CN221694997U - Multifunctional stamping, trimming, forging and pressing compound die for rotor hubs of multiple aircraft - Google Patents
Multifunctional stamping, trimming, forging and pressing compound die for rotor hubs of multiple aircraft Download PDFInfo
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- CN221694997U CN221694997U CN202420574150.2U CN202420574150U CN221694997U CN 221694997 U CN221694997 U CN 221694997U CN 202420574150 U CN202420574150 U CN 202420574150U CN 221694997 U CN221694997 U CN 221694997U
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- aircraft rotor
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- 150000001875 compounds Chemical class 0.000 title claims abstract description 23
- 238000005242 forging Methods 0.000 title claims abstract description 18
- 238000009966 trimming Methods 0.000 title claims description 8
- 238000003825 pressing Methods 0.000 title description 6
- 238000005520 cutting process Methods 0.000 claims abstract description 33
- 238000004080 punching Methods 0.000 claims abstract description 18
- 238000000034 method Methods 0.000 claims abstract description 14
- 239000002131 composite material Substances 0.000 claims abstract description 4
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 238000013329 compounding Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000007599 discharging Methods 0.000 description 11
- 238000012937 correction Methods 0.000 description 7
- 229910001234 light alloy Inorganic materials 0.000 description 5
- 238000012545 processing Methods 0.000 description 4
- 238000007906 compression Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 238000005056 compaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
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Abstract
A multi-functional multi-piece aircraft rotor hub die-cut, swage-correct, composite mold comprising: the upper die comprises a lower large plate, an upper large plate, a plurality of punches, a plurality of cutting edges, an upper stripper and a lower die, wherein the lower large plate and the upper large plate are connected with the guide sleeve through guide posts in sliding fit, the punches are fixedly connected with the upper large plate and used for punching shaft holes, the cutting edges are used for cutting burrs, the lower die is fixedly connected with the lower large plate, a plurality of groups of upper stripper plates and lower dies are arranged between the lower large plate and the upper large plate in parallel, and the lower molded surface of the upper stripper plate and the upper molded surface of the lower die are formed to be in profiling with the contact surface of a forging piece of an aircraft rotor hub. The compound die can be suitable for the existing press, a plurality of clamping jaws of the robot are designed on the rotor hub of the aircraft to grasp the process boss, so that the robot can grasp the rotor hub of the aircraft once, the production stability can be ensured, and the production efficiency is improved.
Description
Technical Field
The utility model relates to a mould, specifically speaking are many aircraft rotor hubs of a multifunctional aircraft punching, cutting, press correction and forge the compound die.
Background
The common trimming, shaft hole and press correction processing technology of the rotor hub of the aircraft is finished through the working procedures of a mechanical processing machine tool, so that the time and the labor are wasted, and the equipment cost is high.
Disclosure of utility model
In order to solve the problems, the utility model aims to provide the multifunctional multi-piece aircraft rotor hub punching, trimming, forging and pressing compound die which can simultaneously complete multi-piece trimming, shaft hole punching and pressing compound work and improve the production efficiency.
According to one aspect of the present utility model, there is provided a multi-functional multi-piece aircraft rotor hub die cut, swage, compound die comprising: the upper die comprises a lower large plate, an upper large plate, a plurality of punches, a plurality of cutting edges, an upper stripper and a lower die, wherein the lower large plate and the upper large plate are connected with the guide sleeve through guide posts in sliding fit, the punches are fixedly connected with the upper large plate and used for punching shaft holes, the cutting edges are used for cutting burrs, the lower die is fixedly connected with the lower large plate, a plurality of groups of upper stripper plates and lower dies are arranged between the lower large plate and the upper large plate in parallel, and the lower molded surface of the upper stripper plate and the upper molded surface of the lower die are formed to be in profiling with the contact surface of a forging piece of an aircraft rotor hub.
Preferably, the lower profile of the upper stripper plate is formed with a profile corresponding to a process boss formed at the upper end of the aircraft rotor hub blank for robotic grasping.
Preferably, the upper large plate is connected with a fixed base plate through a fixed bolt I, and each cutting edge is respectively connected below the upper large plate and the fixed base plate.
Preferably, the upper stripper plate is connected below the upper large plate and the fixed base plate through a fixing bolt I and a discharging spring, and the discharging spring passes through the fixing bolt I and is arranged between the lower part of the fixed base plate and the upper stripper plate, and the fixing bolt I is arranged in a bolt hole penetrating through the upper large plate.
Preferably, each punch is fixed in the upper large plate and the fixed backing plate.
Preferably, a lower die support post is provided between the lower die and the lower large plate.
Preferably, the die-cut, die-corrected and die-forged composite die for the rotor hub of the multifunctional multi-piece aircraft further comprises: the lifting device is arranged on the upper large plate in a penetrating way, and comprises a lifting device connecting plate, a lower connecting supporting plate connected with the lifting device connecting plate and a lower flash discharging tray.
Preferably, the lower connecting pallet is connected with the lower flash discharge tray via the connecting plate I.
Preferably, the ram comprises an edge ram and a center ram for punching an edge hole and a center hole, respectively, of an aircraft rotor hub.
According to the multifunctional multi-piece aircraft rotor hub punching, cutting, correcting and forging compound die, the die is suitable for an existing press, a robot clamping jaw grabbing process boss is designed on the aircraft rotor hub, multiple pieces are grabbed by a robot at one time, production stability can be guaranteed, and production efficiency is improved.
Drawings
Figure 1 is a schematic view of a forged aircraft rotor hub blank.
Figure 2 is a schematic cross-sectional view of an aircraft rotor hub forging blank.
Fig. 3 is a schematic drawing of a die-cut, swaged, compound mold (upper and lower mold closed state) for a rotor hub of a multi-functional aircraft.
Fig. 4 is a schematic drawing of a die-cut, swaged, composite mold (upper and lower mold open) for a rotor hub of a multi-functional aircraft.
Fig. 5 is a schematic diagram of the lower die layout distribution of a multi-functional multi-piece aircraft rotor hub die-cut, swaged and swaged compound die.
Detailed Description
Exemplary embodiments of the present utility model are described in detail below with reference to the attached drawings. The exemplary embodiments described below and illustrated in the drawings are intended to teach the principles of the present utility model to enable one skilled in the art to make and use the present utility model in a number of different environments and for a number of different applications. The scope of the utility model is therefore defined by the appended claims, and the exemplary embodiments are not intended, and should not be considered, as limiting the scope of the utility model. Moreover, for ease of description, where like elements are designated by like or similar reference numerals throughout the drawings, the dimensions of the various illustrated portions are not necessarily drawn to actual scale, and references to orientation or positional relationships, such as upper, lower, left, right, top, bottom, etc., are based on the orientation or positional relationships shown in the drawings, are merely for ease of describing the utility model and to simplify the description, and do not indicate or imply that the apparatus or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore are not to be construed as limiting the utility model. The following description of the embodiments emphasizes the differences between the embodiments, and the same or similar features may be referred to each other, so that technical features in the different embodiments may be freely combined to form further embodiments according to design needs for brevity and not described in detail.
According to the utility model, a multifunctional multi-piece aircraft rotor hub punching, cutting, correcting and forging compound die (hereinafter also referred to as compound die) can be used in a compound mode, or each function can be used independently, so that the effect of one die with multiple functions is realized, and the multifunctional multi-piece aircraft rotor hub punching, cutting, correcting and forging compound die comprises the following components: the upper large plate 1, the fixing bolt I2, the punch I3, the punch III 6 (a group of 6 and 8 groups), the discharging spring 4 (a group of 4 and 8 groups), the punch II 5, the fixing base plate 7, the cutting edge I8, the upper discharging plate 9, the cutting edge II 10, the pin 11, the lower flash discharging tray 13 (left and right one respectively), the fixing bolt II 15, the lower die supporting upright post 16, the connecting plate I17, the lower connecting supporting plate 18 (left and right one respectively), the ejector connecting plate 19 (left and right one respectively), the lower large plate 20, the guide post 22, the guide sleeve 23 and the lower die 24.
Fig. 1 is a blank for making an aircraft rotor hub of a prior art product, which is formed by forging, internally forged, and has excellent performance. Fig. 1 shows a top view, a B-B sectional view, an A-A sectional view, and a perspective view, respectively, in order from left to right and from top to bottom. The process boss 25 for process flow transfer is designed at the upper end of the aircraft rotor hub blank, so that the purpose of grabbing a plurality of aircraft rotor hub blanks by one robot can be realized.
Fig. 2 shows in cross section a blank to be die-cut press-calibrated by means of a compound die to which the utility model is to be applied.
As shown in fig. 3, 4 and 5, an example of a compound die of 8 pieces is shown, 8 pieces of aircraft rotor hub blanks can be arranged between the lower large plate 20 and the upper large plate 1 in parallel between the lower die 24 and the upper discharge plate 9 respectively, and punching, pressing and correcting forging is carried out by adopting a punch i 3, a punch ii 5, a punch iii 6, a cutting edge i 8, a cutting edge ii 10 and the like respectively, so that the punching, pressing and correcting work can be finished by 8 punches simultaneously with 8 cutting edges at one time, and the production efficiency is improved.
The guide post 22 and the guide sleeve 23 which are slidably matched with each other are respectively connected to the lower large plate 20 and the upper large plate 1 through bolts. The upper large plate 1 is connected with the fixed base plate 7 through a fixed bolt I2, and the cutting edge I8 and the cutting edge II 10 are connected under the upper large plate 1 and the fixed base plate 7 through the fixed bolt I2. The upper stripper plate 9 is connected under the upper large plate 1 and the fixed base plate 7 through a fixed bolt I2 and a stripper spring 4, the stripper spring 4 passes through the fixed bolt I2 and is arranged between the lower part of the fixed base plate 7 and the upper stripper plate 9, and the fixed bolt I2 is arranged in a bolt hole penetrating through the upper large plate 1. The pin 11 is arranged in the cutting edge I8, the cutting edge II 10, the upper large plate 1 and the fixed base plate 7 to play a role in positioning. The punch I3, the punch II 5 and the punch III 6 are fixed in the upper large plate 1 and the fixed base plate 7.
A lower die supporting column 16 is arranged between the lower die 24 and the lower large plate 20, wherein the lower die 24 is connected with the lower die supporting column 16 through a fixing bolt II 15, the lower die supporting column 16 is connected onto the lower large plate 20 through a fixing bolt II 15, the lower flash discharging tray 13 is connected onto a connecting plate I17 through a fixing bolt II 15, and the connecting plate I17 is in threaded connection with a lower connecting supporting plate 18. The lower connection pallet 18 is connected with a lifter connection plate 19 (one on each of left and right sides) which is arranged in a vertically movable manner on the lower large plate 20. 4 guide posts 22 are arranged on the lower large plate 20 through bolts, and 4 guide sleeves 23 are arranged below the upper large plate 1 through bolts.
The upper and lower profiles of the upper and lower discharge plates 9 and 24 are required to be subjected to profiling numerical control processing with the forging contact surface of the aircraft rotor hub 12, compaction is guaranteed, the cutting edges I8 and 10 and the lower flash discharge tray 13 are required to be subjected to profiling numerical control processing with the forging contact surface of the aircraft rotor hub 12, the quality of punched parts can be guaranteed along with the shape of products, and deformation of the forging of the aircraft rotor hub 12 in the punching and press correction processes is prevented.
Because of the relatively large size and profile of the aircraft rotor hub 12, this creates a difficult, i.e., non-grabbing, problem for one robot to grab multiple aircraft rotor hubs. In order to grasp a plurality of aircraft rotor hubs in an effective clamping jaw space, a robot clamping jaw grasping process boss 25 for process flow transfer is specially designed on an aircraft rotor hub blank as a grasping process jaw so as to achieve the aim of grasping a plurality of aircraft rotor hub blanks by one robot.
In this way, multiple groups of upper stripper plates 9 and lower dies 24 are arranged in parallel between the lower large plate 20 and the upper large plate 1, and 4 or 8 trimming and punching combined works can be completed simultaneously in a one-die-multiple-piece mode. One die 8 pieces are used for simultaneously cutting off the forging flash and punching the shaft hole for one time to complete the press correction and the combination, so that the time and the labor can be saved, the equipment can be saved, the cost can be reduced, and the efficiency can be improved. Meanwhile, the upper surface of the upper stripper plate 9 and the lower surface of the lower die 24 can be subjected to micro-correction and micro-compression according to the requirements. The lower profile of the upper stripper plate 9 is formed with a profile corresponding to the process boss 25.
When the whole upper die of the upper large plate 1, the upper discharging plate 9 and the cutting edge II 10 is in an upper state, the robot clamping jaw can grasp 8 aircraft rotor hub blanks at the positioning position by grabbing 8 aircraft rotor hub blanks, and the robot can grasp the process boss 25.
The robot clamping jaw leaves after putting 8 light alloy aircraft rotor hub blanks on lower mould 24, and then the press slider drives big board 1 to descend and drives drift I3, drift II 5, drift III 6, go up stripper 9 and blade I8, blade II 10 and descend, go up stripper 9 compaction press correction formula light alloy aircraft rotor hub blanks, and big board 1 continues to descend and drives drift I3, drift II 5, drift III 6 continues to descend, and discharge spring 4 is compressed simultaneously.
Thus, the punch I3, the punch II 5 and the punch III 6 start to punch, the cutting edge I8 and the cutting edge II 10 start to cut off the flash 14 of the rotor hub blank of the light alloy aircraft until the stop of the work is completed until the limit is completed, and the scraps 21 punched by the punch I3, the punch II 5 and the punch III 6 fall from the lower die 24.
Meanwhile, the upper surface of the upper discharging plate 9 and the lower surface of the lower die 24 can be subjected to micro-correction and micro-compression on the upper surface of the rotor hub blank, and the effect of one die with multiple functions can be achieved.
After the work is finished, the press slide block of the equipment press drives the upper large plate 1 to move upwards, drives the punch I3, the punch II 5, the punch III 6 and the upper stripper 9 to move upwards, and the punched light alloy aircraft rotor hub blank is ejected out of the punch I3, the punch II 5 and the punch III 6 under the compression force of the unloading spring 4 connected with the upper stripper 9.
The robot hand clamping jaw takes away the light alloy aircraft rotor hub blank after the operation and leaves, and simultaneously the cut flash 14 is jacked up under the jacking action of a lower ejector of the press, namely, an ejector rod (not shown) of the press jacks up the ejector connecting plate 19, and under the driving of the ejector connecting plate 19, the connecting support plate 18, the connecting plate I17 connected with the connecting plate and the lower flash discharging tray 13 jack up the flash 14, so that the flash 14 is ejected out of the lower flash discharging tray 13 from the lower die 24, and the work is completed. The flash 14 is removed by a separate gripping device.
The next set of work-piece work-cycles may then be cycled to accomplish the task.
The description has been made above with reference to the arrangement of fig. 3 in which the punch i 3 and the punch iii 6 constitute a group of 6 and 8 in total, serving as an edge punch for punching the edge hole. The punches ii 5 constitute a group of 1 and 8 in total, and serve as a center punch for punching a center hole. The cutting edges I8 and II 10 adopt the same structure, and any one of the cutting edges used for cutting flash is arranged between every two groups.
In the description of the present utility model, the meaning of "a plurality" is two or more, unless explicitly defined otherwise. Unless specifically stated or limited otherwise, the terms "mounted," "connected," "secured" and the like should be construed broadly, as they may be fixed, removable, or integral, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances. While the utility model has been described with reference to various specific embodiments, it should be understood that numerous changes could be made within the spirit and scope of the inventive concepts described. Accordingly, it is intended that the utility model not be limited to the described embodiments, but that it have the full scope defined by the language of the following claims.
Claims (9)
1. A multi-functional multi-piece aircraft rotor hub die-cut, swage-correct, compound die comprising: the rotor hub comprises a lower large plate (20) and an upper large plate (1) which are connected with a guide sleeve (23) through a guide post (22) in sliding fit, a plurality of punches which are fixedly connected with the upper large plate (1) and used for punching shaft holes, a plurality of cutting edges which are used for cutting burrs, an upper stripper plate (9) and a lower die (24) which is fixedly connected with the lower large plate (20), wherein a plurality of groups of upper stripper plates (9) and lower dies (24) are arranged between the lower large plate (20) and the upper large plate (1) in parallel, and the lower molded surface of the upper stripper plate (9) and the upper molded surface of the lower die (24) are formed to be in profile modeling with the forged piece contact surface of the rotor hub of the aircraft.
2. The multifunctional multi-piece aircraft rotor hub stamping, stamping and compounding die is characterized in that the lower profile of the upper stripper plate (9) is provided with a profile corresponding to a process boss (25), and the process boss (25) is formed at the upper end of an aircraft rotor hub blank for robotic grasping.
3. The multifunctional multi-piece aircraft rotor hub punching, cutting, trimming and forging compound die according to claim 1 is characterized in that the upper large plate (1) is connected with a fixed base plate (7) through a fixed bolt I (2), and each cutting edge is respectively connected under the upper large plate (1) and the fixed base plate (7).
4. A multifunctional multi-piece aircraft rotor hub die-cut stamping and forging compound die according to claim 3, characterized in that the upper stripper plate (9) is connected under the upper large plate (1) and the fixed backing plate (7) by a fixing bolt i (2) and a stripper spring (4), the stripper spring (4) is placed between the lower and upper stripper plates (9) under the fixed backing plate (7) through the fixing bolt i (2), and the fixing bolt i (2) is arranged in a bolt hole penetrating through the upper large plate (1).
5. A multifunctional multi-piece aircraft rotor hub die-cut, swage-swage compound die according to claim 3, wherein each ram is fixed in the upper large plate (1) and the fixed bolster (7).
6. The multi-function, multi-piece aircraft rotor hub die-cut, swage-swage compound die of claim 1, wherein a lower die support post (16) is disposed between the lower die (24) and the lower large plate (20).
7. The multi-function multi-piece aircraft rotor hub die-cut, die-cast, composite mold of claim 1, further comprising: the lifting device is characterized by comprising a liftout device connecting plate (19) which is arranged on the lower large plate (20) in a penetrating manner, a lower connecting supporting plate (18) which is connected with the liftout device connecting plate (19) and a lower flash unloading tray (13).
8. The multifunctional multi-piece aircraft rotor hub die-cut trimming and forging compound die according to claim 7, characterized in that the lower connecting pallet (18) is connected with the lower flash discharge tray (13) via the connecting plate i (17).
9. The multi-function multi-piece aircraft rotor hub die-cut, swage-swage compound die of claim 1, wherein the ram comprises an edge ram and a center ram for die cutting an edge hole and a center hole of an aircraft rotor hub, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202420574150.2U CN221694997U (en) | 2024-03-22 | 2024-03-22 | Multifunctional stamping, trimming, forging and pressing compound die for rotor hubs of multiple aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202420574150.2U CN221694997U (en) | 2024-03-22 | 2024-03-22 | Multifunctional stamping, trimming, forging and pressing compound die for rotor hubs of multiple aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221694997U true CN221694997U (en) | 2024-09-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202420574150.2U Active CN221694997U (en) | 2024-03-22 | 2024-03-22 | Multifunctional stamping, trimming, forging and pressing compound die for rotor hubs of multiple aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221694997U (en) |
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- 2024-03-22 CN CN202420574150.2U patent/CN221694997U/en active Active
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