CN112643293A - Machining method for large-sized cylinder thin-wall cabin section part - Google Patents

Machining method for large-sized cylinder thin-wall cabin section part Download PDF

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Publication number
CN112643293A
CN112643293A CN202011438301.4A CN202011438301A CN112643293A CN 112643293 A CN112643293 A CN 112643293A CN 202011438301 A CN202011438301 A CN 202011438301A CN 112643293 A CN112643293 A CN 112643293A
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processing
machining
tool
milling
cabin
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张风磊
李中华
邢鹏
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Beijing Xinghang Electromechanical Equipment Co Ltd
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Beijing Xinghang Electromechanical Equipment Co Ltd
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00Making specific metal objects by operations not covered by a single other subclass or a group in this subclass

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Abstract

The invention discloses a method for processing a large-sized cylinder thin-wall cabin part, which comprises the following processing steps: s1, performing laser scanning on the casting blank and performing fitting comparison on a theoretical model to determine a rough machining reference; s2, milling a reference surface and a reference pin hole; s3, roughly machining the characteristics of the excircle and the end face by a lathe; s4 stabilizing treatment; s5, determining a finish machining reference by detecting the deformation condition by a bench worker; s6, milling to obtain a finish machining standard; s7 finishing by turning; s8 finish machining external features by numerical milling; and S9, finishing the inner cavity features by milling. The invention ensures that all the characteristics of the complex parts are processed in place, and meets the use requirements; the tool is used for clamping, so that the rigidity of the thin-wall part is improved, and the clamping deformation is reduced; the clamping of large thin-wall parts and the reference transmission among different working procedures are realized; the datum is determined through scanning, and after the datum is transmitted through the tool, the borrowing amount adjusting time on the lathe is shortened.

Description

Machining method for large-sized cylinder thin-wall cabin section part
Technical Field
The invention belongs to the technical field of machining, and relates to a machining method of a large-sized cylinder thin-wall cabin part.
Background
The large-sized cylinder thin-wall cabin section part is ZL114A, the whole body is of a cylinder structure, and the diameter of the outer circle of the large-sized cylinder thin-wall cabin section part is
Figure BDA0002821417470000011
The height is 570mm, the end surface has butt joint holes and step features, and the inner cavityThe surface and the ribs are provided with mounting bosses and mounting holes, the front and rear inner end surfaces have end surface characteristics, the typical wall thickness of the part is 2.5 +/-0.2 mm, the size of the part is large, the processing characteristics are more, and the related procedures are more.
Disclosure of Invention
Objects of the invention
The purpose of the invention is: the processing method of the large-sized cylinder thin-wall cabin part is provided, clamping and reference transmission of the large-sized cylinder thin-wall cabin part are achieved, part processing deformation is reduced, and all features are processed in place.
(II) technical scheme
In order to solve the technical problem, the invention provides a large-sized cylindrical thin-wall cabin section part, which mainly comprises the following processing flows: the laser scanning blank and a theoretical model are matched and compared to determine a datum, a datum plane and a datum pin hole are machined through numerical milling, the outer circle and the end face are roughly machined through a lathe, the characteristics are stabilized, the deformation condition is detected through a bench worker to determine a finish machining datum, the finish machining datum is machined through numerical milling, the finish machining datum is turned and finished, the external characteristics are machined through numerical milling, the characteristics of an inner cavity are machined through numerical control boring, and machining is finished.
(III) advantageous effects
The processing method of the large-sized cylinder thin-wall cabin part provided by the technical scheme ensures that all characteristics of the complex part are processed in place, and meets the use requirement; the tool is used for clamping, so that the rigidity of the thin-wall part is improved, and the clamping deformation is reduced; the clamping of large thin-wall parts and the reference transmission among different working procedures are realized; the datum is determined through scanning, and after the datum is transmitted through the tool, the borrowing amount adjusting time on the lathe is shortened.
Drawings
Fig. 1 is a schematic view of a tooling in turning.
Fig. 2 is a schematic view of a boring and clamping tool.
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.
Aiming at the characteristics of large size and thin wall of a large-sized cylinder thin-wall cabin part, the invention compares a laser scanning casting blank with a theoretical model, adjusts each position of the blank to have enough allowance so as to meet the best fitting state, and obtains a processing reference by reverse deduction.
After determining the reference through scanning, rough machining such as part number milling, turning and the like is carried out, machining stress is removed through stabilization, and then characteristics of the outer circle and the inner cavity are subjected to line milling, turning and finish machining.
Aiming at the problems of difficult clamping and reference transmission and large part processing deformation caused by large appearance and thin wall thickness of parts, the turning and boring clamping tool is designed. The specific structure of the tool is shown in figure 1, and mainly comprises a bottom plate clamping plate 2, a part and a tool positioning pin hole 3, wherein the tool and a machine tool A shaft positioning pin 4 penetrate through a tool center hole to position and install the tool on a machine tool A shaft workbench 1, and the bottom plate clamping plate 2 is provided with a plurality of parts and tool positioning pin holes 3 along the circumferential direction and used for installing and positioning parts to be machined.
The main processing flow of the large-sized cylinder thin-wall cabin part is as follows: the laser scanning blank and a theoretical model are matched and compared to determine a datum, a datum plane and a datum pin hole are machined through numerical milling, the outer circle and the end face are roughly machined through a lathe, the characteristics are stabilized, the deformation condition is detected through a bench worker to determine a finish machining datum, the finish machining datum is machined through numerical milling, the finish machining datum is turned and finished, the external characteristics are machined through numerical milling, the characteristics of an inner cavity are machined through numerical control boring, and machining is finished.
S1: and (4) determining a rough machining reference by utilizing the laser scanning cast blank and the theoretical model fitting contrast.
The parts have larger structural size and more processing characteristics, in order to ensure that enough processing allowance and reference are determined accurately, laser scanning is carried out on the inner surface and the outer surface of a casting blank to obtain casting scanning data, then the scanning data is compared with the theoretical model allowance through special software, the allowance is adjusted uniformly and sufficiently, then a reference surface is determined in an adjusted state, and the reference surface is exported to UG software in an stp format for numerical control processing to determine a rough processing reference.
S2: and machining a reference end face according to the rough reference determined by laser scanning fitting, and transmitting the reference to the end face of the part and the end face process pin hole.
S3: the lathe rough-machines the outer circle and other features. Designing and manufacturing the turning, boring and clamping tool shown in figure 1. When the lathe is roughly machined, the bottom plate clamping disc 1 is fixed with the lathe workbench by utilizing a fixing screw to pass through a bolt hole in the bottom plate clamping disc 2 in the tool, and the bottom plate clamping disc 2 is adjusted to be coaxial with the lathe workbench. And inserting the cylindrical pin into the part and tooling positioning pin hole 3, and inserting the cabin section part with the positioning pin hole on the end surface after the processing of the step S2 into the cylindrical pin to realize quick positioning and alignment, then clamping and roughly processing.
S4: and (5) stabilizing treatment. And stabilizing and removing the processing stress.
S5: and (5) preliminarily determining a finish machining standard by a bench worker according to the rough machining standard and the part size detection deformation condition.
S6: and (4) performing end face milling, correcting the reference, and performing expanding processing on the end face process pin hole to obtain a subsequent finish-processed reference pin hole.
S7: and finishing all the turning process contents of the part by using a lathe. The process is similar to the rough turning process of the step S3, and the tooling clamping and the part processing are completed. The rough turning method is the same as the finish turning method, the difference is that the pin hole of the end face of the part is small during rough machining, the expansion machining is carried out during finish machining, and the positioning pin with the same specification is correspondingly selected by matching with the part in the baseplate clamping plate 2 in the tool and the tool positioning pin hole 3.
S8: and (5) performing finish machining on the external features by using a numerical milling machine. Similar to a lathe clamping mode, when a triaxial device (or a horizontal elbow) is machined, a fixing screw is used for fixing the bottom plate clamping plate 2 and a workbench of a numerical control machining center through a bolt hole in the bottom plate clamping plate 2 in the tool, the position relation between the bottom plate clamping plate 2 and the workbench is adjusted, reference transmission is carried out, and the end face and external machining characteristics of cabin section parts are completed.
S9: and (5) milling various characteristics of the inner cavity of the finish machining part. Because the size of the part is larger, when the elbow is extended into the inner cavity on a numerical control boring (horizontal type) to process the inner cavity characteristic of the part, the clamping is difficult, and the inner cavity is characterized by most being distributed in the circumferential direction, the part and the digital display rotary table are required to be coaxial, the part and the digital display rotary table are adjusted to be coaxial with each other with great difficulty due to large size of the part, therefore, firstly, a cylindrical pin is inserted into a positioning pin hole 3 of the part and the tooling, and a cabin part with a positioning pin hole on the rear end surface after being processed by the step S2 is inserted into the cylindrical pin, and then, fixing the base plate clamping plate 2 and the part on a machine tool A shaft workbench 1 through a tool and a machine tool A shaft positioning pin 4, wherein the machine tool A shaft workbench 1 is a digital display rotary table, ensuring that the part is coaxial with the digital display rotary table, fixing the part with the digital display rotary table by using a pull rod screw, aligning the outer circle of the chassis, completing reference transmission and clamping, processing an inner cavity and each characteristic hole, and processing each characteristic in the circumferential direction.
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 processing method of a large-sized cylinder thin-wall cabin section part is characterized by comprising the following processing steps: s1, performing laser scanning on the casting blank and performing fitting comparison on a theoretical model to determine a rough machining reference; s2, milling a reference surface and a reference pin hole; s3, roughly machining the characteristics of the excircle and the end face by a lathe; s4 stabilizing treatment; s5, determining a finish machining reference by detecting the deformation condition by a bench worker; s6, milling to obtain a finish machining standard; s7 finishing by turning; s8 finish machining external features by numerical milling; and S9, finishing the inner cavity features by milling.
2. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 1, wherein in step S1: and carrying out laser scanning on the inner surface and the outer surface of the casting blank to obtain casting scanning data, then comparing the scanning data with the theoretical model allowance, adjusting the allowance to be uniform and enough, then determining a reference surface in an adjusted state, and exporting the reference surface to UG software in an stp format for numerical control processing to determine a rough processing reference.
3. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 2, wherein in step S2: and machining a reference end face according to the rough reference determined by laser scanning fitting, and transmitting the reference to the end face of the part and the end face process pin hole.
4. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 3, wherein in step S3: designing a tool, which comprises a bottom plate clamping plate, wherein a part and a tool positioning pin hole are formed in the bottom plate clamping plate; during rough turning, fixing screws are utilized to pass through bolt holes in a baseplate clamping plate in the tool, the baseplate clamping plate is fixed with a lathe workbench, the baseplate clamping plate is adjusted to be coaxial with the lathe workbench, a cylindrical pin is inserted into a part and a tool positioning pin hole, a cabin section part with a positioning pin hole in the processed rear end face of the step S2 is inserted into the cylindrical pin, positioning and alignment are achieved, and then clamping is carried out, and rough turning is carried out.
5. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 4, wherein in step S4: the stabilization removes the machining stress.
6. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 5, wherein in step S5: and (5) preliminarily determining a finish machining standard by a bench worker according to the rough machining standard and the part size detection deformation condition.
7. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 6, wherein in step S6: and (4) performing end face milling, correcting the reference, and performing expanding processing on the end face process pin hole to obtain a subsequent finish-processed reference pin hole.
8. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 7, wherein in step S7: and (5) finishing tool clamping and part machining by using the tool in the step S3.
9. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 8, wherein in step S8: when the three-axis equipment is machined, the bottom plate clamping disc 2 is fixed with a workbench of a numerical control machining center by fixing screws through bolt holes in the bottom plate clamping disc 2 in the tooling, the position relation between the bottom plate clamping disc 2 and the workbench is adjusted, reference transmission is carried out, and the end face and external machining characteristics of cabin section parts are completed.
10. The method for processing the large-sized cylindrical thin-walled cabin-like section part according to claim 9, wherein in step S9: the method comprises the steps of firstly inserting a part and a tooling positioning pin hole by using a cylindrical pin, inserting a cabin section part with a positioning pin hole on the end surface after the processing of the step S2 into the cylindrical pin, then fixing a bottom plate clamping plate and the part on a machine tool A shaft workbench by using a tooling and a machine tool A shaft positioning pin, wherein the machine tool A shaft workbench is a digital display turntable, ensuring that the part and the digital display turntable are coaxial, fixing the part and the digital display turntable by using a pull rod screw, aligning the outer circle of a chassis, completing reference transmission and clamping, processing an inner cavity and each characteristic hole, and realizing the processing of each circumferential characteristic.
CN202011438301.4A 2020-12-07 2020-12-07 Machining method for large-sized cylinder thin-wall cabin section part Pending CN112643293A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114211206A (en) * 2021-12-22 2022-03-22 北京星航机电装备有限公司 Method for processing multi-cavity casting cabin body of revolving body
CN116140939A (en) * 2023-03-10 2023-05-23 北京星航机电装备有限公司 Processing method of thin-wall part with annular groove on end face

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Publication number Priority date Publication date Assignee Title
US5983496A (en) * 1996-03-15 1999-11-16 J.A. Hermanson Circular and oval flanged rings for connecting ducting and method of making
US20010008096A1 (en) * 1998-05-19 2001-07-19 Peter Sturrus Die apparatus for cutting end of bumper bar
US6432031B1 (en) * 1996-04-04 2002-08-13 Stowe Woodward Inc. Roll having a composite cover
CN103028909A (en) * 2012-11-29 2013-04-10 西安航空动力控制科技有限公司 Method for processing thin-wall semi-circular parts
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
CN108127341A (en) * 2017-12-11 2018-06-08 中国航空工业集团公司洛阳电光设备研究所 A kind of processing technology of precision support bushing class 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

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5983496A (en) * 1996-03-15 1999-11-16 J.A. Hermanson Circular and oval flanged rings for connecting ducting and method of making
US6432031B1 (en) * 1996-04-04 2002-08-13 Stowe Woodward Inc. Roll having a composite cover
US20010008096A1 (en) * 1998-05-19 2001-07-19 Peter Sturrus Die apparatus for cutting end of bumper bar
CN103028909A (en) * 2012-11-29 2013-04-10 西安航空动力控制科技有限公司 Method for processing thin-wall semi-circular parts
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
CN108127341A (en) * 2017-12-11 2018-06-08 中国航空工业集团公司洛阳电光设备研究所 A kind of processing technology of precision support bushing class 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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114211206A (en) * 2021-12-22 2022-03-22 北京星航机电装备有限公司 Method for processing multi-cavity casting cabin body of revolving body
CN114211206B (en) * 2021-12-22 2022-10-25 北京星航机电装备有限公司 Method for processing multi-cavity casting cabin body of revolving body
CN116140939A (en) * 2023-03-10 2023-05-23 北京星航机电装备有限公司 Processing method of thin-wall part with annular groove on end face

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