CN213164993U - Universal positioning tool for airplane structural parts - Google Patents
Universal positioning tool for airplane structural parts Download PDFInfo
- Publication number
- CN213164993U CN213164993U CN202021795415.XU CN202021795415U CN213164993U CN 213164993 U CN213164993 U CN 213164993U CN 202021795415 U CN202021795415 U CN 202021795415U CN 213164993 U CN213164993 U CN 213164993U
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- connecting plate
- universal
- adsorption device
- spring
- base
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Abstract
The utility model discloses a general location apparatus of aircraft structure, include: the support chassis, the connecting plate and the adsorption device; the connecting plate is rotatably connected with the supporting underframe through a rotating shaft, one end of the connecting plate is provided with a first screw rod, and the other end of the connecting plate is provided with a second screw rod; the first screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe, and the second screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe; a connecting rod is fixed in the middle of the connecting plate, the connecting rod and the connecting plate are perpendicular to each other, and one end, far away from the connecting plate, of the connecting rod is fixed with the adsorption device; the adsorption device comprises a base and a fence part which surrounds and is fixed on the base; the base is provided with a vacuum suction hole; the rail portion includes a plurality of sponge layers stacked together. The utility model has the advantages that: the clamping angle can be adjusted.
Description
Technical Field
The utility model relates to an aircraft structure field, concretely relates to general location apparatus of aircraft structure.
Background
The structural members of the airplane are important components for forming the skeleton and the aerodynamic shape of the airplane body, and have various varieties, complex shapes and different materials. In order to reduce the weight, various complicated cavities are formed in the structural member in strength design, and the structural member is likely to be deformed.
The traditional technology has the following technical problems:
the universal positioning tool for the aircraft structural part is largely used in the machining process of the aircraft structural part, and the clamping angle cannot be adjusted when the existing universal positioning tool for the aircraft structural part and the aircraft structural part clamps the aircraft structural part.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide a general location apparatus of aircraft structure can carry out the adjustment of centre gripping angle.
In order to solve the technical problem, the utility model provides a general location apparatus of aircraft structure spare, include: the support chassis, the connecting plate and the adsorption device; the connecting plate is rotatably connected with the supporting underframe through a rotating shaft, one end of the connecting plate is provided with a first screw rod, and the other end of the connecting plate is provided with a second screw rod;
the first screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe, and the second screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe;
a connecting rod is fixed in the middle of the connecting plate, the connecting rod and the connecting plate are perpendicular to each other, and one end, far away from the connecting plate, of the connecting rod is fixed with the adsorption device;
the adsorption device comprises a base and a fence part which surrounds and is fixed on the base; the base is provided with a vacuum suction hole; the rail portion includes a plurality of sponge layers stacked together.
The utility model has the advantages that:
the clamping angle can be adjusted.
In one embodiment, a first spring and a second spring are arranged between the connecting plate and the supporting chassis, and the first spring and the second spring are respectively positioned on two sides of the connecting plate.
In one embodiment, a protractor is arranged on the supporting chassis.
In one embodiment, the connecting rod is provided with a pointer.
In one embodiment, a metal plate is disposed between adjacent sponge layers.
In one embodiment, a plastic plate is disposed between adjacent foam layers.
In one embodiment, the thickness of the rail portion is 3 to 5 cm.
In one embodiment, the number of sponge layers is 3 to 5.
In one embodiment, the diameter of the vacuum suction hole is 3 to 5 cm.
In one embodiment, the support chassis is made of stainless steel material.
Drawings
Fig. 1 is a schematic structural view of the universal positioning tool for aircraft structural members of the present invention.
Fig. 2 is a schematic structural view of the adsorption device in the universal positioning tool for aircraft structural members of the present invention.
Fig. 3 is a cross-sectional view of fig. 2.
Detailed Description
The present invention is further described with reference to the following drawings and specific embodiments so that those skilled in the art can better understand the present invention and can implement the present invention, but the embodiments are not to be construed as limiting the present invention.
Referring to fig. 1 to 3, a universal positioning tool for an aircraft structural member comprises: a support chassis 100, a connection plate 200, and an adsorption device; the connecting plate is rotatably connected with the supporting underframe through a rotating shaft 230, one end of the connecting plate is provided with a first screw 210, and the other end of the connecting plate is provided with a second screw 220;
the first screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe, and the second screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe;
a connecting rod 240 is fixed in the middle of the connecting plate, the connecting rod and the connecting plate are perpendicular to each other, and one end of the connecting rod, which is far away from the connecting plate, is fixed with the adsorption device;
the adsorption device 300 includes a base 310 and a fence portion surrounding and fixed to the base; the base is provided with a vacuum suction hole 311; the rail portion includes a plurality of sponge layers 321 stacked together.
The utility model has the advantages that:
the clamping angle can be adjusted. Specifically, the angle of the connecting plate can be changed by changing the depth of the first screw and the second screw for connecting and supporting the underframe, so that the change of the angle of the adsorption device is further driven. When the adsorption device is used, only the vacuum pump is needed to be connected with the adsorption holes through the pipeline, the elastic deformation of the sponge layer can compensate the unevenness of the surface of the aircraft structural part, so that the surface of the sponge layer can be well attached to the aircraft structural part, the vacuum leakage is prevented, and the aircraft structural part is more reliably absorbed.
In one embodiment, a first spring 121 and a second spring 122 are disposed between the connecting plate and the supporting chassis, and the first spring and the second spring are respectively disposed at two sides of the connecting plate. Therefore, the first spring and the second spring can bring supporting force to the connecting plate, and the service life of the supporting plate is prolonged.
In one embodiment, a protractor 110 is provided on the support chassis. In one embodiment, the connecting rod is provided with a pointer 241. The angle gauge is arranged on the supporting underframe, and the pointer is correspondingly arranged on the connecting rod, so that the rotating angle of the adsorption device can be conveniently known.
In one embodiment, a metal plate 322 is disposed between adjacent sponge layers.
In one embodiment, a plastic plate is disposed between adjacent foam layers.
Wherein, the sponge layer has certain flexibility, can carry out the compression of all directions. During the adsorption process, the direction of the aircraft structural part sucked by the suction disc is expected to deform, but the direction perpendicular to the direction of the aircraft structural part sucked by the suction disc, namely the lateral direction, is not expected to deform, and the phenomenon is prevented by arranging a metal plate or a plastic plate between the adjacent sponge layers.
In one embodiment, the thickness of the rail portion is 3 to 5 cm. In one embodiment, the number of sponge layers is 3 to 5. In one embodiment, the diameter of the vacuum suction hole is 3 to 5 cm. In one embodiment, the support chassis is made of stainless steel material.
The above-mentioned embodiments are merely preferred embodiments for fully illustrating the present invention, and the scope of the present invention is not limited thereto. Equivalent substitutes or changes made by the technical personnel in the technical field on the basis of the utility model are all within the protection scope of the utility model. The protection scope of the present invention is subject to the claims.
Claims (10)
1. A universal positioning kit for an aircraft structural member, comprising: the support chassis, the connecting plate and the adsorption device; the connecting plate is rotatably connected with the supporting underframe through a rotating shaft, one end of the connecting plate is provided with a first screw rod, and the other end of the connecting plate is provided with a second screw rod;
the first screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe, and the second screw penetrates through the connecting plate and then is in threaded fit with the supporting underframe;
a connecting rod is fixed in the middle of the connecting plate, the connecting rod and the connecting plate are perpendicular to each other, and one end, far away from the connecting plate, of the connecting rod is fixed with the adsorption device;
the adsorption device comprises a base and a fence part which surrounds and is fixed on the base; the base is provided with a vacuum suction hole; the rail portion includes a plurality of sponge layers stacked together.
2. An aircraft structural member universal locating fixture as claimed in claim 1, wherein a first spring and a second spring are provided between the connection plate and the support chassis, the first spring and the second spring being located on either side of the connection plate.
3. The universal positioning kit for an aircraft structural member of claim 1, wherein a protractor is provided on said support chassis.
4. A universal positioning kit for an aircraft structural member as claimed in claim 3, wherein the connector bar is provided with a pointer.
5. The universal aircraft structure locating tool as claimed in claim 1, wherein a metal plate is disposed between adjacent foam layers.
6. The universal aircraft structure locating tool of claim 1, wherein a plastic panel is disposed between adjacent foam layers.
7. The universal aircraft structure locating tool of claim 1, wherein the rail portion has a thickness of 3 to 5 cm.
8. The universal aircraft structure locating tool of claim 1, wherein the number of sponge layers is 3 to 5.
9. The universal aircraft structure locating tool as claimed in claim 1, wherein the diameter of the vacuum suction hole is 3 to 5 cm.
10. The universal aircraft structure locating tool of claim 1, wherein the support chassis is made of stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021795415.XU CN213164993U (en) | 2020-08-25 | 2020-08-25 | Universal positioning tool for airplane structural parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021795415.XU CN213164993U (en) | 2020-08-25 | 2020-08-25 | Universal positioning tool for airplane structural parts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213164993U true CN213164993U (en) | 2021-05-11 |
Family
ID=75767508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021795415.XU Active CN213164993U (en) | 2020-08-25 | 2020-08-25 | Universal positioning tool for airplane structural parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213164993U (en) |
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2020
- 2020-08-25 CN CN202021795415.XU patent/CN213164993U/en active Active
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