CN204471045U - The little stress of weak rigidity aerospace component fills shock-absorbing mounting and clamping system - Google Patents
The little stress of weak rigidity aerospace component fills shock-absorbing mounting and clamping system Download PDFInfo
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- CN204471045U CN204471045U CN201520151548.6U CN201520151548U CN204471045U CN 204471045 U CN204471045 U CN 204471045U CN 201520151548 U CN201520151548 U CN 201520151548U CN 204471045 U CN204471045 U CN 204471045U
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- aerospace component
- fixture
- clamping system
- little stress
- absorbing mounting
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- 239000012530 fluid Substances 0.000 claims abstract description 9
- 239000000945 filler Substances 0.000 claims abstract description 6
- 238000010276 construction Methods 0.000 claims description 18
- 238000001125 extrusion Methods 0.000 claims description 9
- 238000003754 machining Methods 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 5
- 238000007711 solidification Methods 0.000 description 5
- 230000008023 solidification Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- 230000001427 coherent effect Effects 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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Abstract
The utility model relates to the process equipment field of aerospace component, particularly the little stress of a kind of weak rigidity aerospace component fills shock-absorbing mounting and clamping system, it comprises: fixture, it is close with aerospace component two ends match profiles, be arranged on the fixture at aerospace component length direction two ends, fixture outside is installed on the table; Supporter, its two ends are fixedly connected between the fixture at described aerospace component two ends, and supporter runs through aerospace component inside; Filler, it is the fluid that can solidify, the little stress of weak rigidity aerospace component of workman's learning cost of filling aerospace component inner space, goal of the invention of the present utility model is to provide a kind of and cuts down finished cost, improve working (machining) efficiency, reduce fills shock-absorbing mounting and clamping system.
Description
Technical field
The utility model relates to the process equipment field of aerospace component, and particularly the little stress of a kind of weak rigidity aerospace component fills shock-absorbing mounting and clamping system.
Background technology
In aerospace component, some is frame-type part, its poor rigidity, and machining can cause judder, even cannot process;
In prior art, to the solution technique of this problem be: adopt a large amount of fixture, for the part of different-stiffness, adopt different clamping scheme, simultaneously, cutting parameter is also supporting separately, and a complete scheme will be made, need to manufacture a large amount of fixtures, the position simultaneously clamped, contact area etc., need through long-term experience accumulation, or the finite element analysis of complexity, and after clamping, for the processing of structural member, because the rigidity at each position is different, so processing scheme is also need the experience accumulation through long-term, or the finite element analysis of complexity, all very conservative under normal circumstances, because the aerospace component rigidity of this frame-type is inadequate, vibrative words in processing, meeting error is very large,
As previously discussed, these techniques all can the serious processing cost that must increase aerospace component, and efficiency is very low simultaneously, and the learning cost of workman is also relatively high.
Utility model content
For prior art Problems existing, goal of the invention of the present utility model is to provide a kind of and cuts down finished cost, improve working (machining) efficiency, reduce the little stress of weak rigidity aerospace component of workman's learning cost fills shock-absorbing mounting and clamping system.
To achieve these goals, the technical solution adopted in the utility model is:
The little stress of a kind of weak rigidity aerospace component fills shock-absorbing mounting and clamping system, and it comprises:
Fixture, it is close with aerospace component two ends match profiles, is arranged on the fixture at aerospace component length direction two ends, and fixture outside is installed on the table;
Supporter, its two ends are fixedly connected between the fixture at described aerospace component two ends, and supporter runs through aerospace component inside;
Filler, it is the fluid that can solidify, and fills aerospace component inner space.
The system of the application in use, other fixtures various of the removing main clamp in prior art around aerospace component are directly cast out, two fixtures coordinated with aerospace component are installed at aerospace component two ends, described supporter is set between fixture, form the structure of main holding capacity, and the fluid after described solidification, fill full aerospace component inner space, at this moment the power on aerospace component framework is by the fluid after solidification, pass on described supporter, fluid after solidification instead of the fixture cast out, originally clamping from aerospace component outside, promote the mode of aerospace component rigidity, become from aerospace component inner support,
Remove a large amount of unnecessary fixtures, after having clamped, add man-hour, as long as the fluid rigidity after solidification reaches requirement simultaneously, no longer need the problem considering whether to vibrate, greatly reduce requirement during machining, also do not need complicated clamping, machining scheme, reduce great amount of cost, and use the processing technology after the application's system more simply too much than in the past, improve working (machining) efficiency, scheme is convenient easy to learn simultaneously, reduces workman's learning cost.
As preferred version of the present utility model, also comprise secondary supporting construction, its two ends coordinate with aerospace component two ends, and are fixed on described supporter, and described fixture gives its clamping at the outside two ends of aerospace component, described secondary supporting construction is at inner support aerospace component, secondary supporting construction is fixedly mounted on supporter simultaneously, and supporter is fixedly connected with fixture again, forms integrative-structure, after the fluid solidification of filling, make aerospace component rigidity larger more stable.
As preferred version of the present utility model, described supporter is strip extrusion, and structure is coherent symmetrical, and rigidity is large, more stable.
As preferred version of the present utility model, described secondary supporting construction interlude is extrusion, and two ends are airtight, and structure is coherent symmetrical, and rigidity is large, more stable.
As preferred version of the present utility model, described supporter is cylinder, and the junction of its two ends and described fixture is positioned in the geometric center of fixture and aerospace component contact surface, be fixture, supporter form load-carrying construction rigidity larger.
As preferred version of the present utility model, the contact surface of described secondary supporting construction two ends and aerospace component is regular hexagon, and symmetrical configuration, stability is strong.
As preferred version of the present utility model, described secondary supporting construction is hollow structure, and its interlude is regular hexagon extrusion.
The beneficial effects of the utility model are:
Cut down finished cost, improve working (machining) efficiency, reduce workman's learning cost.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is the secondary supporting construction schematic diagram of the utility model.
Fig. 3 is the utility model result of use figure.
Mark in figure: 1-supporter, 2-fixture, the secondary supporting construction of 3-, 4-mounting blocks, 5-workbench, 6-filler, 7-aerospace component.
Detailed description of the invention
Below in conjunction with embodiment and detailed description of the invention, the utility model is described in further detail.But this should be interpreted as that the scope of the above-mentioned theme of the utility model is only limitted to following embodiment, all technology realized based on summary of the invention of the present utility model all belong to scope of the present utility model.
embodiment 1
As Fig. 1-3, the little stress of a kind of weak rigidity aerospace component 7 fills shock-absorbing mounting and clamping system, and it comprises:
Fixture 2, its be with the structural member of aerospace component 7(the present embodiment as shown in Figure 3, frame-like structures part the most common in the weak rigid structural member of aviation field) conjunction of two ends match profiles, be arranged on the fixture 2 at aerospace component 7 length direction two ends, fixture 2 outside is arranged on workbench 5 and (diagonal outside fixture 2 is installed with the mounting blocks 4 of strip, be arranged on workbench 5 by mounting blocks 4), as Fig. 1, fixture 2 described in the present embodiment is rhombus, all arranges some clamping holes above;
Supporter 1, its two ends are fixedly connected between the fixture 2 at described aerospace component 7 two ends, and it is inner that supporter 1 runs through aerospace component 7, and described supporter 1 is strip extrusion, is cylinder in the present embodiment;
Filler 6, it is the fluid that can solidify, and fill aerospace component 7 inner space, as shown in Figure 3, aerospace component 7 is frame-like structures part, and filler 6 fills up its inner space;
Secondary supporting construction 3, its two ends coordinate with aerospace component 7 two ends, and be fixed on described supporter 1, described secondary supporting construction 3 interlude is extrusion, and two ends are airtight, as shown in Figure 2, the face that secondary supporting construction 3 two ends coordinate with aerospace component 7 is regular hexagon, symmetrical configuration is more stable, and rigidity is larger, improves machining accuracy.
In the present embodiment, described supporter 1 is cylinder, the junction of its two ends and described fixture 2 is positioned at fixture 2 with in the geometric center of aerospace component 7 contact surface, the contact surface of described secondary supporting construction 3 two ends and aerospace component 7 is regular hexagon, described secondary supporting construction 3 is hollow structure, and its interlude is regular hexagon extrusion.
Claims (7)
1. the little stress of weak rigidity aerospace component fills a shock-absorbing mounting and clamping system, and it comprises:
Fixture, it is close with aerospace component two ends match profiles, is arranged on the fixture at aerospace component length direction two ends, and fixture outside is installed on the table;
Supporter, its two ends are fixedly connected between the fixture at described aerospace component two ends, and supporter runs through aerospace component inside;
Filler, it is the fluid that can solidify, and fills aerospace component inner space.
2. the little stress of weak rigidity aerospace component according to claim 1 fills shock-absorbing mounting and clamping system, and it is characterized in that, also comprise secondary supporting construction, its two ends coordinate with aerospace component two ends, and are fixed on described supporter.
3. the little stress of weak rigidity aerospace component according to claim 1 fills shock-absorbing mounting and clamping system, and it is characterized in that, described supporter is strip extrusion.
4. the little stress of weak rigidity aerospace component according to claim 2 fills shock-absorbing mounting and clamping system, and it is characterized in that, described secondary supporting construction interlude is extrusion, and two ends are airtight.
5. the little stress of weak rigidity aerospace component according to claim 3 fills shock-absorbing mounting and clamping system, and it is characterized in that, described supporter is cylinder, and the junction of its two ends and described fixture is positioned in the geometric center of fixture and aerospace component contact surface.
6. the little stress of weak rigidity aerospace component according to claim 4 fills shock-absorbing mounting and clamping system, and it is characterized in that, the contact surface of described secondary supporting construction two ends and aerospace component is regular hexagon.
7. the little stress of weak rigidity aerospace component according to claim 6 fills shock-absorbing mounting and clamping system, and it is characterized in that, described secondary supporting construction is hollow structure, and its interlude is regular hexagon extrusion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520151548.6U CN204471045U (en) | 2015-03-17 | 2015-03-17 | The little stress of weak rigidity aerospace component fills shock-absorbing mounting and clamping system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520151548.6U CN204471045U (en) | 2015-03-17 | 2015-03-17 | The little stress of weak rigidity aerospace component fills shock-absorbing mounting and clamping system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204471045U true CN204471045U (en) | 2015-07-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520151548.6U Active CN204471045U (en) | 2015-03-17 | 2015-03-17 | The little stress of weak rigidity aerospace component fills shock-absorbing mounting and clamping system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204471045U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107617911A (en) * | 2017-08-23 | 2018-01-23 | 成都飞机工业（集团）有限责任公司 | A kind of aerospace component Universal efficient clamping device |
-
2015
- 2015-03-17 CN CN201520151548.6U patent/CN204471045U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107617911A (en) * | 2017-08-23 | 2018-01-23 | 成都飞机工业（集团）有限责任公司 | A kind of aerospace component Universal efficient clamping device |
| CN107617911B (en) * | 2017-08-23 | 2019-06-11 | 成都飞机工业（集团）有限责任公司 | A kind of aerospace component Universal efficient clamping device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3 Patentee after: SICHUAN FUTURE AEROSPACE INDUSTRIAL Co.,Ltd. Address before: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3 Patentee before: Shifang City Mingri Space Navigation Industry Co.,Ltd. |
|
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 618400 No. 3, Lantian Avenue, Shifang Economic Development Zone (North District), Deyang City, Sichuan Province Patentee after: Sichuan Xinhang Titanium Technology Co.,Ltd. Address before: 618400 No. 3, Lantian Avenue, Shifang Economic Development Zone (North District), Deyang City, Sichuan Province Patentee before: SICHUAN FUTURE AEROSPACE INDUSTRIAL Co.,Ltd. |