and combined, the adjusting mechanism is conveniently matched to control the second connection frame to overturn, and the separation and combination control is simple; the inner locking tooth surface is arranged on the inner side arc-shaped surface of the inner locking ring, the lateral meshing tooth surface is arranged on the outer side surface of the inner thread guide cylinder, and the first assembling cylinder and the second assembling cylinder are assembled more firmly and stably through the inner locking tooth surface and the lateral meshing tooth surface.
Description
Technical Field
The utility model belongs to the technical field of the aeronautical structure spare is connected technique and specifically relates to a built-in aviation composite connection knot component of adjusting locking mechanism.
Background
The integral structural member of the airplane is an important component for forming the skeleton and the aerodynamic appearance of the airplane body, and has various varieties, complex shapes and different materials. In order to reduce the weight, the strength design is carried out, and a guest complex cavity is formed on a structural part.
Aviation composite connection spare on the present market is mostly fixed knot structure, can't assist and adjust the structure of aeronautical equipment, leads to functional very singleness.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is: in order to solve the problem that exists among the above-mentioned background art, provide an aviation composite connection knot component of built-in regulation locking mechanism of modified, solve aviation composite connection spare on the present market and mostly be fixed knot structure, can't assist and adjust the structure of aeronautical equipment, lead to functional and stability very single problem.
The utility model provides a technical scheme that its technical problem adopted is: an aviation composite connection component with a built-in adjusting locking mechanism comprises a first connection frame, a second connection frame and an adjusting motor, wherein a first assembly cylinder with an integral structure is arranged at the center of the right side of the first connection frame, a second assembly cylinder with an integral structure is arranged at the front end and the rear end of the first assembly cylinder on the left side of the second connection frame, a longitudinal fixing plate with an integral structure is fixedly connected onto the inner side surface of the second assembly cylinder, an internal locking ring with an integral structure is arranged at the edge of the outer side surface of the longitudinal fixing plate, an internal locking tooth surface is arranged on the arc surface of the inner side of the internal locking ring, the inner diameter of the internal locking tooth surface is gradually increased from two ends to the center, an internal fixing frame for installing the adjusting motor is fixed inside the first assembly cylinder, and an external thread adjusting rod is axially fixed on a rotating shaft at two ends of the adjusting motor, the outer side of the external thread adjusting rod is located inside the second assembling cylinder and is in threaded connection with an internal thread guide cylinder, a lateral meshing tooth surface is arranged on the outer side surface of the internal thread guide cylinder close to the inner locking ring, and the first assembling cylinder is inserted into the inner locking tooth surface through the lateral meshing tooth surface and is fixedly connected with the second assembling cylinder.
The inner side surface of the first assembling cylinder is provided with limiting rings with integrated structures at the opening positions at two sides, and the inner side surface of the second assembling cylinder is elastically connected with an internal sealing cylinder.
The side direction adjusting sliding groove is formed in the position, located on the inner side arc face of the second assembling cylinder, of the inner sealing cylinder, an integral structure adjusting sliding block protruding towards the inside of the side direction adjusting sliding groove is arranged on the outer side arc face of the inner sealing cylinder, and a built-in extrusion spring is arranged inside the side direction adjusting sliding groove.
And a lateral inner screw hole communicated with the lateral adjusting chute is formed in the outer side surface of the second assembling cylinder, and a lateral adjusting screw rod is connected to the inner thread of the lateral inner screw hole.
The inner section of the second assembling cylinder is of a non-circular structure, and no gap exists between the inner side surface of the second assembling cylinder and the outer side connecting surface of the internal thread guide cylinder.
The first assembling cylinder and the second assembling cylinder have the same outer diameter.
The utility model has the advantages that:
(1) the utility model discloses an aviation composite connection structural member with a built-in adjusting locking mechanism, which is characterized in that an adjusting motor is arranged in a first assembling cylinder by a first connection frame and a second connection frame which are movably assembled through the assembling cylinder, and an internal thread guide cylinder in a second assembling cylinder is matched to extrude an internal locking ring, so that the first assembling cylinder and the second assembling cylinder are conveniently controlled to be separated and combined, the adjusting mechanism is conveniently matched to control the second connection frame to overturn, and the separation and combination control is simple;
(2) the inner locking tooth surface is arranged on the inner side arc-shaped surface of the inner locking ring, the lateral meshing tooth surface is arranged on the outer side surface of the inner thread guide cylinder, and the first assembling cylinder and the second assembling cylinder are assembled more firmly and stably through the inner locking tooth surface and the lateral meshing tooth surface.
Drawings
The present invention will be further explained with reference to the drawings and examples.
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a partial sectional view of the connecting end of the first assembling tube and the second assembling tube of the present invention.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic drawings and illustrate the basic structure of the present invention only in a schematic manner, and thus show only the components related to the present invention.
Fig. 1 and 2 show an aviation composite connecting joint component with a built-in adjusting locking mechanism, which comprises a first connecting frame 1, a second connecting frame 2 and an adjusting motor 3, wherein a first assembling cylinder 4 with an integrated structure is arranged at the right center of the first connecting frame 1, a second assembling cylinder 5 with an integrated structure is arranged at the front end and the rear end of the first assembling cylinder 4 at the left side of the second connecting frame 2, an integrated structure longitudinal fixing plate 6 is fixedly connected to the inner side of the second assembling cylinder 5, an integrated structure inner locking ring 7 is arranged at the edge position of the outer side of the longitudinal fixing plate 6, an inner locking tooth surface is arranged on the inner arc surface of the inner locking ring 7, the inner diameter of the inner locking tooth surface is gradually increased from two ends to the center, an inner fixing frame 8 for installing the adjusting motor 3 is fixed in the first assembling cylinder 4, an external thread adjusting rod 9 is axially fixed on the rotating shafts at two ends of the adjusting motor 3, the outer side of the external thread adjusting rod 9 is located inside the second assembling cylinder 5 and is in threaded connection with an internal thread guide cylinder 10, a lateral meshing tooth surface is arranged on the outer side surface, close to the inner locking ring 7, of the internal thread guide cylinder 10, and the first assembling cylinder 4 is inserted into the inner locking tooth surface through the lateral meshing tooth surface and is fixedly connected with the second assembling cylinder 5.
Further, for the purpose of matching and limiting, the opening positions on the two sides of the inner side surface of the first assembling cylinder 4 are respectively provided with an integral structure inner limiting ring 11, and the inner side surface of the second assembling cylinder 5 is elastically connected with an inner sealing cylinder 12.
Further, in order to cooperate the elastic extrusion, the lateral regulation sliding groove 13 is formed in the position, located on the arc-shaped surface on the inner side of the second assembly cylinder 5, of the inner sealing cylinder 12, the sliding block 14 is adjusted to the inside protruding integrated structure of the lateral regulation sliding groove 13 on the arc-shaped surface on the outer side of the inner sealing cylinder 12, the internal side of the lateral regulation sliding groove 13 is internally provided with a built-in extrusion spring 15, further, the internal elastic extrusion device is conveniently assembled and disassembled, the lateral internal screw hole communicated with the lateral regulation sliding groove 13 is formed in the outer side surface of the second assembly cylinder 5, and the internal thread of the lateral internal screw hole is connected with a lateral regulation screw 16.
Further, in order to facilitate telescopic translation, the inner section of the second assembling cylinder 5 is of a non-circular structure, no gap exists between the inner side surface of the second assembling cylinder 5 and the outer side connecting surface of the internal thread guide cylinder 10, and further, in order to reduce cost and facilitate assembly, the outer diameters of the first assembling cylinder 4 and the second assembling cylinder 5 are the same.
The utility model discloses an aviation composite connection structural member with a built-in adjusting locking mechanism, which is characterized in that an adjusting motor 3 is arranged in a first assembling cylinder 4 by a first connecting frame 1 and a second connecting frame 2 which are movably assembled by the assembling cylinder, and an internal thread guide cylinder 10 in a second assembling cylinder 5 is matched to extrude an internal locking ring 7, so that the first assembling cylinder 4 and the second assembling cylinder 5 are conveniently controlled to be separated and combined, the adjusting mechanism is conveniently matched to control the second connecting frame 2 to overturn, and the separation and combination control is simple; the inside locking flank of tooth has been seted up on the inboard arcwall face of inside lock ring 7, has the side direction engaging flank of tooth on the lateral surface of internal thread guide cylinder 10, meshes mutually through inside locking flank of tooth and side direction engaging flank of tooth for first assembly section of thick bamboo 4 and the assembly of second assembly section of thick bamboo 5 are firm more stable.
In light of the foregoing, it will be apparent to those skilled in the art from this disclosure that various changes and modifications can be made without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.
Claims (6)
1. The utility model provides a built-in aviation composite connection structural member who adjusts locking mechanism, includes first linking frame (1), second linking frame (2) and accommodate motor (3), characterized by: the right center of the first connecting frame (1) is provided with a first assembling cylinder (4) with an integral structure, the left side of the second connecting frame (2) is positioned in front of the first assembling cylinder (4), the rear end of the first assembling cylinder is provided with a second assembling cylinder (5) with an integral structure, the inner side of the second assembling cylinder (5) is fixedly connected with a longitudinal fixing plate (6) with an integral structure, the edge position of the outer side of the longitudinal fixing plate (6) is provided with an inner locking ring (7) with an integral structure, the inner arc-shaped surface of the inner locking ring (7) is provided with an inner locking tooth surface, the inner diameter of the inner locking tooth surface is gradually increased from two ends to the center, the inner fixing frame (8) for installing the adjusting motor (3) is fixed in the first assembling cylinder (4), and an external thread adjusting rod (9) is axially fixed on the rotating shaft at two ends of the adjusting motor (3), the outer side of the external thread adjusting rod (9) is located inside the second assembling cylinder (5) and is connected with an internal thread guide cylinder (10) in a threaded manner, a lateral meshing tooth surface is arranged on the outer side surface of the internal thread guide cylinder (10) close to the inner locking ring (7), and the first assembling cylinder (4) is inserted into the inner locking tooth surface through the lateral meshing tooth surface and is fixedly connected with the second assembling cylinder (5).
2. The aeronautical composite coupling component with an adjustable locking mechanism built in according to claim 1, wherein: the inner side surface of the first assembling cylinder (4) is provided with an integral structure inner limiting ring (11) at the opening positions at two sides, and the inner side surface of the second assembling cylinder (5) is elastically connected with an inner sealing cylinder (12).
3. The aeronautical composite coupling component with an adjustable locking mechanism built in according to claim 2, wherein: the side direction adjusting device is characterized in that a side direction adjusting sliding groove (13) is formed in the position, located on the inner side arc-shaped surface of the second assembling cylinder (5), of the inner sealing cylinder (12), an integral structure adjusting sliding block (14) protruding towards the inside of the side direction adjusting sliding groove (13) is arranged on the outer side arc-shaped surface of the inner sealing cylinder (12), and a built-in extrusion spring (15) is arranged inside the side direction adjusting sliding groove (13).
4. The aeronautical composite coupling component with an adjustable locking mechanism built in according to claim 1, wherein: and a lateral inner screw hole communicated with the lateral adjusting chute (13) is formed in the outer side surface of the second assembling cylinder (5), and a lateral adjusting screw rod (16) is connected to the inner part of the lateral inner screw hole in a threaded manner.
5. The aeronautical composite coupling component with an adjustable locking mechanism built in according to claim 1, wherein: the inner section of the second assembling cylinder (5) is of a non-circular structure, and no gap exists between the inner side surface of the second assembling cylinder (5) and the outer side connecting surface of the internal thread guide cylinder (10).
6. The aeronautical composite coupling component with an adjustable locking mechanism built in according to claim 1, wherein: the first assembling cylinder (4) and the second assembling cylinder (5) have the same outer diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022985594.XU CN214661458U (en) | 2020-12-11 | 2020-12-11 | Aviation composite connection structural member with built-in adjusting locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022985594.XU CN214661458U (en) | 2020-12-11 | 2020-12-11 | Aviation composite connection structural member with built-in adjusting locking mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214661458U true CN214661458U (en) | 2021-11-09 |
Family
ID=78499185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022985594.XU Active CN214661458U (en) | 2020-12-11 | 2020-12-11 | Aviation composite connection structural member with built-in adjusting locking mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214661458U (en) |
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2020
- 2020-12-11 CN CN202022985594.XU patent/CN214661458U/en active Active
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