CN213794359U - Based on aviation titanium alloy part perforating device - Google Patents
Based on aviation titanium alloy part perforating device Download PDFInfo
- Publication number
- CN213794359U CN213794359U CN202022663659.9U CN202022663659U CN213794359U CN 213794359 U CN213794359 U CN 213794359U CN 202022663659 U CN202022663659 U CN 202022663659U CN 213794359 U CN213794359 U CN 213794359U
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- fixed
- titanium alloy
- groove
- controller
- aviation
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 37
- 238000004080 punching Methods 0.000 claims abstract description 16
- 238000009434 installation Methods 0.000 claims description 8
- 238000001179 sorption measurement Methods 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 3
- 230000005611 electricity Effects 0.000 abstract description 4
- 230000008878 coupling Effects 0.000 abstract description 2
- 238000010168 coupling process Methods 0.000 abstract description 2
- 238000005859 coupling reaction Methods 0.000 abstract description 2
- 238000005260 corrosion Methods 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 244000025254 Cannabis sativa Species 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 229910002065 alloy metal Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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Abstract
The utility model relates to the technical field of punching devices, and discloses a punching device based on an aviation titanium alloy part, which comprises a base, wherein a processing groove is formed in the top of the base, and a fixed groove is formed in the opening at the top of the processing groove; the back of base is fixed with the mounting bracket, the front of mounting bracket is fixed with the module, the one end of module has the module motor through the coupling joint, the front of module is provided with the slider. This based on aviation titanium alloy part perforating device, pressure sensor of pressure head bottom can avoid causing work piece deformation and wearing and tearing because pressure is too big when fixing the work piece to pressure sensor and flexible motor all are connected through electric wire and master controller electricity, can make through the master controller press from both sides tight pressure control at appointed numerical value, ensure that clamping device is fixed can the steady operation many times.
Description
Technical Field
The utility model relates to a perforating device technical field specifically is a based on aviation titanium alloy part perforating device.
Background
Titanium alloy refers to a variety of alloy metals made from titanium and other metals. Titanium is an important structural metal developed in the 50 s of the 20 th century, and titanium alloy has high strength, good corrosion resistance and high heat resistance. In the 50-60 s of the 20 th century, warm titanium alloy for developing aeroengines and structural titanium alloy for engines are mainly developed. A batch of corrosion resistant titanium alloy was developed in the 70 s, and corrosion resistant titanium alloy and high titanium alloy were further developed in the 80 s. The titanium alloy is mainly used for manufacturing parts of an air compressor of an aircraft engine, and is a structural part of rockets, missiles and high-speed machines.
Because titanium alloy is light and high, further fixing is needed to be carried out on the workpiece in the process of punching the titanium alloy, however, the required precision of the aviation workpiece is high, the workpiece is deformed and abraded due to excessive clamping, and the existing punching device generally moves point positions manually, so that the precision of manually determining the point positions is low, and the quality of finished products cannot be guaranteed.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
To prior art's not enough among the above-mentioned background art, the utility model provides a based on aviation titanium alloy part perforating device to overcome the current based on aviation titanium alloy part perforating device that proposes in the above-mentioned background art, excessive clamp is tight can cause work piece deformation, wearing and tearing when processing aviation work piece, and the lower shortcoming of manual definite hole site precision.
(II) technical scheme
In order to achieve the above purpose, the utility model discloses a following technical scheme realizes:
a punching device based on an aviation titanium alloy part comprises a base, wherein a machining groove is formed in the top of the base, and a fixing groove is formed in an opening in the top of the machining groove;
the back of the base is fixedly provided with a mounting frame, the front of the mounting frame is fixedly provided with a module, one end of the module is connected with a module motor through a coupler, and the front of the module is provided with a sliding block;
a mounting plate is fixed on the front side of the sliding block, a perforating machine is fixed on the front side of the mounting plate, a perforating machine handle is arranged on one side of the perforating machine, and a drill bit is arranged on an output shaft of the perforating machine through a drill bit clamp;
a fixed block is fixed at the top of the base, an installation block is fixed at the top of the fixed block, a telescopic motor is fixed at the bottom of the installation block, and a pressure head is fixed at the bottom end of an output shaft of the telescopic motor;
the mounting groove has been seted up to one side of base, the interior diapire of mounting groove is provided with master controller and motor servo controller, one side activity of base is provided with the controller, one side of controller is provided with emergency stop button, first operating button and second operating button.
As an optimal technical solution of the utility model: the bottom of the pressure head is provided with a pressure groove;
a pressure sensor is fixed in the pressure groove and can control the clamping force, and the workpiece can be fixed while the workpiece is prevented from being deformed.
As an optimal technical solution of the utility model: an adsorption groove is formed in the other side of the controller;
the adsorption tank is internally fixed with a magnet, the controller is movably arranged on one side of the base through the magnet, and the controller is electrically connected with the main controller through an electric wire, so that the overall operation of the device is facilitated when the hole position is determined.
Further, a sensing head is arranged at the bottom of the pressure sensor;
the bottom of the sensing head extends to the opening of the pressure tank.
Furthermore, the number of the fixing grooves is two, and the two fixing grooves are symmetrically formed in the opening of the processing groove;
the number of the fixing blocks is two, and the two fixing blocks are fixed on two sides of the fixing groove in a symmetrical mode.
Furthermore, the number of the mounting blocks at the top of the single fixing block is at least two;
the mounting block is fixed above the fixing groove.
Furthermore, the controller, the pressure sensor, the perforating machine and the motor servo controller are all electrically connected with the main controller through electric wires;
the module motor is electrically connected with the motor servo controller through an electric wire.
The theory of operation, this based on aviation titanium alloy part perforating device, when needs use, at first be connected to the device to the power, then place the work piece in the fixed slot, push down through the flexible motor of controller control, after pushing down the head contact work piece, pressure sensor detects the pressure value, after the pressure value is arrived, the flexible motor of controller control stops to push down, accomplish fixedly, then through the operation of controller control module motor, the module motor passes through the slider and drives the puncher removal, reach the appointed position after, open the puncher through the controller, the puncher drives the drill bit rotation, push down the puncher handle at last, accomplish drilling.
The electrical components present in this document are all electrically connected to a master controller within the device and to the 220V mains, and the master controller may be a conventional known device which is controlled by a computer or the like.
The relevant modules referred to in the present application are all hardware system modules or functional modules combining computer software programs or protocols with hardware in the prior art, and the computer software programs or protocols referred to by the functional modules are all known in the art per se, and are not improvements of the present application; the improvement of the application is the interaction relation or the connection relation among all the modules, namely, the integral structure of the system is improved, so as to solve the corresponding technical problems to be solved by the application.
(III) advantageous effects
The utility model provides a based on aviation titanium alloy part perforating device possesses following beneficial effect:
(1) this based on aviation titanium alloy part perforating device, the pressure sensor of pressure head bottom can avoid causing work piece deformation and wearing and tearing because pressure is too big when fixing the work piece to pressure sensor and flexible motor all are connected through electric wire and master controller electricity, can make through the master controller press from both sides tight pressure control at appointed numerical value, ensure that clamping device is fixed can the steady operation many times.
(2) This based on aviation titanium alloy part perforating device can remove at will through the controller that electric wire and master controller electricity are connected, is convenient for remove the puncher when confirming the hole site to remove through controller control module group motor, can make the hole site more accurate.
Drawings
FIG. 1 is a schematic front view of the punching device for aviation titanium alloy parts of the present invention;
fig. 2 is a schematic view of a three-dimensional structure of a first viewing angle of the aviation titanium alloy part perforating device according to the present invention;
fig. 3 is a schematic perspective view of a second viewing angle of the aviation titanium alloy part perforating device according to the present invention;
FIG. 4 is a schematic side view of the punching device for aviation titanium alloy parts of the present invention;
FIG. 5 is a schematic structural diagram of a pressure head of the aviation titanium alloy part perforating device;
FIG. 6 is a schematic structural diagram of the controller of the aviation titanium alloy part perforating device according to the present invention;
fig. 7 is a program control diagram of the aviation titanium alloy part perforating device.
In the figure: the punching machine comprises a base 1, a machining groove 101, a fixing groove 102, a mounting groove 103, a mounting frame 2, a module 3, a module motor 301, a sliding block 302, a mounting plate 4, a punching machine 5, a punching machine handle 501, a drilling bit 6, a fixing block 7, a mounting block 8, a telescopic motor 9, a pressure head 10, a pressure groove 1001, a controller 11, an adsorption groove 1101, an emergency stop button 1102, a first operating button 1103, a second operating button 1104, a master controller 12, a motor servo controller 13, a pressure sensor 14, a sensing head 1401 and a magnet 15.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
Referring to fig. 1-7, the present invention provides a punching device for titanium alloy parts based on aviation;
as shown in fig. 1 and 2, the device comprises a base 1, wherein a processing groove 101 is formed in the top of the base 1, a fixing groove 102 is formed in an opening in the top of the processing groove 101, a mounting frame 2 is fixed on the back of the base 1, a module 3 is fixed on the front of the mounting frame 2, one end of the module 3 is connected with a module motor 301 through a coupling, and a mounting plate 4 is arranged on the front of the module 3;
a perforating machine 5 is fixed on the front surface of the mounting plate 4, a perforating machine handle 501 is arranged on one side of the perforating machine 5, and an output shaft of the perforating machine 5 is provided with a drill bit 6 through a drill bit clamp;
the top of the base 1 is fixedly provided with two fixed blocks 7, the two fixed blocks 7 are symmetrically fixed on two sides of the fixed groove 102, the top of each fixed block 7 is fixedly provided with an installation block 8, the number of the installation blocks 8 on the top of each fixed block 7 is at least two, the installation blocks 8 are fixed above the fixed groove 102, the bottom of each installation block 8 is fixedly provided with a telescopic motor 9, and the bottom end of an output shaft of each telescopic motor 9 is fixedly provided with a pressure head 10;
according to the fig. 3 and 4, one side of the base 1 is provided with a mounting groove 103, the inner bottom wall of the mounting groove 103 is provided with a main controller 12 and a motor servo controller 13, one side of the base 1 is movably provided with a controller 11, and one side of the controller 11 is provided with an emergency stop button 1102, a first operating button 1103 and a second operating button 1104;
according to the illustration in fig. 5, a pressure groove 1001 is formed at the bottom of the indenter 10, a pressure sensor 14 is fixed inside the pressure groove 1001, a sensing head 1401 is arranged at the bottom of the pressure sensor 14, and the bottom of the sensing head 1401 extends to the opening of the pressure groove 1001;
as shown in fig. 6, an adsorption groove 1101 is formed on the other side of the controller 11, and a magnet 15 is fixed in the adsorption groove 1101;
according to the illustration in fig. 7, the controller 11, the pressure sensor 14, the hole puncher 5 and the motor servo controller 13 are all electrically connected with the main controller 12 through electric wires, and the module motor 301 is electrically connected with the motor servo controller 13 through electric wires;
as shown in fig. 5, a preferred embodiment of the present invention is: when the pressure sensor 14 at the bottom of the pressure head 10 is used for fixing a workpiece, the workpiece deformation and abrasion caused by overlarge pressure can be avoided, the pressure sensor 14 and the telescopic motor 9 are electrically connected with the main controller 12 through electric wires, the clamping pressure can be controlled at an appointed value through the main controller 12, and the pressure sensor 14 ensures that the clamping device can be fixed and can stably run for many times;
as shown in fig. 6, a preferred embodiment of the present invention is: controller 11 through electric wire and the electricity of master controller 12 is connected can remove at will, can adsorb the arbitrary position at the device through magnet 15, is convenient for remove and operate to control module motor 301 through controller 11 and remove, can make the hole site more accurate.
It should be noted that, in the present invention, unless explicitly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "fixed" are to be understood in a broad sense, and may be, for example, either fixedly or detachably connected; or indirectly through an intermediary. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Above pressure grass, only be the concrete implementation of the preferred embodiment of the present invention, nevertheless the utility model discloses a protection scope is not limited to this, and any technical personnel who is familiar with this technical field are in the technical scope of the utility model discloses an according to the technical scheme of the utility model and the utility model design equivalence replacement or change, all should be covered within the protection scope of the utility model.
Claims (7)
1. The utility model provides a based on aviation titanium alloy part perforating device, includes base (1), its characterized in that: a processing groove (101) is formed in the top of the base (1), and a fixing groove (102) is formed in an opening in the top of the processing groove (101);
the back of the base (1) is fixedly provided with a mounting rack (2), the front of the mounting rack (2) is fixedly provided with a module (3), one end of the module (3) is connected with a module motor (301) through a coupler, and the front of the module (3) is provided with a sliding block (302);
a mounting plate (4) is fixed on the front surface of the sliding block (302), a punching machine (5) is fixed on the front surface of the mounting plate (4), a punching machine handle (501) is arranged on one side of the punching machine (5), and a drill bit (6) is arranged on an output shaft of the punching machine (5) through a drill bit clamp;
a fixed block (7) is fixed to the top of the base (1), an installation block (8) is fixed to the top of the fixed block (7), a telescopic motor (9) is fixed to the bottom of the installation block (8), and a pressure head (10) is fixed to the bottom end of an output shaft of the telescopic motor (9);
mounting groove (103) have been seted up to one side of base (1), the interior diapire of mounting groove (103) is provided with master controller (12) and motor servo controller (13), one side activity of base (1) is provided with controller (11), one side of controller (11) is provided with scram button (1102), first operating button (1103) and second operating button (1104).
2. The aviation-based titanium alloy part perforating device as claimed in claim 1, wherein: the bottom of the pressure head (10) is provided with a pressure groove (1001);
a pressure sensor (14) is fixed inside the pressure tank (1001).
3. The aviation-based titanium alloy part perforating device as claimed in claim 1, wherein: the other side of the controller (11) is provided with an adsorption tank (1101);
a magnet (15) is fixed in the adsorption groove (1101).
4. The aviation-based titanium alloy part perforating device as claimed in claim 2, wherein: the bottom of the pressure sensor (14) is provided with a sensing head (1401);
the bottom of the sensing head (1401) extends to the opening of the pressure tank (1001).
5. The aviation-based titanium alloy part perforating device as claimed in claim 1, wherein: the number of the fixing grooves (102) is two, and the two fixing grooves (102) are symmetrically formed in the opening of the processing groove (101);
the number of the fixing blocks (7) is two, and the two fixing blocks (7) are fixed on two sides of the fixing groove (102) in a symmetrical mode.
6. The aviation-based titanium alloy part perforating device as claimed in claim 1, wherein: the number of the mounting blocks (8) on the top of the single fixing block (7) is at least two;
the mounting block (8) is fixed above the fixing groove (102).
7. The aviation titanium alloy part-based punching device as claimed in claim 1 or 2, wherein: the controller (11), the pressure sensor (14), the perforating machine (5) and the motor servo controller (13) are all electrically connected with the main controller (12) through electric wires;
the module motor (301) is electrically connected with the motor servo controller (13) through an electric wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022663659.9U CN213794359U (en) | 2020-11-17 | 2020-11-17 | Based on aviation titanium alloy part perforating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022663659.9U CN213794359U (en) | 2020-11-17 | 2020-11-17 | Based on aviation titanium alloy part perforating device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213794359U true CN213794359U (en) | 2021-07-27 |
Family
ID=76935144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022663659.9U Expired - Fee Related CN213794359U (en) | 2020-11-17 | 2020-11-17 | Based on aviation titanium alloy part perforating device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213794359U (en) |
-
2020
- 2020-11-17 CN CN202022663659.9U patent/CN213794359U/en not_active Expired - Fee Related
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210727 |