CN114211206A - Method for processing multi-cavity casting cabin body of revolving body - Google Patents
Method for processing multi-cavity casting cabin body of revolving body Download PDFInfo
- Publication number
- CN114211206A CN114211206A CN202111582735.6A CN202111582735A CN114211206A CN 114211206 A CN114211206 A CN 114211206A CN 202111582735 A CN202111582735 A CN 202111582735A CN 114211206 A CN114211206 A CN 114211206A
- Authority
- CN
- China
- Prior art keywords
- processing
- cavity
- machining
- revolving body
- allowance
- Prior art date
- 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.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
- B23Q17/00—Arrangements for observing, indicating or measuring on machine tools
- B23Q17/22—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring existing or desired position of tool or work
-
- 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
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Numerical Control (AREA)
Abstract
The invention discloses a method for processing a multi-cavity casting cabin body of a revolving body, which comprises the following steps: s1: detecting the inner and outer molded surfaces of the casting by a laser scanning method, and comparing a theoretical model with a scanning result to obtain residual data of each part of the inner and outer molded surfaces; s2: then, the allowance data of the selected position is utilized to align the machining reference of the part and scribe; s3: aligning a datum line on a milling machine, and reserving and processing an excircle and an end face; s4: and (4) aligning the outer circle machined by the milling machine by using a lathe for subsequent machining. According to the invention, the milling machine processing establishes the processing reference for the lathe processing, so that the problem that the lathe cannot align the reference line is solved, meanwhile, a reliable processing reference can be used, the efficient turning method is adopted for processing, the trial cutting time and the equipment occupation are reduced, and the method is a reliable and convenient processing method.
Description
Technical Field
The invention belongs to the technical field of cabin section machining, and relates to a method for machining a multi-cavity casting cabin body of a revolving body.
Background
The cast cabin section has deformation after casting, and the problems of insufficient wall thickness, insufficient appearance allowance, misplacement of the containing cavity and the like are easily caused. The multi-cavity cabin section needs to simultaneously consider the shape, the wall thickness and the size precision of each cavity during processing, and has processing difficulty. The laser scanning technology can be adopted to establish the benchmark before processing, but the revolving body cabin section generally adopts turning processing with high processing efficiency, and the benchmark established by scanning data cannot be aligned on a lathe, so that the benchmark can not be established by effectively utilizing the scanning data.
Disclosure of Invention
Objects of the invention
The purpose of the invention is: the machining method has high reliability and can effectively control the machining precision of the casting, the datum line is aligned by the milling machine and is transferred to the lathe, the problem that the lathe cannot directly utilize the datum line is solved, and the machining precision control of the multi-cavity complex casting cabin section of the revolving body is further realized.
(II) technical scheme
In order to solve the technical problem, the invention provides a method for processing a multi-cavity casting cabin body of a revolving body, which comprises the following steps:
s1: detecting the inner and outer molded surfaces of the casting by a laser scanning method, and comparing a theoretical model with a scanning result to obtain residual data of each part of the inner and outer molded surfaces;
s2: then, the allowance data of the selected position is utilized to align the machining reference of the part and scribe;
s3: aligning a datum line on a milling machine, and reserving and processing an excircle and an end face;
s4: and (4) aligning the outer circle machined by the milling machine by using a lathe for subsequent machining.
In step S2, the specification of the selected position is set as: two points are selected, which are not vertices, on the same straight line of the lumen, as far as possible, and with as little surface relief as possible.
In step S2, 8 points of residual data at positions right above, right below, right left, and right of the front end of the heading near the end face in the inner cavity, and right above, right below, right left, and right of the rear end, the residual data of the side wall of the cavity, and the residual data of the inner wall of the end frame are selected.
In step S2, the part machining references include a horizontal reference, a symmetrical reference, a heading positioning reference, and an angular direction reference.
In step S2, selecting a horizontal reference and a symmetric reference: and selecting the positions right above, right below, right left and right of the inner cavity with the front end close to the end surface, the positions right above, right below, right left and right of the inner cavity with the rear end close to the end surface, and taking the residual data of the inner cavities at 8 point positions as reference values to determine a horizontal datum and a symmetrical datum.
In step S2, selecting a heading reference: and the course selects the allowance at the end frame or the numerical value of the existing plane as a reference value to determine a processing standard.
In step S2, selecting an angular direction reference: and determining the angular direction reference by taking the allowance of the side wall of the cavity of the cabin section as the reference.
In step S2, drawing lines by a bench worker according to the allowance reference value data to establish a machining standard; when scribing, supporting the excircle, and correctly matching 8 point margins at the positions right above, right below, right left and right of the front end and the positions right above, right below, right left and right of the rear end; and determining the angle direction according to the allowance of the side wall of the accommodating cavity, and marking a horizontal datum line and a symmetrical plane line on the excircle of the part after determining the datum.
In step S3, the end face of the part is placed downwards on a three-axis milling machine, the table is made from top to bottom on the milling machine by using the combination of a main shaft and a lever meter, the horizontal datum line and the symmetrical plane line on the excircle are aligned, the posture of the part is adjusted, and the alignment error is within 0.1; during machining, the front end face and the rear end face are milled flat, and a section of excircle is machined in a reserved amount to establish a reference for a subsequent lathe; and placing the machined end face on a platform, determining a course datum by using the allowance of the side wall of the containing cavity, and marking the course datum.
And step S4, aligning the end face and a section of excircle processed by the milling machine on a lathe, reserving and processing the whole excircle, confirming that the processing reference of the part is correct by detecting the wall thickness data of each part in the processing, and carrying out reference adjustment in real time when deviation occurs, and finally processing the part in place.
(III) advantageous effects
According to the method for processing the multi-cavity casting cabin of the revolving body, the laser scanning detection method is used before processing, the allowance condition, the deficiency condition and the like of complex casting parts are mastered, and compared with a method for centering the allowance of the characteristic point adopted by a conventional centering method, the method for processing the multi-cavity casting cabin of the revolving body has the advantages that the processing precision of the parts can be guaranteed better by considering the allowance data of all positions, and a reliable processing reference can be obtained. In practical application, the method is used for marking and aligning, a milling machine is used for establishing a machining reference for lathe machining, the problem that a lathe cannot align the reference line is solved, meanwhile, a reliable machining reference can be used, efficient turning method machining is adopted, machining trial cutting time and equipment occupation are reduced, and the method is a reliable and convenient machining method.
Drawings
FIG. 1 is a flow chart of the process of the present invention.
Fig. 2 is a schematic view of the structure of the cabin.
FIG. 3 is a front view of the datum.
FIG. 4 is a side view of a datum.
Detailed Description
In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
Referring to fig. 1, the invention provides a method for processing a multi-cavity casting cabin section of a revolving body, which comprises the following steps:
s1: detecting the inner and outer molded surfaces of the casting by a laser scanning method, and comparing a theoretical model with a scanning result to obtain residual data of each part of the inner and outer molded surfaces;
s2: then, the allowance data of the selected position is utilized to align the part datum and scribe;
s3: aligning a datum line on a milling machine, and reserving and processing an excircle and an end face;
s4: and (4) aligning the outer circle machined by the milling machine by using a lathe for subsequent machining.
In step S2, the amount of laser scanning data is large, and only the remaining data at a specific position is selected for reference for convenience of the operation method. As shown in fig. 2 to 4, when establishing the reference by referring to the scan data, two points with the same straight line of the cavity, as far as possible and as small surface relief as possible should be selected, but the top point is not selected because the cast part usually has large surface relief in the edge and fillet area and the selection error is large. Therefore, the characteristic positions can generally select 8 points of residual data at positions right above, below, right left and right of the front end of the course close to the end surface in the inner cavity, right above, below, right left and right of the rear end, the residual data of the side wall of the cavity, the residual data of the inner wall of the end frame and the like. The allowance data of the inner cavity is selected as much as possible, because the casting generally has no allowance in the inner cavity and large allowance on the outer side, when the appearance of the casting is processed through allowance, the deviation of reference alignment can be found in time and adjusted in time; if the shape data is selected, the accuracy of the datum alignment cannot be judged according to the inner cavity allowance data after the shape is processed.
The processing reference of the cabin part relates to a horizontal reference, a symmetrical reference, a course positioning reference and an angle direction reference: a) selecting a horizontal reference and a symmetrical reference: selecting a reference as much as possible, selecting positions right above, right below, right left and right of the inner cavity with the front end close to the end surface and positions right above, right below, right left and right of the inner cavity with the rear end close to the end surface, and determining a horizontal reference and a symmetrical reference by using the residual data of the inner cavity at 8 point positions as reference values; b) selecting a course reference: and the course selects the allowance at the end frame or the numerical value of the existing plane as a reference value to determine a processing standard. c) Selecting an angular direction reference: in order to avoid deflection errors when the reference of the revolving body part is established, the angular direction reference is determined by taking the allowance of the side wall of the containing cavity of the cabin section as the reference.
Specifically, the bench worker scribes based on the residual reference value data to establish a machining standard. When scribing, supporting the excircle, and correctly matching 8 point margins at the positions right above, right below, right left and right of the front end and the positions right above, right below, right left and right of the rear end; and determining the angle direction by the allowance of the side wall of the cavity. After the reference is determined, a horizontal reference line and a symmetrical plane line are marked on the excircle of the part.
In step S3, the end face of the part is placed on a three-axis milling machine, the spindle and lever meter combination is used on the milling machine to make a meter from top to bottom, the horizontal reference line and the symmetrical plane line on the excircle are aligned, the posture of the part is adjusted, and the alignment error is within 0.1. During machining, the front end face and the rear end face are milled flat, and a section of excircle is machined in a reserved amount to establish a reference for a subsequent lathe. And further, marking a course datum line, placing the machined end face on a platform, determining a course datum by using the allowance of the side wall of the cavity, and marking the course datum line.
In step S4, the end face and a section of excircle processed by the milling machine are aligned on the lathe, the whole excircle is processed by allowance, the processing reference of the part is confirmed to be correct by detecting the wall thickness data of each part in the processing, and a small amount of reference adjustment can be performed when deviation occurs, so that the reference deviation of the part is avoided. And finally, machining the part in place.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A method for processing a multi-cavity casting cabin body of a revolving body is characterized by comprising the following steps:
s1: detecting the inner and outer molded surfaces of the casting by a laser scanning method, and comparing a theoretical model with a scanning result to obtain residual data of each part of the inner and outer molded surfaces;
s2: then, the allowance data of the selected position is utilized to align the machining reference of the part and scribe;
s3: aligning a datum line on a milling machine, and reserving and processing an excircle and an end face;
s4: and (4) aligning the outer circle machined by the milling machine by using a lathe for subsequent machining.
2. The method for machining a multi-cavity casting capsule body of a revolving body according to claim 1, wherein in step S2, the rule for determining the selected position is set as: two points are selected, which are not vertices, on the same straight line of the lumen, as far as possible, and with as little surface relief as possible.
3. The method for processing the revolving body multi-cavity casting cabin according to claim 2, wherein in step S2, 8 point residual data at positions right above, right below, right left and right of the front end of the heading near the end face and at positions right above, right below, right left and right of the rear end in the inner cavity, residual data of the side wall of the cavity, and residual data of the inner wall of the end frame are selected.
4. The method for machining the revolving body multi-cavity casting cabin according to claim 3, wherein in step S2, the part machining references include a horizontal reference, a symmetrical reference, a heading positioning reference, and an angular direction reference.
5. The method for processing the revolving body multi-cavity casting cabin according to claim 4, wherein in step S2, the selection of the horizontal reference and the symmetrical reference is as follows: and selecting the positions right above, right below, right left and right of the inner cavity with the front end close to the end surface, the positions right above, right below, right left and right of the inner cavity with the rear end close to the end surface, and taking the residual data of the inner cavities at 8 point positions as reference values to determine a horizontal datum and a symmetrical datum.
6. The method for processing the revolving body multi-cavity casting cabin according to claim 5, wherein in step S2, the heading reference is selected as follows: and the course selects the allowance at the end frame or the numerical value of the existing plane as a reference value to determine a processing standard.
7. The method for processing the revolving body multi-cavity casting cabin according to claim 6, wherein in step S2, the angular direction reference is selected from the group consisting of: and determining the angular direction reference by taking the allowance of the side wall of the cavity of the cabin section as the reference.
8. The method for machining the revolving body multi-cavity casting cabin according to claim 7, wherein in step S2, a bench worker scribes a line according to the allowance reference value data to establish a machining standard; when scribing, supporting the excircle, and correctly matching 8 point margins at the positions right above, right below, right left and right of the front end and the positions right above, right below, right left and right of the rear end; and determining the angle direction according to the allowance of the side wall of the accommodating cavity, and marking a horizontal datum line and a symmetrical plane line on the excircle of the part after determining the datum.
9. The method for processing the revolving body multi-cavity casting capsule body according to claim 8, wherein in step S3, the end face of the part is placed downwards on a three-axis milling machine, the table is made on the milling machine from top to bottom by using the combination of the spindle and the lever meter, the horizontal reference line and the symmetry plane line on the excircle are aligned, the posture of the part is adjusted, and the alignment error is within 0.1; during machining, the front end face and the rear end face are milled flat, and a section of excircle is machined in a reserved amount to establish a reference for a subsequent lathe; and placing the machined end face on a platform, determining a course datum by using the allowance of the side wall of the containing cavity, and marking the course datum.
10. The method for processing the revolving body multi-cavity casting capsule body according to claim 9, wherein in step S4, the end face and a section of the outer circle processed by the milling machine are aligned on a lathe, the whole outer circle is processed in a reserved manner, the processing reference of the part is confirmed to be correct by detecting the wall thickness data of each part during processing, the reference adjustment is performed in real time when deviation occurs, and the part is finally processed in place.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111582735.6A CN114211206B (en) | 2021-12-22 | 2021-12-22 | Method for processing multi-cavity casting cabin body of revolving body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111582735.6A CN114211206B (en) | 2021-12-22 | 2021-12-22 | Method for processing multi-cavity casting cabin body of revolving body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114211206A true CN114211206A (en) | 2022-03-22 |
| CN114211206B CN114211206B (en) | 2022-10-25 |
Family
ID=80705085
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111582735.6A Active CN114211206B (en) | 2021-12-22 | 2021-12-22 | Method for processing multi-cavity casting cabin body of revolving body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114211206B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114800056A (en) * | 2022-04-30 | 2022-07-29 | 徐德富 | Method for machining and mounting high-form-position precision part |
| CN117282995A (en) * | 2023-11-24 | 2023-12-26 | 天津航天长征火箭制造有限公司 | Method for detecting and processing machining allowance of space spinning box bottom and electronic equipment |
Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102229048A (en) * | 2011-06-11 | 2011-11-02 | 吴江市天龙机械有限公司 | Method for machining aluminum alloy thin-wall cabin |
| CN103586640A (en) * | 2013-11-14 | 2014-02-19 | 湖北三江航天红阳机电有限公司 | Method for machining ductile thin-wall multi-opening conical revolved body and revolved body |
| CN104070513A (en) * | 2013-12-09 | 2014-10-01 | 北京航星机器制造有限公司 | Method for precision lineation of thin-wall special-shaped cast cabin |
| CN106002088A (en) * | 2016-05-24 | 2016-10-12 | 湖北三江航天红阳机电有限公司 | Manufacturing method for integral wing-body-fused cabin |
| CN106239066A (en) * | 2016-08-31 | 2016-12-21 | 湖北三江航天红阳机电有限公司 | A kind of processing method of cabin section workpiece |
| CN106425303A (en) * | 2016-10-28 | 2017-02-22 | 航天科工哈尔滨风华有限公司 | Processing method of large-scale thin-wall cabin shell body and clamp |
| CN109079584A (en) * | 2018-09-03 | 2018-12-25 | 北京星航机电装备有限公司 | A kind of hot investment casting part machining benchmark aligning method |
| CN109531273A (en) * | 2018-11-15 | 2019-03-29 | 北京星航机电装备有限公司 | A kind of casting bay section processing method based on precise detection technology |
| CN110587231A (en) * | 2019-09-06 | 2019-12-20 | 北京星航机电装备有限公司 | Method for processing composite cabin body made of thermal protection material and metal material |
| CN110631535A (en) * | 2019-09-02 | 2019-12-31 | 北京星航机电装备有限公司 | Machining reference transmission method for large casting cabin type structural part |
| CN110744262A (en) * | 2019-11-07 | 2020-02-04 | 北京星航机电装备有限公司 | Machining method for large complex thin-wall cabin part |
| WO2020253818A1 (en) * | 2019-06-20 | 2020-12-24 | 苏州市意可机电有限公司 | Machining process for large-diameter thin-walled part |
| CN112276490A (en) * | 2020-10-22 | 2021-01-29 | 航天科工哈尔滨风华有限公司 | Method for processing large-scale cast stainless steel wing cabin fusion cabin section |
| CN112589168A (en) * | 2020-12-02 | 2021-04-02 | 航天科工哈尔滨风华有限公司 | Method for machining inner cavity of special-shaped thin-wall cabin section |
| CN112643368A (en) * | 2020-12-08 | 2021-04-13 | 北京星航机电装备有限公司 | Deformation control method for vertical clamping machining of special-shaped thin-wall cabin parts |
| CN112643293A (en) * | 2020-12-07 | 2021-04-13 | 北京星航机电装备有限公司 | Machining method for large-sized cylinder thin-wall cabin section part |
| CN112846478A (en) * | 2020-12-31 | 2021-05-28 | 湖北三江航天红阳机电有限公司 | Machining method for large thin-wall easily-deformable cabin shell |
-
2021
- 2021-12-22 CN CN202111582735.6A patent/CN114211206B/en active Active
Patent Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102229048A (en) * | 2011-06-11 | 2011-11-02 | 吴江市天龙机械有限公司 | Method for machining aluminum alloy thin-wall cabin |
| CN103586640A (en) * | 2013-11-14 | 2014-02-19 | 湖北三江航天红阳机电有限公司 | Method for machining ductile thin-wall multi-opening conical revolved body and revolved body |
| CN104070513A (en) * | 2013-12-09 | 2014-10-01 | 北京航星机器制造有限公司 | Method for precision lineation of thin-wall special-shaped cast cabin |
| CN106002088A (en) * | 2016-05-24 | 2016-10-12 | 湖北三江航天红阳机电有限公司 | Manufacturing method for integral wing-body-fused cabin |
| CN106239066A (en) * | 2016-08-31 | 2016-12-21 | 湖北三江航天红阳机电有限公司 | A kind of processing method of cabin section workpiece |
| CN106425303A (en) * | 2016-10-28 | 2017-02-22 | 航天科工哈尔滨风华有限公司 | Processing method of large-scale thin-wall cabin shell body and clamp |
| CN109079584A (en) * | 2018-09-03 | 2018-12-25 | 北京星航机电装备有限公司 | A kind of hot investment casting part machining benchmark aligning method |
| CN109531273A (en) * | 2018-11-15 | 2019-03-29 | 北京星航机电装备有限公司 | A kind of casting bay section processing method based on precise detection technology |
| WO2020253818A1 (en) * | 2019-06-20 | 2020-12-24 | 苏州市意可机电有限公司 | Machining process for large-diameter thin-walled part |
| CN110631535A (en) * | 2019-09-02 | 2019-12-31 | 北京星航机电装备有限公司 | Machining reference transmission method for large casting cabin type structural part |
| CN110587231A (en) * | 2019-09-06 | 2019-12-20 | 北京星航机电装备有限公司 | Method for processing composite cabin body made of thermal protection material and metal material |
| CN110744262A (en) * | 2019-11-07 | 2020-02-04 | 北京星航机电装备有限公司 | Machining method for large complex thin-wall cabin part |
| CN112276490A (en) * | 2020-10-22 | 2021-01-29 | 航天科工哈尔滨风华有限公司 | Method for processing large-scale cast stainless steel wing cabin fusion cabin section |
| CN112589168A (en) * | 2020-12-02 | 2021-04-02 | 航天科工哈尔滨风华有限公司 | Method for machining inner cavity of special-shaped thin-wall cabin section |
| CN112643293A (en) * | 2020-12-07 | 2021-04-13 | 北京星航机电装备有限公司 | Machining method for large-sized cylinder thin-wall cabin section part |
| CN112643368A (en) * | 2020-12-08 | 2021-04-13 | 北京星航机电装备有限公司 | Deformation control method for vertical clamping machining of special-shaped thin-wall cabin parts |
| CN112846478A (en) * | 2020-12-31 | 2021-05-28 | 湖北三江航天红阳机电有限公司 | Machining method for large thin-wall easily-deformable cabin shell |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114800056A (en) * | 2022-04-30 | 2022-07-29 | 徐德富 | Method for machining and mounting high-form-position precision part |
| CN117282995A (en) * | 2023-11-24 | 2023-12-26 | 天津航天长征火箭制造有限公司 | Method for detecting and processing machining allowance of space spinning box bottom and electronic equipment |
| CN117282995B (en) * | 2023-11-24 | 2024-02-02 | 天津航天长征火箭制造有限公司 | Method for detecting and processing machining allowance of space spinning box bottom and electronic equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114211206B (en) | 2022-10-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114211206B (en) | Method for processing multi-cavity casting cabin body of revolving body | |
| CN105467927B (en) | It is a kind of that forging and casting processing positioning method of crossing is exempted from based on registration alignment | |
| CN109531273B (en) | Casting cabin section processing method based on precision detection technology | |
| CN107378497A (en) | Three dissection type high inclination-angles tilt processing and detecting system and its processing and the detection method of casing | |
| US20230121919A1 (en) | Method for generating machining cutter path for curved deep cavity surface | |
| CN112197725B (en) | Accurate positioning method for large composite material part machining tool | |
| CN111266803B (en) | Processing method of thin-wall special-shaped metal casting | |
| CN111069642B (en) | Three-dimensional space inclined hole machining process | |
| CN112685858B (en) | Forging piece correcting and adjusting method based on three-dimensional scanning auxiliary positioning | |
| CN112222497B (en) | Method for processing large conical adapter space curved surface on three-axis linkage milling machine | |
| JP2006517151A (en) | Method and apparatus for manufacturing service blades | |
| CN108581365B (en) | A kind of processing method of enclosed ternary slot welding impeller | |
| CN110928234A (en) | Use method of universal angle milling head | |
| CN108555533A (en) | The splicing assembly method of carbon fibre composite space truss | |
| CN101391358B (en) | Method for processing welding frame device using bolt, pun bush as positioning reference | |
| CN110153896B (en) | Method for rapidly and stably cutting rough edges of forge pieces by water | |
| CN108073131B (en) | Mirror milling skin appearance error real-time non-contact measurement and compensation device and skin thickness accurate control method | |
| CN115837563A (en) | Machining method for improving centering precision of two tooth parts of herringbone gear shaft | |
| CN210523854U (en) | Roll arm boring machining tool | |
| CN211490746U (en) | Machining cutter verifying device | |
| CN209969800U (en) | Copper male for processing hidden glue inlet | |
| CN113814795B (en) | Workpiece processing data measuring, correcting and checking method and system based on dual-channel on-machine measurement | |
| CN110181229A (en) | A kind of manufacturing method of ship and offshore equipment middle gear case | |
| CN109158671B (en) | Machining correction method for three-dimensional flow blade profiling die | |
| CN111090259A (en) | Method for checking and correcting workpiece rotating shaft coordinate deviation in numerical control system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information |
Inventor after: Lin Lin Inventor after: Chen Xingzu Inventor after: Ding Guozhi Inventor after: Yang Hongqing Inventor after: Xu Baode Inventor before: Lin Lin Inventor before: Chen Xingzu Inventor before: Xu Baode |
|
| CB03 | Change of inventor or designer information |