CN203031980U - Aircraft low-expansion alloy-steel composite material forming die - Google Patents
Aircraft low-expansion alloy-steel composite material forming die Download PDFInfo
- Publication number
- CN203031980U CN203031980U CN 201220717856 CN201220717856U CN203031980U CN 203031980 U CN203031980 U CN 203031980U CN 201220717856 CN201220717856 CN 201220717856 CN 201220717856 U CN201220717856 U CN 201220717856U CN 203031980 U CN203031980 U CN 203031980U
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- China
- Prior art keywords
- die
- composite material
- steel composite
- core
- expansion alloy
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses an aircraft low-expansion alloy-steel composite material forming die, relates to the technical field of machining dies, and in particular to a die used in the process of forming and processing aircraft low-expansion alloy-steel composite materials. The die comprises a lower die plate (1) and a die handle (8) mounted above the lower die plate (1). A flexible sleeve (3) is arranged above the lower die plate (1), and springs (2) are arranged between the lower periphery of the flexible sleeve (3) and the lower die plate (1). A core (4) is arranged in an inner hole of the flexible sleeve (3). An upper die plate (7) is arranged at the lower end of the die handle (8), and a female die (6) is arranged at the lower end face of the upper die plate (7). The female die (6) is located right above the core (4), and a to-be-processed alloy-steel composite material component is arranged on the core (4). By the aid of the aircraft low-expansion alloy-steel composite material forming die, defect of low efficiency of existing aircraft low-expansion alloy-steel composite material in the forming and processing process can be overcome.
Description
Technical field
The utility model relates to the machining technical field of mold, is specifically related to the mould that aircraft uses in processing and forming with the low-expansion alloy steel composite material.
Background technology
Low-expansion alloy steel mostly be applied to certain environment temperature require size approximate lazy fixed without device in.Mainly contain: precision instrument, instrument, the element in optical instrument, various resonators, the waveguide of microwave communication, the mould of Aeronautics and Astronautics industry composite material parts etc.
There is inefficient shortcoming in existing aircraft with the low-expansion alloy steel composite material in processing and forming.
The utility model content
The utility model provides aircraft low-expansion alloy steel composite material shaping mould, and the utility model has solved existing aircraft and had inefficient shortcoming with the low-expansion alloy steel composite material in processing and forming.
For addressing the above problem, the utility model adopts following technical scheme: aircraft low-expansion alloy steel composite material shaping mould comprises lower bolster 1 and the die shank 8 that is installed on lower bolster 1 top; Movable sleeve 3 is installed above lower bolster 1, between movable sleeve 3 periphery belows and lower bolster 1, is provided with spring 2, in movable sleeve 3 endoporus, be provided with core 4; Die shank 8 lower ends are equipped with cope match-plate pattern 7, die 6 are installed below cope match-plate pattern 7; Die 6 is positioned at directly over core 4, and alloy steel composite material element 5 to be processed is arranged at above core 4.
Be positioned at movable sleeve 3 sides and be provided with a supporter 11 on lower bolster 1, the hinged shift fork 10 in supporter 11 upper ends, shift fork 10 1 ends are hinged through vertical strip hole and the core 4 of movable sleeve 3 sides, the other end of shift fork 10 connects a connection cord 9, and connection cord 9 upper ends are fixedly connected with cope match-plate pattern 7.
Advantage of the present utility model: rational in infrastructure, be convenient to maintenance, production efficiency is high, and machining accuracy is high.
The accompanying drawing explanation
Fig. 1 is the utility model structural representation.
Symbol description in figure: lower bolster 1, spring 2, movable sleeve 3, core 4, alloy steel composite material element 5 to be processed, die 6, cope match-plate pattern 7, die shank 8, connection cord 9, shift fork 10, supporter 11.
The specific embodiment
below with best embodiment, the utility model is described in detail
.
As shown in Figure 1, aircraft low-expansion alloy steel composite material shaping mould, comprise lower bolster 1 and the die shank 8 that is installed on lower bolster 1 top; Movable sleeve 3 is installed above lower bolster 1, between movable sleeve 3 periphery belows and lower bolster 1, is provided with spring 2, in movable sleeve 3 endoporus, be provided with core 4; Die shank 8 lower ends are equipped with cope match-plate pattern 7, die 6 are installed below cope match-plate pattern 7; Die 6 is positioned at directly over core 4, and alloy steel composite material element 5 to be processed is arranged at above core 4.During use, die shank 8 is installed on the head of press, and lower bolster 1 is installed on the work top of press.
Be positioned at movable sleeve 3 sides and be provided with a supporter 11 on lower bolster 1, the hinged shift fork 10 in supporter 11 upper ends, shift fork 10 1 ends are hinged through vertical strip hole and the core 4 of movable sleeve 3 sides, the other end of shift fork 10 connects a connection cord 9, and connection cord 9 upper ends are fixedly connected with cope match-plate pattern 7.During use, pull connection cord 9, can make shift fork 10 rotate, shift fork 10 drives core 4 upwards, can upwards promote alloy steel composite material element 5 to be processed away from movable sleeve 3, thereby increase work efficiency.
Finally it should be noted that: obviously, above-described embodiment is only for the utility model example clearly is described, and is not the restriction to embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without also giving all embodiments.And the apparent variation of being amplified out thus or change are still among protection domain of the present utility model.
Claims (2)
1. aircraft low-expansion alloy steel composite material shaping mould, comprise lower bolster (1) and be installed on the die shank (8) of lower bolster (1) top; It is characterized in that, in lower bolster (1) top, movable sleeve (3) is installed, between movable sleeve (3) periphery below and lower bolster (1), be provided with spring (2), in movable sleeve (3) endoporus, be provided with core (4); Die shank (8) lower end is equipped with cope match-plate pattern (7), die (6) is installed below cope match-plate pattern (7); Die (6) is positioned at directly over core (4), and alloy steel composite material element to be processed (5) is arranged at above core (4).
2. aircraft low-expansion alloy steel composite material shaping mould as claimed in claim 1, it is characterized in that, be positioned at movable sleeve (3) side and be provided with a supporter (11) on lower bolster (1), the hinged shift fork in supporter (11) upper end (10), shift fork (10) one ends are hinged through vertical strip hole and the core (4) of movable sleeve (3) side, the other end of shift fork (10) connects a connection cord (9), and connection cord (9) upper end is fixedly connected with cope match-plate pattern (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220717856 CN203031980U (en) | 2012-12-24 | 2012-12-24 | Aircraft low-expansion alloy-steel composite material forming die |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220717856 CN203031980U (en) | 2012-12-24 | 2012-12-24 | Aircraft low-expansion alloy-steel composite material forming die |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203031980U true CN203031980U (en) | 2013-07-03 |
Family
ID=48684120
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220717856 Expired - Fee Related CN203031980U (en) | 2012-12-24 | 2012-12-24 | Aircraft low-expansion alloy-steel composite material forming die |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203031980U (en) |
-
2012
- 2012-12-24 CN CN 201220717856 patent/CN203031980U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130703 Termination date: 20131224 |