CN216803184U - Aircraft skin mouth frame positioner - Google Patents
Aircraft skin mouth frame positioner Download PDFInfo
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- CN216803184U CN216803184U CN202220545588.9U CN202220545588U CN216803184U CN 216803184 U CN216803184 U CN 216803184U CN 202220545588 U CN202220545588 U CN 202220545588U CN 216803184 U CN216803184 U CN 216803184U
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- block
- adjusting rod
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- negative pressure
- aircraft skin
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- 238000001179 sorption measurement Methods 0.000 claims abstract description 24
- 238000009434 installation Methods 0.000 claims abstract description 16
- 230000005540 biological transmission Effects 0.000 claims description 14
- 238000012546 transfer Methods 0.000 claims description 6
- 230000002457 bidirectional effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 2
- 230000001360 synchronised effect Effects 0.000 claims 1
- 238000010030 laminating Methods 0.000 abstract description 7
- 238000010521 absorption reaction Methods 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 5
- 238000001125 extrusion Methods 0.000 abstract 1
- 238000012545 processing Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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Abstract
The utility model discloses an aircraft skin opening frame positioning device which comprises a base and a bottom supporting block, wherein the bottom supporting block is fixed above the base and provides bottom support for a product, lateral supporting plates are symmetrically arranged on the left side and the right side of the bottom supporting block, a fitting block is arranged above the lateral supporting plates and is in contact with the surface of the product through the fitting block, an installation shaft is fixed on the outer side of the fitting block, the fitting block is rotationally connected with the lateral supporting plates through the installation shaft, and the front side of the installation shaft is connected with a first motor. This aircraft covering mouthful frame positioner can make the absorption mouth produce the adsorption affinity through the removal of negative pressure intracavity piston to adsorb spacingly to the product side, the adjustment of angle can be carried out to the laminating piece simultaneously, makes absorption mouth ability and product surface keep effectual laminating, has avoided the product to appear sliding or by extrusion deformation after by spacing, the location effect of improvement device.
Description
Technical Field
The utility model relates to the technical field of aircraft skin opening frames, in particular to an aircraft skin opening frame positioning device.
Background
The aircraft skin opening frame is used as a processing carrier of an aircraft external skin, and the aircraft skin opening frame needs to be positioned by a positioning device when being processed, so that the aircraft skin opening frame keeps good stability, but the existing skin opening frame positioning device has some defects when being used;
the existing positioning device is mostly positioned by adopting a clamping mode, the opening frame is easy to slide and shift in the follow-up process of clamping, the deformation of the opening frame can be caused when the clamping force is large, the follow-up stability and the processing effect are influenced, and the overall positioning effect of the device is reduced.
In order to solve the above problems, innovative design based on the original positioning device is urgently needed.
Disclosure of Invention
The utility model aims to provide an aircraft skin opening frame positioning device, which aims to solve the problems that the existing positioning devices in the current market provided by the background technology mostly adopt a clamping mode to position the opening frame, the opening frame is easy to slide and shift during the subsequent clamping, and the deformation of the opening frame is caused when the clamping force is large, so that the subsequent stability and the subsequent processing effect are influenced.
In order to achieve the purpose, the utility model provides the following technical scheme: a positioning device for an aircraft skin opening frame comprises a base and a bottom supporting block, wherein the bottom supporting block is fixed above the base to provide bottom support for a product, lateral supporting plates are symmetrically arranged on the left side and the right side of the bottom supporting block, a fitting block is arranged above the lateral supporting plates and is in contact with the surface of the product through the fitting block, an installation shaft is fixed on the outer side of the fitting block, the fitting block is in rotating connection with the lateral supporting plates through the installation shaft, a first motor is connected to the front side of the installation shaft to control the rotation of the installation shaft, an adsorption opening is formed in the fitting block to adsorb the product through the adsorption opening, the lower end of the adsorption opening is connected with the lateral supporting plates through flexible communicating pipes, a negative pressure cavity is connected below the flexible communicating pipes, and the internal space of the negative pressure cavity is communicated with the adsorption opening through the flexible communicating pipes, the piston is arranged in the negative pressure cavity, the transmission rod is fixed below the piston, the vertical position control mechanism is connected below the transmission rod, the position of the piston in the negative pressure cavity can be adjusted through the vertical position control mechanism, and the horizontal position control mechanism is arranged below the lateral supporting plate and used for controlling the horizontal position of the lateral supporting plate.
Further optimize this technical scheme, the surface bonding of laminating piece has the rubber pad, improves the laminating compactness of laminating piece and product surface, makes follow-up absorption mouth can provide effectual absorption confining force to the product.
Further optimize this technical scheme, constitute the up-and-down sliding structure between transfer line and the side direction backup pad, and the lower extreme of side direction backup pad is provided with the control panel to the control panel runs through and constitutes the side-to-side sliding structure between the transfer line of left and right sides and the transfer line, vertical position control mechanism and control panel are connected, through the removal synchro control of control panel the removal of two sets of transfer lines.
Further optimizing the technical scheme, the vertical position control mechanism comprises a first adjusting rod and a second motor;
the first adjusting rod penetrates through the control plate and is in threaded connection with the control plate, a first adjusting rod bearing is arranged inside the bottom supporting block, and an up-and-down sliding structure is formed between the control plate and the bottom supporting block;
the second motor is arranged at the end part of the first adjusting rod and provides rotary driving force for the first adjusting rod, and the control panel can be driven to move through the rotation of the subsequent first adjusting rod, so that the position of the transmission rod is controlled.
Further optimize this technical scheme, the radial outside surface of piston and the inner wall in negative pressure chamber laminate mutually and set up, and sliding structure about constituting between piston and the negative pressure chamber, make negative pressure intracavity energy production negative pressure through the removal of piston in the negative pressure intracavity to make the absorption mouth can produce the adsorption affinity.
Further optimizing the technical scheme, the horizontal position control mechanism comprises a driving block, a second adjusting rod and a third motor;
the driving block is fixed below the lateral supporting plate, and a left-right sliding structure is formed between the driving block and the base;
the second adjusting rod penetrates through the driving blocks to form threaded connection with the driving blocks, is a bidirectional threaded rod and can drive the two groups of driving blocks on the surface of the second adjusting rod to synchronously move reversely when rotating;
the third motor is connected with the second adjusting rod to provide rotary driving force for the second adjusting rod, so that the subsequent lateral supporting plate can move in the horizontal direction, and the adaptation to different products is facilitated.
Compared with the prior art, the utility model has the beneficial effects that:
(1) the aircraft skin opening frame positioning device can enable the adsorption opening to generate adsorption force through the movement of the piston in the negative pressure cavity, so that the side edge of a product is adsorbed and limited, and meanwhile, the angle of the adhesion block can be adjusted, so that the adsorption opening can be effectively adhered to the surface of the product, the product is prevented from sliding or being extruded and deformed after being limited, and the positioning effect of the device is improved;
(2) this aircraft covering mouthful frame positioner can adjust the horizontal position of laminating piece through horizontal position control mechanism, and the rotation of cooperation laminating piece self can make its and the product surface of different radians laminate to make the device can fix a position the product of equidimension not, increase the functionality of device.
Drawings
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is a schematic view of the main section structure of the present invention;
FIG. 3 is an enlarged view of a portion a of FIG. 2 according to the present invention;
FIG. 4 is a schematic side view of a bonding block according to the present invention;
FIG. 5 is a schematic diagram of the connection structure of the control plate and the transmission rod in side view.
In the figure: 1. a base; 2. a bottom support block; 3. a lateral support plate; 4. fitting blocks; 5. installing a shaft; 6. a first motor; 7. an adsorption port; 8. a rubber pad; 9. a flexible communicating tube; 10. a negative pressure chamber; 11. a piston; 12. a transmission rod; 13. a control panel; 14. a first adjusting lever; 15. a second motor; 16. a drive block; 17. a second adjusting lever; 18. a third motor.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-5, the present invention provides a technical solution: a positioning device for an aircraft skin opening frame comprises a base 1 and a bottom supporting block 2, wherein the bottom supporting block 2 is fixed above the base 1 and provides bottom support for a product, lateral supporting plates 3 are symmetrically arranged on the left side and the right side of the bottom supporting block 2, a fitting block 4 is arranged above the lateral supporting plates 3 and is in contact with the surface of the product through the fitting block 4, an installation shaft 5 is fixed on the outer side of the fitting block 4, the fitting block 4 is rotatably connected with the lateral supporting plates 3 through the installation shaft 5, a first motor 6 is connected to the front side of the installation shaft 5 and controls the rotation of the installation shaft 5, an adsorption opening 7 is formed in the fitting block 4 and adsorbs the product through the adsorption opening 7, the lower end of the adsorption opening 7 is connected with the lateral supporting plates 3 through a flexible communicating pipe 9, a negative pressure cavity 10 is connected below the flexible communicating pipe 9, and the inner space of the negative pressure cavity 10 is communicated with the adsorption opening 7 through the flexible communicating pipe 9, a piston 11 is arranged in the negative pressure cavity 10, a transmission rod 12 is fixed below the piston 11, a vertical position control mechanism is connected below the transmission rod 12, the position of the piston 11 in the negative pressure cavity 10 can be adjusted through the vertical position control mechanism, and a horizontal position control mechanism is arranged below the lateral support plate 3 and used for controlling the horizontal position of the lateral support plate 3;
the rubber pad 8 is bonded on the surface of the attaching block 4, the attaching tightness of the attaching block 4 and the surface of a product is improved, a vertical sliding structure is formed between the transmission rod 12 and the lateral supporting plate 3, the lower end of the lateral supporting plate 3 is provided with a control plate 13, the control plate 13 penetrates through the transmission rods 12 on the left side and the right side and the transmission rods 12 to form a left-right sliding structure, the vertical position control mechanism is connected with the control plate 13, the movement of the two groups of transmission rods 12 is synchronously controlled through the movement of the control plate 13, and the vertical position control mechanism comprises a first adjusting rod 14 and a second motor 15;
the first adjusting rod 14 penetrates through the control plate 13 and forms threaded connection with the control plate 13, the first adjusting rod 14 is mounted inside the bottom supporting block 2 in a bearing mode, and a vertical sliding structure is formed between the control plate 13 and the bottom supporting block 2;
a second motor 15 installed at an end of the first adjusting lever 14 to provide a rotational driving force for the first adjusting lever 14;
the radial outer side surface of the piston 11 is attached to the inner wall of the negative pressure cavity 10, and an up-and-down sliding structure is formed between the piston 11 and the negative pressure cavity 10;
the product to be positioned can be placed on the bottom supporting block 2, then the first motor 6 is used for controlling the installation shaft 5 to rotate, the angle of the fitting block 4 is controlled, the adsorption port 7 can be tightly fitted with the surface of the product, then the second motor 15 can be started to drive the first adjusting rod 14 to rotate, the first adjusting rod 14 is connected with the control plate 13 through threads to drive the control plate 13 to move when rotating, the control plate 13 pulls the transmission rod 12 to move, the transmission rod 12 drives the piston 11 to move, negative pressure is generated in the negative pressure cavity 10 and is transmitted into the adsorption port 7 through the flexible communication pipe 9, the adsorption port 7 adsorbs the product, the positioning of the product is completed, the subsequent sliding of the product is avoided, the piston 11 is controlled to reset when the positioning is required to be released subsequently, and the air pressure in the adsorption port 7 is recovered.
The horizontal position control mechanism comprises a driving block 16, a second adjusting rod 17 and a third motor 18;
the driving block 16 is fixed below the lateral supporting plate 3, and a left-right sliding structure is formed between the driving block 16 and the base 1;
the second adjusting rod 17 penetrates through the driving block 16 and forms threaded connection with the driving block 16, and the second adjusting rod 17 is a bidirectional threaded rod and can drive the two groups of driving blocks 16 on the surface of the second adjusting rod to synchronously move in the opposite direction when rotating;
a third motor 18 connected to the second adjusting lever 17 to provide a rotational driving force to the second adjusting lever 17;
when the size and the radian of a product are changed, the horizontal position of the attaching block 4 can be adjusted, the second adjusting rod 17 is driven to rotate by the third motor 18, the second adjusting rod 17 drives the lateral supporting plate 3 to move through the threaded connection with the driving block 16, the horizontal position of the attaching block 4 is adjusted, and the attaching block can continue to be attached to the surface of the product by matching with the subsequent adjustment of the angle of the attaching block 4.
The working principle is as follows: when the positioning device for the aircraft skin opening frame is used, a product can be placed on the bottom supporting block 2, then the attachment block 4 can be stably attached to the surface of the product through adjustment of the horizontal position and the angle of the attachment block, and then the adsorption opening 7 generates adsorption force through movement of the piston 11 in the negative pressure cavity 10 to position the product.
Those not described in detail in this specification are within the skill of the art.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the utility model can be made, and equivalents and modifications of some features of the utility model can be made without departing from the spirit and scope of the utility model.
Claims (6)
1. The aircraft skin opening frame positioning device comprises a base (1) and a bottom supporting block (2), wherein the bottom supporting block (2) is fixed above the base (1) and provides bottom support for a product;
the method is characterized in that: lateral support plates (3) are symmetrically arranged on the left side and the right side of the bottom support block (2), an attaching block (4) is arranged above the lateral support plates (3) and contacts with the surface of a product through the attaching block (4), an installation shaft (5) is fixed on the outer side of the attaching block (4), the attaching block (4) is rotatably connected with the lateral support plates (3) through the installation shaft (5), a first motor (6) is connected to the front side of the installation shaft (5) to control the rotation of the installation shaft (5), an adsorption port (7) is formed in the attaching block (4), the product is adsorbed through the adsorption port (7), the lower end of the adsorption port (7) is connected with the lateral support plates (3) through a flexible communicating pipe (9), a negative pressure cavity (10) is connected below the flexible communicating pipe (9), the inner space of the negative pressure cavity (10) is communicated with the adsorption port (7) through the flexible communicating pipe (9), the inside in negative pressure chamber (10) is provided with piston (11), and the below of piston (11) is fixed with transfer line (12) to the below of transfer line (12) is connected with vertical position control mechanism, can adjust the position of piston (11) in negative pressure chamber (10) through vertical position control mechanism, the below of side direction backup pad (3) is provided with horizontal position control mechanism, controls the horizontal position of side direction backup pad (3).
2. The aircraft skin opening frame positioning device of claim 1, wherein: a rubber pad (8) is bonded on the surface of the attaching block (4), so that the attaching tightness between the attaching block (4) and the surface of a product is improved.
3. The aircraft skin opening frame positioning device of claim 1, wherein: the vertical position control mechanism is connected with the control plate (13), and the movement of the two groups of transmission rods (12) is synchronously controlled through the movement of the control plate (13).
4. The aircraft skin opening frame positioning device according to claim 3, wherein: the vertical position control mechanism comprises a first adjusting rod (14) and a second motor (15);
the first adjusting rod (14) penetrates through the control plate (13) and is in threaded connection with the control plate (13), the first adjusting rod (14) is installed inside the bottom supporting block (2) in a bearing mode, and an up-and-down sliding structure is formed between the control plate (13) and the bottom supporting block (2);
and a second motor (15) installed at an end of the first adjusting lever (14) to provide a rotational driving force for the first adjusting lever (14).
5. The aircraft skin opening frame positioning device according to claim 1, wherein: the radial outer side surface of the piston (11) is attached to the inner wall of the negative pressure cavity (10), and an up-and-down sliding structure is formed between the piston (11) and the negative pressure cavity (10).
6. The aircraft skin opening frame positioning device of claim 1, wherein: the horizontal position control mechanism comprises a driving block (16), a second adjusting rod (17) and a third motor (18);
the driving block (16) is fixed below the lateral supporting plate (3), and a left-right sliding structure is formed between the driving block (16) and the base (1);
the second adjusting rod (17) penetrates through the driving block (16) and is in threaded connection with the driving block (16), the second adjusting rod (17) is a bidirectional threaded rod, and the second adjusting rod can drive the two groups of driving blocks (16) on the surface of the second adjusting rod to perform synchronous reverse movement when rotating;
and the third motor (18) is connected with the second adjusting rod (17) to provide rotary driving force for the second adjusting rod (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220545588.9U CN216803184U (en) | 2022-03-14 | 2022-03-14 | Aircraft skin mouth frame positioner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220545588.9U CN216803184U (en) | 2022-03-14 | 2022-03-14 | Aircraft skin mouth frame positioner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216803184U true CN216803184U (en) | 2022-06-24 |
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ID=82045717
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220545588.9U Active CN216803184U (en) | 2022-03-14 | 2022-03-14 | Aircraft skin mouth frame positioner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216803184U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115540791A (en) * | 2022-12-01 | 2022-12-30 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
-
2022
- 2022-03-14 CN CN202220545588.9U patent/CN216803184U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115540791A (en) * | 2022-12-01 | 2022-12-30 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
| CN115540791B (en) * | 2022-12-01 | 2023-03-14 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A positioning device for aircraft skin frame Effective date of registration: 20231218 Granted publication date: 20220624 Pledgee: Harbin Kechuang Financing Guarantee Co.,Ltd. Pledgor: Harbin Qiangli Aviation Industry Co.,Ltd. Registration number: Y2023230000107 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |