CN104690572B - Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method - Google Patents
Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method Download PDFInfo
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- CN104690572B CN104690572B CN201510116853.6A CN201510116853A CN104690572B CN 104690572 B CN104690572 B CN 104690572B CN 201510116853 A CN201510116853 A CN 201510116853A CN 104690572 B CN104690572 B CN 104690572B
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- aerospace component
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- structural member
- aerospace
- processing method
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- 238000003754 machining Methods 0.000 title abstract description 14
- 238000000034 method Methods 0.000 title abstract description 13
- 238000010521 absorption reaction Methods 0.000 title abstract 3
- 230000035939 shock Effects 0.000 title abstract 3
- 239000012530 fluid Substances 0.000 claims abstract description 29
- 238000010276 construction Methods 0.000 claims description 17
- 238000003672 processing method Methods 0.000 claims description 12
- 238000007711 solidification Methods 0.000 claims description 12
- 230000008023 solidification Effects 0.000 claims description 12
- 238000001125 extrusion Methods 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 5
- 239000007788 liquid Substances 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 5
- 238000003801 milling Methods 0.000 description 5
- 229920005830 Polyurethane Foam Polymers 0.000 description 4
- 239000011496 polyurethane foam Substances 0.000 description 4
- OSGAYBCDTDRGGQ-UHFFFAOYSA-L calcium sulfate Chemical compound [Ca+2].[O-]S([O-])(=O)=O OSGAYBCDTDRGGQ-UHFFFAOYSA-L 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000009825 accumulation Methods 0.000 description 2
- 238000004458 analytical method Methods 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
- 230000007812 deficiency Effects 0.000 description 1
- 239000004088 foaming agent Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000010197 meta-analysis Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Working Measures On Existing Buildindgs (AREA)
Abstract
The invention relates to the field of machining of aviation structural members, in particular to a weakly rigid aviation structural member small stress filling and shock absorption clamping machining method. The method includes the steps of firstly, installing clamps which can support an aviation structural member at the two ends of the aviation structural member in the length direction; secondly, fixedly installing a supporting body penetrating through the aviation structural member between the clamps at the two ends of the aviation structural member; thirdly, filling the inner portion of the aviation structural member with fluid capable of being solidified, wrapping a supporting body in the fluid, and filling the internal space of the aviation structural member; fourthly, solidifying the fluid, completing clamping, and conducting machining. The invention aims at providing the weakly rigid aviation structural member small stress filling and shock absorption clamping machining method which can reduce the machining cost, improve the machining efficiency and reduce the study cost of workers.
Description
Technical field
The present invention relates to the manufacture field of aerospace component, particularly to the little stress filling of the weak rigid aerospace component of one kind
Shock-absorbing clamping processing method.
Background technology
In aerospace component, some is frame-type part, its poor rigidity, and machining can cause judder, or even
Cannot process；
In prior art, to the solution technique of this problem it is: using a large amount of fixtures, for the part of different-stiffness, adopt
Different clamping scheme, meanwhile, cutting parameter is also individually supporting, and will make a complete scheme, needs to produce system
Make substantial amounts of fixture, the position that simultaneously clamps, contact area etc., need through long-term experience accumulation, or complexity is limited
Meta-analysis, and after clamping, for the processing of structural member, because the rigidity at each position is different, so processing scheme is also to need
Will be through long-term experience accumulation, or finite element analyses of complexity, all very conservative under normal circumstances, because this frame-type
Not, if producing vibration in processing, meeting error is very big for aerospace component rigidity；
As previously discussed, these techniques all can the serious processing cost that must increase aerospace component, efficiency is very low simultaneously, work
The learning cost of people is also of a relatively high.
Content of the invention
It is an object of the invention to the above-mentioned deficiency in the presence of overcoming prior art, provide a kind of reduce processing cost,
Improve the weak rigid aerospace component little stress filling shock-absorbing clamping processing method of working (machining) efficiency, reduction workman's learning cost.
In order to realize foregoing invention purpose, the invention provides technical scheme below:
A kind of little stress of weak rigid aerospace component fills shock-absorbing clamping processing method, the steps include:
A, install at the two ends of described aerospace component length direction and can drag the fixture of aerospace component；
B, between the fixture at aerospace component two ends fixed installation run through the supporter of aerospace component；
C, the fluid that filling can solidify inside aerospace component, Fluid inclusions supporter, fills up in aerospace component
Portion space；
D, curing liquid, complete clamping, are processed.
The present invention has directly cast out various other fixtures of the removing main clamp around aerospace component, in aerospace component
Two fixtures with aerospace component cooperation are installed at two ends, arrange described supporter between fixture, constitute main holding capacity
Structure, and the fluid after described solidification, fill full aerospace component inner space, at this moment the power on aerospace component framework is passed through
Fluid after solidification, passed on described supporter, and the fixture cast out of the fluid, instead after solidification, originally from aeronautic structure
Clamped outside part, the mode of lifting aerospace component rigidity, become to support inside aerospace component；
Remove substantial amounts of unnecessary fixture, after having clamped, during processing, as long as the fluid rigidity after solidification reaches wanting simultaneously
Ask it is no longer necessary to consider whether the problem vibrated, greatly reduce requirement during machining it is not required that the clamping of complexity,
Machining scheme, reduces great amount of cost, and technique is more simply too much than in the past, improves working (machining) efficiency, and scheme is convenient simultaneously
Easy to learn, reduce workman's learning cost.
As the preferred version of the present invention, in step c, d, described fluid parameter meets: after described fluid solidification, its weight
Ensure in the scope that aerospace component will not be caused with deformation, and make the integral rigidity of now aerospace component meet minimum processing
Require, according to different aerospace components, using different curable fluids or different meterings, if for some rigidity
Very low aerospace component is using the very big fluid of quality after solidification, then it may deform when undressed, thus " described
After fluid solidification, its weight ensures aerospace component will not be caused with the scope that deforms, and makes the whole of now aerospace component
Body rigidity meets minimum processing request " it is that critically important to the inventive method limits.
As the preferred version of the present invention, in step b, described supporter is strip extrusion, and structure links up symmetrical, just
Degree is big, more stable.
As the preferred version of the present invention, described step b particularly as follows:
The strip extrusion running through aerospace component is installed between the fixture at aerospace component two ends, in strip stretching
Between body and aerospace component shell space mounting pair supporting construction, described pair supporting construction be hollow structure, its two ends with
Aerospace component two ends coordinate, and are fixed on described supporter, and described fixture gives its folder at the outside two ends of aerospace component
Hold, described pair supporting construction internally supports aerospace component, and secondary supporting construction is fixedly mounted on supporter simultaneously, supporter
It is fixedly connected with fixture again, form integrative-structure, after the fluid solidification of filling, make aerospace component rigidity more more stable greatly.
As the preferred version of the present invention, in step b, described pair supporting construction interlude is extrusion, and two ends are airtight, knot
Structure links up symmetrically, and rigidity is big, more stable.
As the preferred version of the present invention, described step c particularly as follows:
Fill the fluid that can solidify, Fluid inclusions pair supporting construction inside aerospace component, fill up aerospace component
Inner space.
As the preferred version of the present invention, in step a, described aerospace component two ends drag the fixture shape of aerospace component
Shape is matched with aerospace component two ends profile, is respectively provided with some clamping holes above, needs unique two ends to aerospace component
Clip position carries out the most comprehensive clamping it is ensured that the precision of overall processing.
Compared with prior art, beneficial effects of the present invention:
Reduce processing cost, improve working (machining) efficiency, reduce workman's learning cost.
Brief description:
Fig. 1 is the flow chart of the inventive method；
Fig. 2 is processed aerospace component schematic diagram by the embodiment of the present invention 1；
Fig. 3 is the two ends fixture and supporter schematic diagram when processing aerospace component in the embodiment of the present invention 1；
Fig. 4 is the scheme of installation of two ends fixture when processing aerospace component in the embodiment of the present invention 1；
Fig. 5 is the schematic diagram only installing two ends fixture when processing aerospace component in the embodiment of the present invention 1；
Fig. 6 is the design sketch that when processing aerospace component in the embodiment of the present invention 1, whole clamping scheme enforcements finish.
Fig. 7 is secondary supporting construction schematic diagram when processing aerospace component in the embodiment of the present invention 1.
Specific embodiment
With reference to embodiment and specific embodiment, the present invention is described in further detail.But this should not be understood
Scope for the above-mentioned theme of the present invention is only limitted to below example, all belongs to this based on the technology that present invention is realized
The scope of invention.
Embodiment 1
As Fig. 1, a kind of little stress of weak rigid aerospace component fills shock-absorbing clamping processing method, is to the method in Fig. 1
Rough flow illustrates, in the present embodiment, its specific step is:
A, in described aerospace component, (structural member of the present embodiment is as shown in Fig. 2 be the weak rigid structural member of aviation field
In most commonly seen frame-like structures part) two ends of length direction install fixture, its shape and the boat that can drag aerospace component
Hollow structure part two ends profile matches (fixture described in the present embodiment is rhombus), is respectively provided with some clamping holes above；
B, between the fixture at aerospace component two ends fixed installation run through the supporter of aerospace component, described supporter is
Strip extrusion (such as Fig. 3, in the present embodiment, it is cylinder, and its two ends is connected to the middle part of rhombus), in strip stretching
(such as Fig. 7, its two ends is hexagon to space mounting pair supporting construction between body and aerospace component shell, coordinates aeronautic structure
Hexagonal outline within part framework two ends, this in figure perspective structure is intended merely to represent the position of supporter, secondary in practice
The material of supporting construction does not limit perspective or non-perspective), described pair supporting construction is hollow structure, its two ends and aerospace component
Two ends coordinate, and are fixed on described supporter, and described pair supporting construction interlude is extrusion, and two ends are airtight, described aviation
Outside the fixture at structural member two ends, mounting bar is installed, it is fixedly connected with fixture, fixture is arranged on work by this mounting bar
It is processed on platform, in the present embodiment, mounting bar is integrally fixed on the diagonal of the fixture of described rhombus, Stability Analysis of Structures, rigidity
Big it is ensured that precision (such as Fig. 4, and the Fig. 5 in the present embodiment is only installing during processing aerospace component of aerospace component processing
The schematic diagram of two ends fixture, in order to show state when aerospace component is clamped, in practice, its internal also supporter and pair
Supporting construction),；
C, fill inside aerospace component can solidify fluid (for Gypsum Fibrosum or polyurethane foam it is easy to shape,
A lot of industries all arrive and can use, and cheap, can use Gypsum Fibrosum for the enough aerospace components of rigidity, low for rigidity
, if using Gypsum Fibrosum, proportion is excessive, part is caused to deform in rough, uses polyurethane foam in this case,
After polyurethane foam solidification, density is about 0.04-0.06g/cm3, very gently, almost all-pervasive when using, hardening time is about
6-8 hour, has stronger hardness after solidification, but arbitrarily can be cut with cutter, and uses simple to operate, and i.e. can；Poly-
Urethane foaming agent is extensively applied in furniture, repairs profession, but borrows in little in machining, in this application, curable
Fluid optimization polyurethane foam), Fluid inclusions pair supporting construction, fill up aerospace component inner space (as Fig. 6)；
D, curing liquid, complete clamping, are processed that (Fig. 6 can also represent the state after fixed line fluid, in this state
Under, you can carry out the processing to aerospace component)；
In the present embodiment, specific machined parameters are as follows:
Unit: mm
| Cutter title | Tool diameter | Processing type | Maximum cuts width | Maximum cutting-in | Rotating speed | Per tooth feeds | Tool blade number |
| Milling cutter | 16 | Roughing | 8 | 2 | 800 | 0.1 | 4 |
| Milling cutter | 16 | Polish | 5 | 1.5 | 800 | 0.1 | 4 |
| Milling cutter | 12 | Roughing | 4 | 0.5 | 1200 | 0.1 | 4 |
| Milling cutter | 12 | Polish | 4 | 0.5 | 1200 | 0.1 | 4 |
| T shape knife | 250 | Polish | 50 | 1 | 50 | 0.1 | 9 |
| T shape knife | 100 | Polish | 24 | 1 | 100 | 0.1 | 10 |
| T shape knife | 25 | Polish | 6 | 1 | 800 | 0.03 | 4 |
| Milling cutter | 20 | Polish | 1 | 10 | 800 | 0.06 | 4 |
Can see, due to employing the present processes, machined parameters, with respect to existing technology, simplify a lot,
It is not directed to the special requirement of certain part yet；
So the clamping scheme of the application is coordinated with subsequently simple and direct processing scheme, convenient and swift reduces cost, make simultaneously
Not only retained part workman learning cost is low for whole technique, and processing department division of labor people's learning cost is also low.
In step c, d, described fluid parameter meets: after described fluid solidification, its weight ensures will not be to aeronautic structure
Part causes the scope deforming, and makes the integral rigidity of now aerospace component meet minimum processing request.
Claims (7)
1. a kind of little stress of weak rigid aerospace component fills shock-absorbing clamping processing method, the steps include:
A, install at the two ends of described aerospace component length direction and can drag the fixture of aerospace component；
B, between the fixture at aerospace component two ends fixed installation run through the supporter of aerospace component；
C, the fluid that filling can solidify inside aerospace component, Fluid inclusions supporter, fills up aerospace component internal empty
Between；
D, curing liquid, complete clamping, are processed.
2. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 1 it is characterised in that
In step c, d, described fluid parameter meets: after described fluid solidification, its weight ensures aerospace component will not caused become
The scope of shape, and make the integral rigidity of now aerospace component meet minimum processing request.
3. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 1 it is characterised in that
In step b, described supporter is strip extrusion.
4. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 3 it is characterised in that
Described step b particularly as follows:
Between the fixture at aerospace component two ends, fixed installation runs through the strip extrusion of aerospace component, in strip stretching
Between body and aerospace component shell space mounting pair supporting construction, described pair supporting construction be hollow structure, its two ends with
Aerospace component two ends coordinate, and are fixed on described supporter.
5. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 4 it is characterised in that
In step b, described pair supporting construction interlude is extrusion, and two ends are airtight.
6. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 4 it is characterised in that
Described step c particularly as follows:
Fill the fluid that can solidify, Fluid inclusions pair supporting construction inside aerospace component, fill up inside aerospace component
Space.
7. the little stress filling shock-absorbing clamping processing method of weak rigid aerospace component according to claim 1 it is characterised in that
In step a, described aerospace component two ends drag the clamp-shaped of aerospace component and aerospace component two ends profile matches,
It is respectively provided with some clamping holes above.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510116853.6A CN104690572B (en) | 2015-03-17 | 2015-03-17 | Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510116853.6A CN104690572B (en) | 2015-03-17 | 2015-03-17 | Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104690572A CN104690572A (en) | 2015-06-10 |
| CN104690572B true CN104690572B (en) | 2017-02-01 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104889706B (en) * | 2015-05-28 | 2017-06-20 | 北京航空航天大学 | A kind of reverse segmental machining method and device of weak rigid workpiece |
| CN107234862A (en) * | 2016-03-29 | 2017-10-10 | 成都飞机工业（集团）有限责任公司 | A kind of holding method of honeycomb core |
| CN106378655B (en) * | 2016-11-29 | 2018-06-08 | 武汉理工大学 | A kind of weak rigid workpiece series-parallel connection intelligence grip device |
| CN107838704A (en) * | 2017-09-29 | 2018-03-27 | 江西昌河航空工业有限公司 | A kind of method being processed to U-shape structure carbon fiber blank |
| CN108655669A (en) * | 2018-05-18 | 2018-10-16 | 陕西测易机电设备有限公司 | A kind of processing method of space flight and aviation thin-walled parts |
| CN114952329A (en) * | 2022-06-21 | 2022-08-30 | 成都飞机工业（集团）有限责任公司 | General filling and stiffening device and method for structural member |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1130285A (en) * | 1967-05-05 | 1968-10-16 | Rolls Royce | Method of making an aerofoil shaped blade for a fluid flow machine |
| US20100122459A1 (en) * | 2008-11-17 | 2010-05-20 | General Electric Company | Method of making wind turbine blade |
| CN101912990B (en) * | 2010-07-27 | 2011-11-23 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for milling and vibration-damping blisk |
| US20120027609A1 (en) * | 2011-05-17 | 2012-02-02 | Prasad Ogde | Wind turbine rotor blade with precured fiber rods and method for producing the same |
| CN103786003B (en) * | 2014-01-15 | 2016-04-06 | 西安航空动力股份有限公司 | A kind of processing method of aero-engine guide vane listrium |
| CN104001781B (en) * | 2014-04-22 | 2017-01-04 | 哈尔滨工业大学（威海） | The forming device of a kind of high accuracy hollow unit and method |
| CN104259883B (en) * | 2014-09-15 | 2016-06-01 | 北京卫星制造厂 | A kind of filling method for supporting strengthening thin-walled part processing rigidity |
| CN104400452A (en) * | 2014-10-31 | 2015-03-11 | 沈阳黎明航空发动机(集团)有限责任公司 | High-temperature alloy honeycomb part milling processing clamping method |
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Address after: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3 Applicant after: SICHUAN FUTURE AEROSPACE INDUSTRIAL Co.,Ltd. Address before: 618400 Deyang City, Shifang Province Economic Development Zone (North), blue sky Avenue, No. 3 Applicant before: Shifang City Mingri Space Navigation Industry Co.,Ltd. |
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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. |
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