CN112846478A - Machining method for large thin-wall easily-deformable cabin shell - Google Patents
Machining method for large thin-wall easily-deformable cabin shell Download PDFInfo
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- 238000003754 machining Methods 0.000 title claims abstract description 109
- 238000000034 method Methods 0.000 title claims abstract description 41
- 238000012545 processing Methods 0.000 claims abstract description 58
- 230000032683 aging Effects 0.000 claims abstract description 26
- 210000001503 joint Anatomy 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims abstract description 11
- 238000005520 cutting process Methods 0.000 claims description 32
- 230000035882 stress Effects 0.000 claims description 18
- 238000003801 milling Methods 0.000 claims description 14
- 238000007514 turning Methods 0.000 claims description 9
- 238000003672 processing method Methods 0.000 claims description 8
- 238000001514 detection method Methods 0.000 claims description 4
- 238000001917 fluorescence detection Methods 0.000 claims description 3
- 238000003466 welding Methods 0.000 description 12
- 238000003756 stirring Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 238000003825 pressing Methods 0.000 description 4
- 238000012797 qualification Methods 0.000 description 4
- 238000005266 casting Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
- B23K20/122—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding using a non-consumable tool, e.g. friction stir welding
- B23K20/1245—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding using a non-consumable tool, e.g. friction stir welding characterised by the apparatus
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/26—Auxiliary equipment
Abstract
The invention discloses a method for processing a large thin-wall easily-deformable cabin shell, which comprises the following steps: removing large allowance of cabin shell parts; roughly machining the end face, the inner shape and the outer shape of the cabin shell part; roughly machining all openings on the outer circular surface of the cabin shell part; aging treatment; roughly machining an asymmetric opening notch on the end face of the cabin section shell part; semi-finishing the end surface, the inner shape and the outer shape of the cabin shell part; finishing all openings and asymmetric openness gaps on the outer circular surface of the cabin shell part: and (3) finishing the end surface, the inner shape and the outer shape of the cabin shell part: and machining a sealing groove, a butt joint hole and a mounting hole in the end face of the cabin section shell part. According to the invention, the asymmetric open notch machining is arranged after the aging treatment, the semi-finishing machining and the finishing allowance are reasonably distributed, and the notch is machined by adopting a radial layering and depth non-layering machining strategy, so that the problems of large deformation, uneven wall thickness and poor roundness of a part caused by an asymmetric open notch structure are solved.
Description
Technical Field
The application belongs to the technical field of machining processes of large-scale revolving bodies, and particularly relates to a machining method of a large-scale thin-wall cabin shell easy to deform, which is used for finally machining a structural member welded and formed through friction stir welding into a thin-wall revolving body with an asymmetric open notch on the end face and multiple openings on the outer circle.
Background
At present, the large-scale thin-wall revolving body parts are mainly manufactured by casting, integral forging or friction stir welding and other technologies.
The casting technology is adopted to manufacture the revolving body parts, and has the advantages of low qualification rate, large mechanical property dispersion, low reliability, weak overload bearing capacity and low precision.
The solid of revolution type parts are manufactured by adopting integral forging, the product weight is large, the material removal rate is high, the price is relatively expensive, and the method is not suitable for large solid of revolution type parts.
The friction stir welding technology is adopted to manufacture the integral revolving body type part, the skin and the end frame are in lap welding, the margin control before welding is relatively small, welding of a long welding line, a large section and different positions can be completed at one time, the operation process is convenient, mechanization and automation are realized, the equipment is simple, the energy consumption is low, and the efficiency is high.
Therefore, in the aerospace manufacturing industry, friction stir welding technology is increasingly adopted for manufacturing blanks for large-sized revolving parts, and the products are manufactured through machining. Part of large-scale revolving body parts are thin-wall asymmetric open gap easily-deformed revolving bodies. Thin wall means that the wall thickness of the revolution body is less than 5mm, and the part diameter is more than phi 1000mm and the height is more than 500mm in the field, so that the part is considered as a large part.
The thin-wall asymmetric open gap easily-deformed revolving body part has the following characteristics:
1. the part has large diameter, thin wall, high height and weak rigidity.
2. The end face of the part is provided with an asymmetric open notch, which greatly affects the stability of the whole structure of the product and is easy to deform.
3. The openings on the excircle surface of the part are more and are distributed asymmetrically, which has great influence on the rigidity of the product and is easy to deform.
4. The deformation of areas in processing is different, the difficulty in correcting deformation is high, and the wall thickness is easy to be out of tolerance;
5. the coaxiality of the positioning holes on the two end faces of the part is high, and the coaxiality of the part appearance and the reference circle of the positioning holes is high.
6. There are cutting heat and cutting stress during machining, resulting in machining distortion of the part.
Aiming at the characteristics of the thin-wall asymmetric open gap easily-deformed revolving body parts, a special process method needs to be designed, so that the quality problem in the manufacturing process of the parts is solved.
Disclosure of Invention
In order to solve the technical problems, the invention provides a method for machining a large thin-wall easily-deformable cabin shell, which solves the problems of large part deformation, poor part roundness, uneven wall thickness and difficult guarantee of coaxiality of butt holes in the existing machining method.
The technical scheme adopted for achieving the purpose of the invention is that the processing method of the large thin-wall easily-deformable cabin shell comprises the following steps:
removing large allowance of cabin shell parts;
roughly machining the end face, the inner shape and the outer shape of the cabin shell part;
roughly machining all openings on the outer circular surface of the cabin shell part;
aging treatment;
roughly machining an asymmetric open notch on the end face of a cabin section shell part, and machining by radial layering and depth non-layering;
semi-finishing the end surface, the inner shape and the outer shape of the cabin shell part;
finishing all openings and asymmetric openness gaps on the outer circular surface of the cabin shell part:
and (3) finishing the end surface, the inner shape and the outer shape of the cabin shell part:
and machining a sealing groove, a butt joint hole and a mounting hole in the end face of the cabin section shell part.
Further, the removing of large allowance of cabin shell parts specifically comprises: and coordinating and removing the large allowance of the inner and outer shapes of the cabin section shell part and the expansion frame according to the size of the cabin section shell part and the position of the expansion frame of the cabin section shell part, wherein the large allowance is at least half of the total machining allowance.
Further, the end face, the inside and the outside of the rough machining cabin shell part specifically include: the end face, the inner shape and the outer shape of the shell part of the coarse cabin section are machined, and the single-side residual cutting amount is 3-4 mm.
Further, all the openings on the outer circular surface of the rough cabin shell part specifically include: roughly milling all openings on the outer circular surface of the shell part of the cabin section, and machining the single side to obtain 1.5-2.5 mm of residual cutting amount.
Further, the rough machining of the asymmetric open notch in the end face of the cabin section shell part specifically includes:
roughly milling an asymmetric open notch on the end face of a shell part at the cabin section, and after machining, radially remaining cutting amount is 3-5 mm, and remaining cutting amount at two sides is 1-3 mm; radial layering and depth non-layering processing are adopted during processing, and a zigzag path is adopted as a processing path.
Further, the terminal surface and inside and outside shape of semi-finishing cabin section casing part specifically includes:
the two end faces of the shell part of the semi-finished car cabin section are machined, and the single-side residual cutting amount is 1.5-2 mm;
the internal and external shapes of the shell parts of the semi-finished car cabin section are machined, and the single-side residual cutting amount is 1-1.5 mm.
Further, all openings and asymmetric openness gaps on the outer circular surface of the fine machining cabin section shell part specifically include:
all openings on the outer circular surface of the cabin section shell part are finely milled and processed to the designed size;
and (4) milling an asymmetric opening notch on the end face of the shell part of the cabin section to a designed size.
Further, the end face, the inside and the outside of the finish machining cabin shell part specifically include:
finishing two end faces of the cabin section shell part, and after machining, carrying out unilateral residual cutting of 0.5-1 mm;
and finishing the inner and outer shapes of the shell parts of the cabin section to the designed size.
Further, the seal groove of processing cabin section casing part terminal surface specifically includes:
uniformly turning the front end surface and the rear end surface of the cabin shell part to remove allowance, and machining to a designed dimension height H;
and (4) processing the sealing grooves on the two end surfaces of the cabin section shell part to the designed size.
Further, the aging treatment specifically includes: eliminating stress in machining through artificial aging;
after the removing of the large allowance of the cabin section shell part and before the rough machining of the end face, the inner shape and the outer shape of the cabin section shell part, the machining method further comprises the following steps:
checking the internal quality: checking the internal quality of the cabin shell part through X-rays;
after the sealing groove, the butt joint hole and the mounting hole of the end face of the cabin shell part are machined, the machining method further comprises the following steps:
ultrasonic flaw detection and fluorescence detection: and detecting whether the surface of the part has cracks or not.
According to the technical scheme, the processing method of the large thin-wall easily-deformed cabin shell is used for processing the large thin-wall easily-deformed cabin shell with the asymmetric opening notch on the end face, and comprises the following steps: removing large allowance of cabin shell parts; roughly machining the end face, the inner shape and the outer shape of the cabin shell part; roughly machining all openings on the outer circular surface of the cabin shell part; aging treatment; roughly machining an asymmetric opening notch on the end face of the cabin section shell part; semi-finishing the end surface, the inner shape and the outer shape of the cabin shell part; finishing all openings and asymmetric openness gaps on the outer circular surface of the cabin shell part: and (3) finishing the end surface, the inner shape and the outer shape of the cabin shell part: and machining a sealing groove, a butt joint hole and a mounting hole in the end face of the cabin section shell part.
According to the processing method of the large thin-wall easily-deformable cabin shell, the processing of the asymmetric opening notch of the end face of the cabin shell part is arranged after the aging treatment, the processing stress is concentrated in a large amount after the openings are formed in the end face, the inner and outer shapes and the outer circular surface of the cabin shell part are roughly processed, the stress can be fully released through the subsequent aging treatment, the whole part is in a more stable and less-deformation state, the notch is processed after the aging treatment, the deformation is limited, and the product quality can be guaranteed through subsequent allowance distribution.
In the processing method of the large thin-wall easily-deformable cabin shell, when an asymmetric open notch on the end face of a cabin shell part is roughly processed, the notch is processed by adopting a processing strategy of radial layering and non-layering depth, and because the depth is not layered, the processing depth of each layering processing step in the depth direction of the cabin (axial direction of the cabin) is the same, namely the whole wall thickness is penetrated in each layering processing step, so that the structure of the part is damaged; due to the adoption of radial layering, the notch is gradually opened through each layering processing step, the damage of the part structure is slowly increased, the stress is released little by little in the processing process, and the deformation of the part can be effectively controlled.
Compared with the prior art, the processing method of the large thin-wall easily-deformable cabin shell comprises the steps of arranging the processing of the asymmetric open notch on the end surface after aging treatment, reasonably distributing semi-finishing and finishing allowance and processing the notch by adopting a radial layering and depth non-layering processing strategy, so that the problems of large deformation, uneven wall thickness and poor roundness of a part caused by the asymmetric open notch structure are solved; ensures various technical indexes of the product, has the qualification rate of over 99 percent, and is particularly suitable for machining the tapered cabin shell with the thin-wall asymmetric open gap and easy deformation.
Drawings
FIG. 1 is a front view in the direction of a large end face of a large thin-wall easily-deformable cabin shell;
FIG. 2 is a full sectional structural view of FIG. 1;
fig. 3 is a schematic view of the processing principle of radial layered processing of the zigzag path in the embodiment of the present invention.
Description of reference numerals: 10-cabin section housing parts; 1-large end face; 2-small end face; 3-asymmetric open gap; 4-opening.
Detailed Description
In order to make the present application more clearly understood by those skilled in the art to which the present application pertains, the following detailed description of the present application is made with reference to the accompanying drawings by way of specific embodiments.
In order to solve the technical problems of large part deformation, poor part roundness, uneven wall thickness and difficult guarantee of coaxiality of butt joint holes in the conventional machining method, the invention provides a machining method of a large thin-wall easily-deformed cabin shell, which is used for machining the large thin-wall easily-deformed cabin shell with an asymmetric opening notch on the end face, and the basic inventive concept is as follows:
a machining method for a large thin-wall easily-deformable cabin shell specifically comprises the following steps: removing large allowance of cabin shell parts; roughly machining the end face, the inner shape and the outer shape of the cabin shell part; roughly machining all openings on the outer circular surface of the cabin shell part; aging treatment; roughly machining an asymmetric open notch on the end face of a cabin section shell part, and machining by radial layering and depth non-layering; semi-finishing the end surface, the inner shape and the outer shape of the cabin shell part; finishing all openings and asymmetric openness gaps on the outer circular surface of the cabin shell part: and (3) finishing the end surface, the inner shape and the outer shape of the cabin shell part: and machining a sealing groove, a butt joint hole and a mounting hole in the end face of the cabin section shell part.
According to the processing method of the large thin-wall cabin shell with the easy deformation, provided by the invention, the processing of the asymmetric opening notch on the end surface is arranged after the aging treatment, the semi-finishing and finishing allowance are reasonably distributed, and the notch is processed by adopting a processing strategy of radial layering and depth non-layering of a zigzag path, so that the problems of large deformation, uneven wall thickness and poor roundness of a part caused by the asymmetric opening notch structure are solved; ensures various technical indexes of the product, has the qualification rate of over 99 percent, and is particularly suitable for machining the tapered cabin shell with the thin-wall asymmetric open gap and easy deformation.
The specific contents of the method for processing the large thin-wall easily-deformable cabin shell are described in detail below by taking the processing of the conical cabin shell of a certain aerospace craft as an example:
the blank of the conical cabin section shell to be processed is manufactured by a friction stir welding technology, the wall thickness of the part is 3.5mm, the diameter of the large end face is phi 1199, the diameter of the small end face is phi 1109, and the overall height H is 500 mm.
Referring to fig. 1 and 2, the conical cabin section shell 10 is designed as a conical rotary body, and two ends are respectively a large end surface 1 and a small end surface 2. An asymmetric opening notch 3 is formed in the large end face 1, and as shown in fig. 1, the asymmetric opening notch 3 greatly affects the overall structural stability of the product and is easily deformed. Referring to fig. 2, a plurality of openings 4 are distributed on the outer circumferential surface of the cabin shell 10, and each opening 4 is asymmetrically distributed, so that the rigidity of the product is greatly influenced and deformation is easily caused.
The machining method of the large thin-wall easily-deformable cabin shell provided by the embodiment of the invention is used for machining the thin-wall asymmetric open notch conical rotary body cabin shell formed by friction stir welding, and comprises the following steps:
(1) and removing large allowance of cabin shell parts.
Specifically, according to the size of the cabin section shell part and the position of the expansion frame of the cabin section shell part, large allowance of the inner and outer shapes of the cabin section shell part and the expansion frame are removed in a coordinated mode, and the inner quality is convenient to check. The large allowance processed in the step is at least half of the total machining allowance of the part. After the step is finished, the parts are detected, and the welding quality is detected.
(2) Checking the internal quality: and (4) checking the internal quality of the cabin section shell part through X-rays, and further detecting the welding quality.
(3) Roughly machining the end face, the inner shape and the outer shape of the cabin shell part, specifically, adopting turning machining in the step, and machining the single side to obtain the residual cutting amount of 3-4 mm.
(3.1) positioning by end faces, coordinating and aligning the symmetrical four-point runout of the part to be not more than 0.2, keeping the coaxiality phi of the outer circles of the end frames at the two ends within 0.5, machining the large end face and the small end face of the shell part at the coarse cabin section and the inner hole of the shell part at the cabin section, and then machining the single side to obtain the finished product with the residual cutting amount of 3mm and the height dimension of 506 mm.
(3.2) positioning by end faces, aligning the symmetric four-point jump of the inner hole within 0.1 and within 0.5 of the coaxiality phi of the outer circles of the end frames at the inner end and the two ends, processing the inner shape, and processing the single side residual cutting amount by 2mm and the wall thickness by 7.5 mm.
(4) And roughly machining all openings on the outer circular surface of the cabin shell part. Specifically, milling is adopted in the step, and the single-side residual cutting amount after the milling is 1.5-2.5 mm.
Adjusting and controlling the coaxiality of outer circles of the large end and the small end of the part within phi 0.3mm, roughly milling all openings on the outer circle surface of the cabin section shell part, and machining the single side to obtain the residual cutting amount of 2 mm.
After the inner appearance and the outer circle of the rough-machined part are opened, a large amount of machining stress is concentrated, and stress can be fully released through aging treatment subsequently, so that the whole part is in a more stable and small-deformation state.
(5) And (5) aging treatment. In this embodiment, this step is preferably artificially aged, by which the stress in the working is eliminated. The artificial aging can effectively homogenize the stress of the cabin shell and eliminate the casting residual stress, thereby reducing the subsequent processing deformation caused by the residual stress and the uneven stress. Of course, in other embodiments, other aging methods may be used to relieve the stresses during machining.
After the artificial aging is carried out, the three-dimensional scanning of the cabin shell part can be carried out, and the scanning result is compared with the state before the artificial aging, so that the deformation of the cabin shell part subjected to the heat treatment artificial aging is detected.
(6) And roughly machining an asymmetric open notch on the end face of the cabin shell part, and machining by radial layering and depth non-layering. Since the asymmetric opening notch 3 is specifically located on the large end face 1 of the cabin section shell part 10, as shown in fig. 1, the notch depth direction of the asymmetric opening notch is the radial direction of the cabin section shell part, and the notch is a through opening, i.e., the notch penetrates through the whole wall thickness, so that the part structure can be damaged.
The specific meaning of no depth stratification is that the machining depth of each layered machining step in the depth direction of the cabin section (axial direction of the cabin section) is the same, namely, the whole wall thickness is penetrated in each layered machining step, and the structure of the part is damaged. The specific meaning of radial layering is that along the depth direction of the notch (namely the radial direction of the cabin shell part), each layered processing step is deeper than the processing depth of the previous layered processing step, the notch is gradually opened through each layered processing step, and the structural damage of the part is slowly increased. Through radial layering and depth non-layering processing, the stress is released little by little in the processing process, and the deformation of the part can be effectively controlled.
Specifically, in the embodiment, the step adopts milling, and after the milling, the radial residual cutting amount is 3mm to 5mm, and the residual cutting amount on two sides is 1mm to 3 mm. The machining step is a key process, the coaxiality of outer circles of the large end and the small end of the part is adjusted and controlled within phi 0.3mm, an asymmetric open notch on the large end face of the cabin section shell part is roughly milled, a 'return' type path radial layering and depth non-layering machining strategy is adopted during machining of the notch, the radial residual cutting amount is 4mm after machining, and the residual cutting amount on two sides (circumferential direction) is 2mm
Based on the fact that radial layering and depth non-layering processing are adopted during processing in the step, a processing path adopts a zigzag path, and a processing path is shown in figure 3. Compare in arranging the asymmetric open nature breach of terminal surface before artifical ageing, after appearance and excircle opening in the rough machining part, the processing stress is concentrated in a large number, if carry out artifical ageing after opening the breach this moment, then because part overall structure nature is destroyed, at the in-process of release stress, the position that the part structure is weak is open nature breach department promptly and will produces very big deformation, the deflection is difficult to eliminate through follow-up surplus, easily leads to the product to scrap. The invention processes the notch after artificial aging, the deformation is limited, and the product quality can be ensured through subsequent allowance distribution.
(7) And (4) semi-finishing the end surface, the inner shape and the outer shape of the cabin shell part. Specifically, in this embodiment, turning is adopted in this step. This step comprises two sub-processes: semi-finishing the end face, wherein the single-side residual cutting amount after machining is 1.5-2 mm; semi-finishing the inner shape, and cutting the single side of the workpiece by 1-1.5 mm.
(7.1) coordinating and aligning the parts, wherein the symmetrical four-point runout is not more than 0.2, the large end surface, the small end surface and the inner hole of the shell part of the semi-finished car cabin section have the unilateral residual cutting amount of 1.5mm, the height dimension of 503mm, the planeness of the two end surfaces of 0.1mm and the parallelism of 0.2mm after processing.
And (7.2) centering the inner hole to jump within 0.05 by taking the end face as a reference, and carrying out semi-finish turning on the inner and outer shapes of the cabin section shell part, wherein the single-side residual cutting amount is 1mm after the processing, and the wall thickness is 5.5 mm.
(8) And finishing all openings and asymmetric opening gaps on the outer circular surface of the cabin shell part. Specifically, in this embodiment, milling is adopted in this step. This step comprises two sub-processes: finely processing an opening on the outer circular surface; asymmetric open notch finishing.
(8.1) pressing an inner hole step by taking the end face as a reference, aligning the coaxiality of outer circles of the upper end and the lower end within phi 0.1 and the end face run-out within 0.1, finely milling all openings on the outer circle face of the cabin shell part, and processing to the design size;
(8.2) adjusting the surface, aligning the coaxiality of the outer circles of the upper end and the lower end within phi 0.1 and the end face run-out within 0.1, finely milling an asymmetric open notch of the end face of the cabin shell part, and processing to the design size.
(9) And (5) finishing the end surface, the inner shape and the outer shape of the cabin shell part. Specifically, in this embodiment, turning is adopted in this step. This step comprises two sub-processes: finish machining the end face, wherein the single-side residual cutting amount after machining is 0.5-1 mm; and (5) finishing the inner shape and the outer shape.
(9.1) coordinating and aligning the symmetrical four-point runout of the part to be not more than 0.1, within the coaxiality phi of the outer circles of the end frames at the two ends, finely turning the two end faces and the inner hole of the shell part at the cabin section, wherein the single-side residual cutting amount is 0.5mm after machining, and the height dimension is 501 +/-0.2 mm.
And (9.2) aligning the inner hole jump within 0.05 by taking the end face as a reference, and finely turning the inner and outer shapes of the cabin shell part to the designed size. The processing is a key process, a mode of repeatedly feeding for many times is adopted during the inner and outer shapes, the pressing plate is loosened during the processing, and the pressing plate is clamped again after being placed for half an hour to remove stress. The feed amount of each time is not more than 0.2mm/r, the cutting depth is not more than 0.2mm, and the rotating speed is 80-90 r/min. The coaxiality of the upper excircle and the lower excircle is 0.05, the planeness is 0.1, the roundness is 0.05, and the wall thickness is 3.5 +/-0.1 mm.
(10) And machining a sealing groove on the end face of the cabin section shell part. Specifically, this step in this embodiment includes two sub-processes:
(10.1) positioning by using the end face, aligning the roundness of the excircle of the part to be 0.1, aligning the coaxiality phi of the excircles at two ends to be 0.1, leveling the end face of the part to be 0.1, uniformly turning the front end face and the rear end face of the cabin section shell part to remove the allowance, and processing to the designed height dimension of 500 +/-0.2 mm.
(10.2) positioning by using the end face, aligning the roundness of the excircle of the part to be 0.1, aligning the coaxiality phi of the excircles at two ends to be 0.1, leveling the end face of the part to be 0.1, processing the sealing grooves on the large end face and the small end face of the cabin section shell part, and processing to the designed size.
(11) And machining the butt joint hole and the mounting hole of the end face of the cabin shell part.
(11.1) pressing an inner hole step by taking the small end face as a reference, finding the coaxiality phi of an upper outer circle and a lower outer circle within 0.05, aligning the roundness of an outer circle of the large end within 0.05, determining a machining coordinate by taking an opening on the outer circle as a reference, and machining the butt joint hole on the large end face to a designed size so as to ensure the subsequent assembly requirement.
And (11.2) positioning by using the pin hole at the large end, and processing the positioning hole on the small end surface to the designed size to ensure the requirement of the coaxiality precision of the butt joint holes of the large end surface and the small end surface.
(12) Ultrasonic flaw detection and fluorescence detection: and detecting whether the surface of the part has cracks or not.
Finally, ultrasonic flaw detection and fluorescent inspection are carried out on the parts, and whether the verson, shrinkage cavity and cracks exist or not is confirmed; and deciding whether to carry out a repairing measure according to the defects of the parts.
Through the embodiment, the invention has the following beneficial effects or advantages:
according to the processing method of the large thin-wall easily-deformable cabin shell, the processing of the asymmetric opening notch on the end surface is arranged after the artificial aging, the semi-finishing and finishing allowance are reasonably distributed, and the notch is processed by adopting a processing strategy of radial layering and depth non-layering of a 'return' type path, so that the problems of large deformation, uneven wall thickness and poor roundness of a part caused by the asymmetric opening notch structure are solved. Ensures various technical indexes of the product, and improves the qualification rate of the product from 50 percent to over 99 percent. The method is verified by small-batch production, effectively controls the quality of the product, and is particularly suitable for machining the tapered cabin shell with the thin-wall asymmetric opening gap and easy deformation.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. A method for processing a large thin-wall easily-deformable cabin shell is characterized by comprising the following steps: the end face of the cabin shell is provided with an asymmetric open notch, and the processing method comprises the following steps:
removing large allowance of cabin shell parts;
roughly machining the end face, the inner shape and the outer shape of the cabin shell part;
roughly machining all openings on the outer circular surface of the cabin shell part;
aging treatment;
roughly machining an asymmetric open notch on the end face of a cabin section shell part, and machining by radial layering and depth non-layering;
semi-finishing the end surface, the inner shape and the outer shape of the cabin shell part;
finishing all openings and asymmetric openness gaps on the outer circular surface of the cabin shell part:
and (3) finishing the end surface, the inner shape and the outer shape of the cabin shell part:
and machining a sealing groove, a butt joint hole and a mounting hole in the end face of the cabin section shell part.
2. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: the removing of large allowance of cabin section shell parts specifically comprises the following steps: and coordinating and removing the large allowance of the inner and outer shapes of the cabin section shell part and the expansion frame according to the size of the cabin section shell part and the position of the expansion frame of the cabin section shell part, wherein the large allowance is at least half of the total machining allowance.
3. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: the terminal surface and inside and outside appearance of rough machining cabin section casing part specifically includes: the end face, the inner shape and the outer shape of the shell part of the coarse cabin section are machined, and the single-side residual cutting amount is 3-4 mm.
4. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: all openings on the outer circular surface of the rough machining cabin section shell part specifically comprise: roughly milling all openings on the outer circular surface of the shell part of the cabin section, and machining the single side to obtain 1.5-2.5 mm of residual cutting amount.
5. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: the asymmetric open gap of the rough machining cabin section shell part end face specifically comprises:
roughly milling an asymmetric open notch on the end face of a shell part at the cabin section, and after machining, radially remaining cutting amount is 3-5 mm, and remaining cutting amount at two sides is 1-3 mm; radial layering and depth non-layering processing are adopted during processing, and a zigzag path is adopted as a processing path.
6. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: the terminal surface and inside and outside appearance of semi-finishing cabin section casing part specifically include:
the two end faces of the shell part of the semi-finished car cabin section are machined, and the single-side residual cutting amount is 1.5-2 mm;
the internal and external shapes of the shell parts of the semi-finished car cabin section are machined, and the single-side residual cutting amount is 1-1.5 mm.
7. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: all openings and asymmetric open gaps on the outer circular surface of the fine machining cabin section shell part specifically comprise:
all openings on the outer circular surface of the cabin section shell part are finely milled and processed to the designed size;
and (4) milling an asymmetric opening notch on the end face of the shell part of the cabin section to a designed size.
8. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: the terminal surface and inside and outside appearance of finish machining cabin section casing part specifically includes:
finishing two end faces of the cabin section shell part, and after machining, carrying out unilateral residual cutting of 0.5-1 mm;
and finishing the inner and outer shapes of the shell parts of the cabin section to the designed size.
9. The machining method for the large thin-wall easily-deformable cabin shell according to claim 1, characterized by comprising the following steps of: the seal groove of processing cabin section casing part terminal surface specifically includes:
uniformly turning the front end surface and the rear end surface of the cabin shell part to remove allowance, and machining to a designed dimension height H;
and (4) processing the sealing grooves on the two end surfaces of the cabin section shell part to the designed size.
10. The machining method for the large thin-wall easily-deformable cabin shell according to any one of claims 1 to 9, characterized by comprising the following steps of: the aging treatment specifically comprises the following steps: eliminating stress in machining through artificial aging;
after the removing of the large allowance of the cabin section shell part and before the rough machining of the end face, the inner shape and the outer shape of the cabin section shell part, the machining method further comprises the following steps:
checking the internal quality: checking the internal quality of the cabin shell part through X-rays;
after the sealing groove, the butt joint hole and the mounting hole of the end face of the cabin shell part are machined, the machining method further comprises the following steps:
ultrasonic flaw detection and fluorescence detection: and detecting whether the surface of the part has cracks or not.
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Application publication date: 20210528 |