CN106271444A - The processing method of ceramic matric composite cabin section assembly - Google Patents
The processing method of ceramic matric composite cabin section assembly Download PDFInfo
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- CN106271444A CN106271444A CN201610786285.5A CN201610786285A CN106271444A CN 106271444 A CN106271444 A CN 106271444A CN 201610786285 A CN201610786285 A CN 201610786285A CN 106271444 A CN106271444 A CN 106271444A
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- metal end
- size
- matric composite
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
Abstract
The processing method that the invention discloses a kind of ceramic matric composite cabin section assembly, on the basis of the metal end face of workpiece, the flatness of levelling metal end face is less than or equal to the first preset value；On workpiece machined go out pin-and-hole bottom outlet on the basis of just determine workpiece centre, carry out roughing and go out workpiece configurations to leaving allowance, wherein, the processing of pin-and-hole bottom outlet is on the metal end face of workpiece: EDDY CURRENT allowance is the most uniform；After the results verification allowance of EDDY CURRENT is uniform, finishing workpiece profile is to size；On the basis of metal end face, the flatness of levelling metal end face is less than or equal to the second preset value；Again determine workpiece centre on the basis of workpiece configurations after being refined to size, be processed metal end face to size.The present invention is difficult to control to the technical problem of the wall unevenness that machining deformation brings when solving processing ceramic based composites cabin section assembly, improve the Product Precision of ceramic matric composite cabin section assembly.
Description
Technical field
The invention belongs to Machining Technology field, particularly to the processing side of a kind of ceramic matric composite cabin section assembly
Method.
Background technology
In recent years, along with the continuous progress of science and technology, material technology is developed rapidly.Composite the most gradually becomes
Take one of material as the leading factor.Composite has light weight, relatively high specific strength, specific modulus, anticorrosive, high temperature resistant, ablation resistance etc.
Feature, is the ideal material of the weapons such as aircraft, guided missile, aerospace craft." metal+composite " is at present in missile armament system
A class formation part more common in system, currently mainly uses the technology manufactures such as winding, suit.Ceramic matric composite is as one
Planting emerging composite, its performance anticorrosive, resistant to elevated temperatures is more powerful.Along with the update of Aerospace Products, right
Flight time, Mach number requirement more and more higher, require to improve constantly to the performance of heat-resistant composite material etc., demand is the most increasingly
Greatly.
The procedure of processing of existing Composite Cabin section assembly the following is: (1) processes workpiece configurations on the basis of end face pin hole；
(2) Roughing and fine machining workpiece configurations is to size；(3) each opening of polish is to size.Owing to the hardness of ceramic matric composite is high,
Fragility is big, processes easy aliquation, falls slag, and sharp edge easily collapses block；Tool wear is fast, processes yielding, evenness of wall thickness, allowance etc.
Larger difference is had with theory state.The processing method of existing Composite Cabin section assembly is carried out on the basis of using end face pin hole all the time
Processing there will be machining deformation, be applied to the processing of ceramic matric composite cabin section assembly again cannot comprehensive coordinate allowance,
The processing method of the most existing Composite Cabin section assembly is difficult to control to add when the section assembly of processing ceramic based composites cabin
Work deforms the wall unevenness brought.
Summary of the invention
The processing method of a kind of ceramic matric composite cabin section assembly that the embodiment of the present invention provides, solves existing processing
Method is difficult to control to the technical problem of the wall unevenness that machining deformation brings when the section assembly of processing ceramic based composites cabin.
The processing method embodiments providing a kind of ceramic matric composite cabin section assembly, including perform successively
Following steps:
On the basis of the metal end face of workpiece, the flatness of levelling described metal end face is less than or equal to the first preset value；
On described workpiece machined go out pin-and-hole bottom outlet on the basis of just determine workpiece centre, carry out roughing and go out workpiece configurations
To leaving allowance, wherein, described pin-and-hole bottom outlet is processed on the metal end face of described workpiece:
Described in EDDY CURRENT, allowance is the most uniform；
After allowance described in the results verification of described EDDY CURRENT is uniform, described in polish, workpiece configurations is to size；
On the basis of described metal end face, the flatness of levelling described metal end face is less than or equal to the second preset value；
Again determine workpiece centre on the basis of described workpiece configurations after being refined to size, be processed described metal
End face is to size.
Preferably, described on described workpiece machined go out pin-and-hole bottom outlet on the basis of just determine workpiece centre, slightly add
Work goes out workpiece configurations to leaving allowance, including:
The machined surface of workpiece configurations described in trial cut is carried out to leaving uniform surplus to big end from the small end of described workpiece；
Polycrystalline diamond milling cutter is used to add along the winding direction climb cutting of ceramic matric composite by end-state made allowance
The described machined surface of workpiece configurations described in work is all shown in light.
Preferably, described end-state made allowance is 0.5～1mm.
Preferably, described in described polish, workpiece configurations is to size, particularly as follows:
Employing monocrystalline diamond milling cutter processes described workpiece configurations extremely along the winding direction climb cutting of ceramic matric composite
Size.
Preferably, again determine workpiece centre on the basis of described described workpiece configurations after being refined to size, carry out
Process described metal end face to size, the following steps including performing successively:
Metal end face procedure of processing: first use the side edge of diamond coatings milling cutter to cut described metal end face remaining to leaving
Amount, uses metal end face described in the shear blade layered cutting of described diamond coatings milling cutter to size afterwards；
End face seal boss procedure of processing: first use the side edge cutting end face seal boss of described diamond coatings milling cutter to add
Station is put to one side made allowance, uses end face described in the shear blade climb cutting layered cutting from the top down of described diamond coatings milling cutter afterwards
Seal boss Working position is to one side made allowance, then uses end face seal boss described in described diamond coatings milling cutter polish to add
Station is put to size；
Boring processing end face pin hole is to size.
Preferably, being processed described metal end face to after size described, described processing method also includes:
Pressing plate, after the U-type groove limit of U-type groove to be processed is compressed by described metal end face to profile side, uses cutter under spiral
Mode carries out segmentation, layering processes U-type groove mouth；
Pressing plate, after the limit, open sunken of open sunken to be processed is compressed by described metal end face to described profile side, is adopted
With described spiral plunge cut way carry out segmentation, layering process open sunken；
Pressing plate, after the sealing trough rim of seal groove to be processed is compressed by described metal end face to described profile side, uses institute
State spiral plunge cut way carry out segmentation, layering process seal groove.
Preferably, described employing described spiral plunge cut way carry out segmentation, layering process seal groove after, described in add
Work method also includes:
Detect the linear dimension of described workpiece；
The wall thickness of heat shield in metal end face described in EDDY CURRENT；
By described metal end face and be machined to size end face pin hole on the basis of carry out detecting the morpheme of described workpiece
Tolerance；
By the described end face pin hole fixed protection plate at two ends.
Preferably, described first preset value and described second preset value are 0.05.
One or more technical schemes that the embodiment of the present invention provides, at least have the following technical effect that or advantage:
1, first first piece profile on the basis of the pin-and-hole bottom outlet processed, then determine with eddy current detection method and add spare time
After amount uniformity, workpiece configurations described in polish is to size, then finished metal end face and each opening on the basis of workpiece configurations,
Thus EDDY CURRENT combines with Reference Transforming and determines the Cutter coordinate system of each step, can analyze ceramic matric composite cabin comprehensively
The allowance of section assembly, thus accurately control the wall unevenness that machining deformation brings, and when combining processing different characteristic
For different machining benchmarks, solve existing processing method when the section assembly of processing ceramic based composites cabin, be difficult to control to processing
The technical problem of the wall unevenness that deformation brings, is effectively increased the Product Precision of ceramic matric composite cabin section assembly, to protect
Card meets Product Assembly requirement.
2, U-type groove is gone out owing to the U-type groove limit of U-type groove to be processed is compressed post-treatment from metal end face to profile side by pressing plate
Mouthful；The limit, open sunken of open sunken to be processed is compressed post-treatment from metal end face to profile side and goes out open sunken by pressing plate；
The sealing trough rim of seal groove to be processed is compressed post-treatment from metal end face to described profile side and goes out seal groove by pressing plate, and processing is not
Different clamping position is used, it is to avoid the heat shield seamed edge aliquation of metal end face in the course of processing, fall slag, energy with feature correspondence
Ensure housing quality.
3, it is fixed on metal end face owing to have employed protective plate, protects the heat shield seamed edge of metal end face and seal convex
Platform.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
In having technology to describe, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is only this
Inventive embodiment, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to according to
The accompanying drawing provided obtains other accompanying drawing.
Fig. 1 is the axonometric chart of ceramic matric composite cabin section assembly in the embodiment of the present invention；
Fig. 2 is the top view of ceramic matric composite cabin section assembly in the embodiment of the present invention.
Detailed description of the invention
For making the purpose of the embodiment of the present invention, technical scheme and advantage clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
The a part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under not making creative work premise, broadly falls into the scope of protection of the invention.
The processing method of a kind of ceramic matric composite cabin section assembly that the embodiment of the present invention provides, it should be noted that
In the case of not conflicting, the embodiment in the present invention and the feature in embodiment can be mutually combined.
As depicted in figs. 1 and 2, ceramic matric composite cabin section assembly is thin-walled diamond structure, and blank material is by graphite mould
Casting forms, and the processing method of this ceramic matric composite cabin section assembly includes the following steps performed successively:
Step 1, on the basis of the metal end face 1 of workpiece the flatness of levelling metal end face 1 less than or equal to first preset
Value.
Such as, the first preset value is 0.05mm, then the plane of levelling metal end face 1 on the basis of the metal end face 1 of workpiece
Degree≤0.05mm.According to the process requirements in specific implementation process, the first preset value is set to other more than or less than 0.05mm
Other approximations fall within protection scope of the present invention, such as, 0,04～0.06.
Step 2, on workpiece machined go out pin-and-hole bottom outlet on the basis of just determine workpiece centre, carry out roughing and go out outside workpiece
Shape is to leaving allowance, and wherein, pin-and-hole bottom outlet is processed on the metal end face 1 of workpiece.
Concrete, perform following trial cut step successively and rough mill step and carry out roughing and go out workpiece configurations and add spare time to leaving
Amount.
Trial cut step is: carry out the machined surface of trial cut workpiece configurations to leaving uniform surplus from the small end of workpiece to big end.
Rough milling step is: use polycrystalline diamond milling cutter by end-state made allowance along the winding of ceramic matric composite
Direction climb cutting is machined to the machined surface of workpiece configurations and all sees light.
Concrete, in rough milling step, use bit diameterPolycrystalline diamond milling cutter, by end-state
Made allowance is 0.5～1mm to be machined to the machined surface of workpiece configurations along the winding direction climb cutting of ceramic matric composite and all see light.?
Rough milling in step, machined parameters is specifically as follows: machine spindle speed F3000, machine tool feed speed S1000, cuts wide 3mm, cuts
Deep 0.5mm.In specific implementation process, it is also possible to check the machined surface of workpiece configurations after rough milling step the most all see light with
And confirm that allowance is enough.
Step 3, EDDY CURRENT allowance are the most uniform.
In step 3, adding by each machined surface of the wall thickness confirmation workpiece configurations of EDDY CURRENT ceramic matric composite
Spare time, amount was the most uniform.Specifically: the coil being connected with alternating current is placed on the workpiece after rough milling or is enclosed within the work after rough milling
Outside part, can induce eddy current in workpiece, coil current can be changed by vortes interference, then the change of coil current can be reacted
Allowance is the most uniform, and size of current change is the least, then allowance is the most uniform.
Step 4, EDDY CURRENT results verification allowance uniformly after, finishing workpiece profile is to size.
Concrete, set a predetermined current size variation threshold value, the size of current changing value that EDDY CURRENT arrives less than or etc.
Allowance is confirmed as uniform, the allowance that the most rough machined workpiece configurations leaves when predetermined current size variation threshold value
Uneven.In specific implementation process, size of current changing value is the current differential between maximum current and minimum current.At eddy current
During detection, coil is not required to directly contact with measured workpiece, therefore can carry out high speed detection.
Concrete, in the step of finishing workpiece profile to size, particularly as follows: use monocrystalline diamond milling cutter along pottery
The winding direction climb cutting processing workpiece configurations of based composites is to size.Such as, bit diameter φ 32mm or other replacements are used
The monocrystalline diamond milling cutter of diameter specifications.
In specific implementation process, in finishing workpiece profile to size procedure, cutting parameter is specifically as follows: lathe master
Axle rotating speed F3000, machine tool feed speed S1000, cut wide 1mm, cutting-in 0.5mm.By the roughing of above-mentioned workpiece configurations and essence
It is processed by different cutters, different cutting parameters so that the most suitable each procedure of processing, thus is further ensured that product matter
Amount.
Step 5, on the basis of metal end face 1 flatness of levelling metal end face 1 less than or equal to the second preset value.
Such as, the second preset value and the first preset value are identical, are also 0.05mm, then on the basis of the metal end face 1 of workpiece
Flatness≤the 0.05mm of levelling metal end face 1.According to the process requirements in specific implementation process, the first preset value is set to it
He falls within protection scope of the present invention at other approximations more than or less than 0.05mm.
Again determine workpiece centre on the basis of step 6, workpiece configurations after being refined to size, be processed metal end
Face 1 to size.
It is processed metal end face 1 to size, is specially and performs following steps 6A～step 6C successively:
Step 6A is processing metal end face 1: the side edge cutting metal end face 1 first using diamond coatings milling cutter is remaining to leaving
Amount, rear shear blade layered cutting metal end face 1 to the size using diamond coatings milling cutter.
Specifically, the included heat shield of processing of metal end face 1 and the processing of metal covering, for boring employed in step 6A
Head diameterThe diamond coatings milling cutter of chamfering R0.5.When the side edge of diamond coatings milling cutter cuts, machined parameters has
Body can be: machine spindle speed F1000, machine tool feed speed S2000, cuts wide 8mm, cutting-in 0.3mm.Diamond coatings milling cutter
Shear blade layered cutting time, machined parameters is specifically as follows: machine spindle speed F500, machine tool feed speed S2000.
Step 6B is the processing of end face seal boss: first use the side edge cutting end face seal boss of diamond coatings milling cutter to add
Station is put to one side made allowance, the rear shear blade climb cutting layered cutting end face seal boss from the top down using diamond coatings milling cutter
Working position is to one side made allowance, then uses diamond coatings milling cutter finish facing seal boss Working position to size.
Bit diameter φ 12mm, the diamond coatings milling cutter of chamfering R0.5 is used in step 6B.Side edge cutting end face is close
Machined parameters during envelope boss Working position is specifically as follows: machine spindle speed F1000, machine tool feed speed S2000, cutting-in
6mm, cuts wide 0.3mm.Machined parameters during shear blade climb cutting layered cutting end face seal boss Working position from the top down specifically may be used
Think: machine spindle speed F500, machine spindle speed S2000.
Step 6C, boring processing end face pin hole are to size.
By in above-mentioned steps 2～step 6, different machining feature uses different cutting parameters, more rationally, reliably,
Thus further increase machining accuracy.
Step 7, process for each opening.
Concrete, the processing of each opening includes step 7A～step 7C performed respectively, but does not limit 7A～step 7C
Processing sequence:
Step 7A, pressing plate, after the U-type groove limit of U-type groove to be processed is compressed by metal end face 1 to profile side 5, use spiral shell
Rotation plunge cut way carries out segmentation, layering processes U-type groove mouth 2；
Step 7B, pressing plate compress from metal end face 1 to profile side 5 by the limit, open sunken 3 of open sunken 3 to be processed
After, employing spiral plunge cut way carries out segmentation, layering processes open sunken 3；
Step 7C, pressing plate, after seal groove 4 limit of seal groove 4 to be processed is compressed by metal end face 1 to profile side 5, are adopted
With spiral plunge cut way carry out segmentation, layering process seal groove 4, seal groove is on face, open sunken.
In step 7A～step 7C, use different installation way by different feature machining, it is possible to prevent from processing U-shaped
When notch 2, open sunken 3 and seal groove 4, material falls slag, aliquation, collapses block, it is ensured that housing quality.
Step 8: Product checking:
The linear dimension of detection workpiece；The wall thickness of heat shield in EDDY CURRENT metal end face 1；With metal end face 1 and end face
Carry out detecting the form and position tolerance of workpiece on the basis of pin-and-hole.
In specific implementation process, the form and position tolerance detected includes product inside and outside shape profile tolerance etc., and the morpheme of workpiece is public
Difference can be detected by 3 D detection method, the form and position tolerance of three-dimensional values workpiece.Specifically it is referred to prior art, for
Description succinct, repeats no more herein.
Step 9: by the end face pin hole fixed protection plate at two ends.Concrete, make protective plate, by the end face pin at two ends
Protective plate is fixed on metal end face 1 by hole, protection heat shield seamed edge and end face seal boss.
The one or more technical schemes used by the embodiment of the present invention of foregoing description, at least have following technology effect
Fruit or advantage:
1, first first piece profile on the basis of the pin-and-hole bottom outlet processed, then determine with eddy current detection method and add spare time
After amount uniformity, workpiece configurations described in polish is to size, then finished metal end face and each opening on the basis of workpiece configurations,
Thus EDDY CURRENT combines with Reference Transforming and determines the Cutter coordinate system of each step, can analyze ceramic matric composite cabin comprehensively
The allowance of section assembly, thus accurately control the wall unevenness that machining deformation brings, and when combining processing different characteristic
For different machining benchmarks, solve existing processing method when the section assembly of processing ceramic based composites cabin, be difficult to control to processing
The technical problem of the wall unevenness that deformation brings, is effectively increased the Product Precision of ceramic matric composite cabin section assembly, to protect
Card meets Product Assembly requirement.
2, U-type groove is gone out owing to the U-type groove limit of U-type groove to be processed is compressed post-treatment from metal end face to profile side by pressing plate
Mouthful；The limit, open sunken of open sunken to be processed is compressed post-treatment from metal end face to profile side and goes out open sunken by pressing plate；
The sealing trough rim of seal groove to be processed is compressed post-treatment from metal end face to described profile side and goes out seal groove by pressing plate, and processing is not
Different clamping position is used, it is to avoid the heat shield seamed edge aliquation of metal end face in the course of processing, fall slag, energy with feature correspondence
Ensure housing quality.
3, it is fixed on metal end face owing to have employed protective plate, protects the heat shield seamed edge of metal end face and seal convex
Platform.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know basic creation
Property concept, then can make other change and amendment to these embodiments.So, claims are intended to be construed to include excellent
Select embodiment and fall into all changes and the amendment of the scope of the invention.
Obviously, those skilled in the art can carry out various change and the modification essence without deviating from the present invention to the present invention
God and scope.So, if these amendments of the present invention and modification belong to the scope of the claims in the present invention and equivalent technologies thereof
Within, then the present invention is also intended to comprise these change and modification.
Claims (8)
1. the processing method of a ceramic matric composite cabin section assembly, it is characterised in that include the following steps performed successively:
On the basis of the metal end face of workpiece, the flatness of levelling described metal end face is less than or equal to the first preset value；
On described workpiece machined go out pin-and-hole bottom outlet on the basis of just determine workpiece centre, carry out roughing and go out workpiece configurations to staying
Having allowance, wherein, described pin-and-hole bottom outlet is processed on described metal end face:
Described in EDDY CURRENT, allowance is the most uniform；
After allowance described in the results verification of described EDDY CURRENT is uniform, described in polish, workpiece configurations is to size；
On the basis of described metal end face, the flatness of levelling described metal end face is less than or equal to the second preset value；
Again determine workpiece centre on the basis of described workpiece configurations after being refined to size, be processed described metal end face
To size.
2. the processing method of ceramic matric composite cabin as claimed in claim 1 section assembly, it is characterised in that described with described
On workpiece machined go out pin-and-hole bottom outlet on the basis of just determine workpiece centre, carry out roughing and go out workpiece configurations and add spare time to leaving
Amount, including:
The machined surface of workpiece configurations described in trial cut is carried out to leaving uniform surplus to big end from the small end of described workpiece；
Use polycrystalline diamond milling cutter by end-state made allowance along ceramic matric composite winding direction climb cutting process institute
The described machined surface stating workpiece configurations is all shown in light.
3. the processing method of ceramic matric composite cabin as claimed in claim 2 section assembly, it is characterised in that described final shape
State made allowance is 0.5～1mm.
4. the processing method of ceramic matric composite cabin as claimed in claim 1 section assembly, it is characterised in that described polish
Described workpiece configurations to size, particularly as follows:
Use monocrystalline diamond milling cutter along the winding direction climb cutting described workpiece configurations of processing of ceramic matric composite to size.
5. the processing method of ceramic matric composite cabin as claimed in claim 1 section assembly, it is characterised in that described with finishing
Work determines workpiece centre to the described workpiece configurations after size again, is processed described metal end face to size, bag
Include the following steps performed successively:
Metal end face procedure of processing: first the side edge described metal end face of cutting of employing diamond coatings milling cutter is to leaving surplus, after
Use metal end face described in the shear blade layered cutting of described diamond coatings milling cutter to size；
End face seal boss procedure of processing: first use the side edge cutting end face seal boss machining position of described diamond coatings milling cutter
Put to one side made allowance, use end face seal described in the shear blade climb cutting layered cutting from the top down of described diamond coatings milling cutter afterwards
Boss Working position is to one side made allowance, then uses end face seal boss machining position described in described diamond coatings milling cutter polish
Put to size；
Boring processing end face pin hole is to size.
6. the processing method of ceramic matric composite cabin as claimed in claim 1 section assembly, it is characterised in that carry out described
Processing described metal end face to after size, described processing method also includes:
Pressing plate, after the U-type groove limit of U-type groove to be processed is compressed by described metal end face to profile side, uses spiral plunge cut way
Carry out segmentation, layering processes U-type groove mouth；
Pressing plate, after the limit, open sunken of open sunken to be processed is compressed by described metal end face to described profile side, uses institute
State spiral plunge cut way carry out segmentation, layering process open sunken；
Pressing plate, after the sealing trough rim of seal groove to be processed is compressed by described metal end face to described profile side, uses described spiral shell
Rotation plunge cut way carries out segmentation, layering processes seal groove.
7. the processing method of ceramic matric composite cabin as claimed in claim 6 section assembly, it is characterised in that in described employing
Described spiral plunge cut way carry out segmentation, layering process seal groove after, described processing method also includes:
Detect the linear dimension of described workpiece；
The wall thickness of heat shield in metal end face described in EDDY CURRENT；
By described metal end face and be machined to size end face pin hole on the basis of carry out detecting the form and position tolerance of described workpiece；
By the described end face pin hole fixed protection plate at two ends.
8. the processing method of ceramic matric composite cabin as claimed in claim 1 section assembly, it is characterised in that described first pre-
If value and described second preset value are 0.05mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610786285.5A CN106271444B (en) | 2016-08-31 | 2016-08-31 | The processing method of ceramic matric composite bay section component |
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| CN201610786285.5A CN106271444B (en) | 2016-08-31 | 2016-08-31 | The processing method of ceramic matric composite bay section component |
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| CN107570970A (en) * | 2017-09-20 | 2018-01-12 | 湖北三江航天红阳机电有限公司 | A kind of large-scale bay section housing docking pin-and-hole processing method |
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| CN103753124A (en) * | 2013-12-19 | 2014-04-30 | 湖北三江航天红阳机电有限公司 | Machining method for large cast titanium alloy diamond-shaped cabin shell |
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| CN101633100A (en) * | 2008-07-21 | 2010-01-27 | 鞠小平 | Method for processing forward gear shifting block of automobile parts |
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| Publication number | Publication date |
|---|---|
| CN106271444B (en) | 2018-08-03 |
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