The little stress of weak rigidity aerospace component fills shock-absorbing clamping processing methodTechnical field
The present invention relates to the manufacture field of aerospace component, particularly the little stress of one weak rigidity aerospace component fills shock-absorbing clamping processing method.
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.
Summary of the invention
To the object of the invention is to overcome in prior art existing above-mentioned deficiency, provide a kind of and cut down finished cost, improve working (machining) efficiency, reduce the little stress of weak rigidity aerospace component of workman's learning cost and fill shock-absorbing clamping processing method.
In order to realize foregoing invention object, the invention provides following technical scheme:
The little stress of a kind of weak rigidity aerospace component fills shock-absorbing clamping processing method, the steps include:
A, to 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 can solidify in the filling of aerospace component inside, Fluid inclusions supporter, fills up aerospace component inner space;
D, curing liquid, complete clamping, processes.
The present invention has directly cast out other fixtures various of the removing main clamp around aerospace component, 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 technique is 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 invention, step C, in D, described fluid parameter meets: after described fluid solidification, its weight ensures in the scope that can not cause distortion to aerospace component, and make the integral rigidity of now aerospace component meet minimum processing request, according to different aerospace components, use different curable fluids or different meterings, if use for the aerospace component that some rigidity is very low the fluid that the rear quality of solidification is very large, so it may be out of shape when undressed, so " after described fluid solidification, its weight ensures in the scope that can not cause distortion to aerospace component, and make the integral rigidity of now aerospace component meet minimum processing request " be a restriction very important to the inventive method.
As preferred version of the present invention, in step B, described supporter is strip extrusion, and structure is coherent symmetrical, and rigidity is large, more stable.
As preferred version of the present invention, described step B is specially:
The strip extrusion running through aerospace component is installed between the fixture at aerospace component two ends, the secondary supporting construction of space mounting between strip extrusion and aerospace component shell, described secondary supporting construction is hollow structure, its two ends coordinate with aerospace component two ends, and be fixed on described supporter, 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, supporter is fixedly connected with fixture again, form integrative-structure, after the fluid solidification of filling, make aerospace component rigidity larger more stable.
As preferred version of the present invention, in step B, 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 invention, described step C is specially:
Fill the fluid that can solidify in aerospace component inside, the secondary supporting construction of Fluid inclusions, fills up aerospace component inner space.
As preferred version of the present invention, in steps A, described aerospace component two ends have dragged the clamp-shaped of aerospace component and aerospace component two ends profile to match, some clamping holes are all set above, need the two ends clip position unique to aerospace component to carry out the most comprehensive clamping, ensure the precision of overall processing.
Compared with prior art, beneficial effect of the present invention:
Cut down finished cost, improve working (machining) efficiency, reduce workman's learning cost.
Accompanying drawing illustrates:
Fig. 1 is the flow chart of the inventive method;
Fig. 2 is by being processed aerospace component schematic diagram in the embodiment of the present invention 1;
Fig. 3 is two ends fixture when processing aerospace component in the embodiment of the present invention 1 and supporter schematic diagram;
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 that when processing aerospace component in the embodiment of the present invention 1, whole clamping scheme implements complete design sketch.
Fig. 7 is secondary supporting construction schematic diagram when processing aerospace component in the embodiment of the present invention 1.
Detailed description of the invention
Below in conjunction with embodiment and detailed description of the invention, the present invention is described in further detail.But this should be interpreted as that the scope of the above-mentioned theme of the present invention is only limitted to following embodiment, all technology realized based on content of the present invention all belong to scope of the present invention.
Embodiment 1
As Fig. 1, the little stress of a kind of weak rigidity aerospace component fills shock-absorbing clamping processing method, and be illustrate the rough flow of the method in Fig. 1, in the present embodiment, its concrete step is:
A, at described aerospace component (structural member of the present embodiment as shown in Figure 2, frame-like structures part the most common in the weak rigid structural member of aviation field) two ends of length direction install the fixture that can drag aerospace component, its shape and aerospace component two ends profile match (fixture described in the present embodiment is rhombus), all arrange some clamping holes above;
B, between the fixture at aerospace component two ends, fixed installation runs through the supporter of aerospace component, described supporter is that strip extrusion is (as Fig. 3, in the present embodiment, it is cylinder, its two ends are connected to the middle part of rhombus), the secondary supporting construction of space mounting between strip extrusion and aerospace component shell is (as Fig. 7, its two ends are hexagon, coordinate the hexagonal outline of inside, aerospace component framework two ends, the position of perspective structure just in order to indicate supporter in this figure, in reality, the material of secondary supporting construction does not limit perspective or non-perspective), described secondary supporting construction is hollow structure, its two ends coordinate with aerospace component two ends, and be fixed on described supporter, described secondary supporting construction interlude is extrusion, two ends are airtight, outside the fixture at described aerospace component two ends, mounting bar is installed, it is fixedly connected with fixture, fixture is arranged on workbench by this mounting bar and processes, in the present embodiment, mounting bar is on the diagonal of the fixture being fixed on described rhombus, Stability Analysis of Structures, rigidity is large, ensure that the precision of aerospace component processing is (as Fig. 4, and the Fig. 5 in the present embodiment is the schematic diagram only installing two ends fixture when processing aerospace component, in order to show state when aerospace component is clamped, in reality, its inner supporter and secondary supporting construction in addition), ,
C, to fill the fluid that can solidify in aerospace component inside (be gypsum or polyurethane foam, be easy to be shaped, all arrive can use in a lot of industry, and cheap, the aerospace component enough for rigidity can use gypsum, low for rigidity, if with gypsum, proportion is excessive, distortion is caused to part in rough, in this case use polyurethane foam, after polyurethane foam solidification, density is about 0.04-0.06g/cm3, very gently, almost all-pervasive in use, hardening time is about 6-8 hour, has stronger hardness after solidification, but arbitrarily can cut with cutter, and use simple to operate, and namely can; Polyurethane foams at furniture, repairs profession extensive use, but borrow in little in machining, in this application, curable fluid optimization polyurethane foam), the secondary supporting construction of Fluid inclusions, fills up aerospace component inner space (as Fig. 6);
D, curing liquid, complete clamping, carries out processing (Fig. 6 also can represent the state after fixed line fluid, in this condition, can carry out the processing to aerospace component);
In the present embodiment, concrete machined parameters is as following table:
Unit: mm
| Cutter title | Tool diameter | Processing type | Maximum cut wide | Maximum cutting-in | Rotating speed | Per tooth feeding | Tool blade number |
| Milling cutter | 16 | Roughing | 8 | 2 | 800 | 0.1 | 4 |
| Milling cutter | 16 | Fine finishining | 5 | 1.5 | 800 | 0.1 | 4 |
| Milling cutter | 12 | Roughing | 4 | 0.5 | 1200 | 0.1 | 4 |
| Milling cutter | 12 | Fine finishining | 4 | 0.5 | 1200 | 0.1 | 4 |
| T-shaped cutter | 250 | Fine finishining | 50 | 1 | 50 | 0.1 | 9 |
| T-shaped cutter | 100 | Fine finishining | 24 | 1 | 100 | 0.1 | 10 |
| T-shaped cutter | 25 | Fine finishining | 6 | 1 | 800 | 0.03 | 4 |
| Milling cutter | 20 | Fine finishining | 1 | 10 | 800 | 0.06 | 4 |
Can see, owing to have employed the method for the application, machined parameters, relative to existing technology, simplifies a lot, also not for the special requirement of certain part;
So the clamping scheme of the application coordinates with follow-up simple and direct processing scheme, convenient and swiftly to reduce costs, make whole technique not only retained part workman learning cost is low simultaneously, and processing part workman's learning cost is also low.
In step C, D, described fluid parameter meets: after described fluid solidification, its weight ensures in the scope that can not cause distortion to aerospace component, and makes the integral rigidity of now aerospace component meet minimum processing request.