CN114888526A - Method for processing inner surface of box bottom of integral central imperforate rocket tank - Google Patents
Method for processing inner surface of box bottom of integral central imperforate rocket tank Download PDFInfo
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- CN114888526A CN114888526A CN202210352691.6A CN202210352691A CN114888526A CN 114888526 A CN114888526 A CN 114888526A CN 202210352691 A CN202210352691 A CN 202210352691A CN 114888526 A CN114888526 A CN 114888526A
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- 238000000034 method Methods 0.000 title claims abstract description 49
- 238000003754 machining Methods 0.000 claims abstract description 67
- 238000000137 annealing Methods 0.000 claims abstract description 22
- 238000003466 welding Methods 0.000 claims abstract description 11
- 238000005520 cutting process Methods 0.000 claims description 14
- 238000007493 shaping process Methods 0.000 claims description 3
- 238000003672 processing method Methods 0.000 claims 1
- 239000007769 metal material Substances 0.000 abstract description 2
- 238000009987 spinning Methods 0.000 description 11
- 230000035882 stress Effects 0.000 description 8
- 239000000243 solution Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 241000219112 Cucumis Species 0.000 description 2
- 235000015510 Cucumis melo subsp melo Nutrition 0.000 description 2
- FJJCIZWZNKZHII-UHFFFAOYSA-N [4,6-bis(cyanoamino)-1,3,5-triazin-2-yl]cyanamide Chemical compound N#CNC1=NC(NC#N)=NC(NC#N)=N1 FJJCIZWZNKZHII-UHFFFAOYSA-N 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000003801 milling Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007723 die pressing method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/20—Recycling
Abstract
The invention provides a method for processing the inner surface of the bottom of an integral central imperforate rocket tank, which relates to the technical field of metal material forming, and comprises the steps of turning a blind hole at the center of the outer surface of the bottom of a workpiece by a vertical lathe, and matching the blind hole with an inner shape machine; welding a plurality of auxiliary process blocks on the outer surface of the opening of the workpiece; roughly machining the inner profile of the workpiece; annealing and stress removing; and (5) finishing the inner shape surface of the workpiece. The invention can realize the fixation of the workpiece and prevent the eccentric and loose phenomena in the processes of clamping and processing.
Description
Technical Field
The invention relates to the technical field of metal material forming, in particular to a method for processing the inner shape surface of the bottom of an integral central imperforate rocket tank.
Background
The storage tank is a part for storing fuel in the rocket, accounts for more than 50% of the weight and space of the rocket body structure, and is formed by welding a tank bottom, a cylinder section, a short shell and other components, wherein the tank bottom is a key structural member in the storage tank and is also a structural member with high development difficulty in the storage tank, and the diameter of the tank bottom is mainly 2.25m, 3.35m and 5m at present. The traditional box bottom is formed by welding a plurality of melon petals and a top cover in a splicing manner, and along with the continuous development of equipment and technology, in order to improve the reliability of the box bottom and reduce the number of main welding lines, the forming technology of the box bottom is gradually developed from the melon petals in the splicing manner to the integral spinning forming manner.
In order to ensure the shape requirement of the product, the thickness of the box bottom after spinning is about 25-40mm, the thickness needs to be reduced to 2-4mm through machining, and the thickness tolerance needs to be ensured within 0.5mm (even stricter). Currently, the mechanical processing and thinning are generally carried out by two modes: one method is that the thickness is turned to the designed thickness by a vertical lathe, but the bottom of the spinning box is a weak-rigidity large-diameter thin-wall structure, the whole bottom is deformed in the mechanical processing and thinning process, the thickness uniformity is difficult to control, and even if the rigidity is improved by a large-scale complex tool, the processing precision is still difficult to ensure; the other method is numerical control machining through five-axis mirror milling, and although the five-axis machining process is high in precision, the five-axis milling is high in machining cost and low in efficiency, and the requirements of commercial aerospace on cost and efficiency cannot be met.
In consideration of cost and efficiency, turning is generally performed by a vertical lathe in the prior art. Before turning, a workpiece generally needs to be subjected to die pressing, spinning, annealing, solid solution and aging treatment, uneven temperature fields and uneven elastoplastic deformation can be generated in the processes, the workpiece generates larger residual stress, particularly the workpiece is turned from the thickness of nearly 40mm to the thickness of 2-4mm, the processing amount is large, the deformation is larger along with stress release and redistribution in the processing process, particularly in the later processing period, along with the reduction of the rigidity of the workpiece, the deformation of the workpiece in the turning process is more obvious, and the shape and the thickness are difficult to guarantee. In addition, since the workpiece has a large diameter-thickness ratio, the workpiece is slightly eccentric at the initial stage of chucking, which results in a large variation in the dimension after the machining. During the turning process, the centrifugal force is large, and eccentricity is generated, and the eccentricity can cause that the precision can not reach the requirement.
The bottom of the spinning box is provided with a through hole at present under the condition of the current spinning technology, and when the inner shape surface is machined, the central through hole is beneficial to positioning the bottom, so that the eccentricity of clamping and turning processes is avoided. But for the spinning box bottom without the central through hole at the bottom, the difficulty of positioning and ensuring non-eccentricity before vertical lathe machining is higher, and no related tool design experience can be used for reference.
Disclosure of Invention
In view of the above, the invention aims to provide a method for processing the inner shape of the bottom of an integral central imperforate rocket tank, so as to solve the technical problems of great difficulty in positioning and ensuring non-eccentricity before vertical lathe processing during processing the inner shape of the bottom of a spinning tank without a central through hole at the bottom in the prior art.
In order to achieve the purpose, the invention provides a method for processing the inner surface of the bottom of an integral central imperforate rocket tank, which comprises the following steps:
s1: turning a blind hole in the center of the outer surface of the bottom of the workpiece by using a vertical lathe, and matching the blind hole with the inner shape machining assembly;
s2: welding a plurality of auxiliary process blocks on the outer surface of the opening of the workpiece;
s3: roughly machining the inner shape surface of the workpiece;
s4: annealing and stress removing;
s5: and finishing the inner shape surface of the workpiece.
According to an alternative embodiment, between step S2 and step S3 further comprises: clamping the workpiece on the inner shape machining device through a lifting appliance, and matching a central positioning support with a central blind hole in the outer surface of the workpiece to realize the positioning of the lower part of the workpiece; the upper part of the workpiece is positioned and fixed by matching the jacking and aligning component with the auxiliary process block of the workpiece; and the workpiece is ensured to be rigidly fixed with the machining tool of the inner shaping machine through adjustable support.
According to an optional implementation mode, the central positioning support comprises a positioning frame and a positioning pin, the positioning frame is arranged on the outer surface of the bottom of the workpiece, and the positioning pin is inserted into a blind hole in the center of the outer surface of the workpiece through the positioning frame.
According to an optional embodiment, the adjustable support comprises an adjustable support A and an adjustable support B, and the adjustable support A and the adjustable support B are used for improving the matching rigidity of the workpiece and the inner forming machine machining tool.
According to an alternative embodiment, the inner profile finishing comprises repeating the steps between steps S2 and S3, including continuing to machine the workpiece inner profile on the machine tool, turning the inner profile to a finished size; when the machine is added to the last 2-3 cutters, the cutting feed amount and the cutting feed amount are reduced, and the cutting feed amount is controlled within 0.5 mm.
According to an alternative embodiment, the rough machining of the inner profile comprises machining the inner profile of the workpiece on a machine tool, feeding the workpiece with a feed rate of not more than 1.5mm per pass, rotating at a speed of not more than 30r/min, feeding at a speed of not more than 0.3mm/r, turning to the inner profile about 2-3mm from the theoretical profile, stopping the machining and separating the workpiece from the inner profile machining device.
According to an alternative embodiment, the annealing destressing includes placing the rough workpiece in an annealing furnace for a destressing annealing process.
According to an alternative embodiment, the blind holes have a diameter of 30-70mm and a depth of 10 mm.
According to an alternative embodiment, the auxiliary process blocks comprise 6-12 and are evenly distributed.
According to an alternative embodiment, step S5 may be followed by separating the workpiece from the inner shape machining tool and waiting for the next outer shape machining.
The invention provides a method for processing the inner shape surface of the bottom of an integrated central imperforate rocket tank, which has the following technical effects:
the machining method comprises the process routes of clamping by adopting a blind hole opening tool, clamping by an inner shape surface tool, rough machining of the inner shape surface, stress relief annealing and finish machining of the inner shape surface, and can realize workpiece fixation and prevent the phenomena of eccentricity and looseness in the clamping and machining processes.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of the actual mounting structure of a workpiece and a forming tool according to an embodiment of the present invention;
fig. 2 is a diagrammatic view of the workpiece and the inner forming machine of fig. 1.
Wherein, fig. 1-2:
1. a workpiece; 11. an auxiliary process block; 111. welding lugs; 12. blind holes; 2. a central positioning support; 21. a positioning frame; 22. positioning pins; 3. a hold-down mechanism; 31. a jacking and aligning assembly; 4. a jacking structure; 41. an adjustable support A; 42. an adjustable support B; 5. and (5) machining a tool by an inner shaping machine.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.
The invention provides a method for processing the inner surface of an integral central imperforate workpiece for a rocket, which aims to ensure the processing precision of the inner surface of the central imperforate workpiece and realize the precise control of the inner surface and the thickness, wherein the workpiece specifically refers to the bottom of a spinning box.
The invention takes a 25-40mm thick 2219-T6 spinning bottom of a box as a processing blank, and is realized by the following method:
(1) turning a blind hole 12 with the diameter of 30-70mm and the depth of 10mm at the center of the outer surface of the bottom of the workpiece 1 by using a vertical lathe, and assembling the blind hole with the inner shape machining device 5 for carrying out bottom center positioning;
(2) 6-12 auxiliary process blocks 11 are welded on the outer surface of the opening of the workpiece 1 and are uniformly distributed, and the auxiliary process blocks 11 are used for compressing and fixing the workpiece 1;
(3) the method comprises the following steps of clamping a workpiece 1 on an inner shape machining device 5 through a lifting appliance, as shown in fig. 1 and 2, realizing the positioning of the lower part of the workpiece 1 by matching a central positioning support 2 with a central blind hole 12 in the outer surface of the workpiece 1, realizing the positioning and fixing of the upper part of the workpiece 1 by matching a jacking and adjusting assembly 31 with an auxiliary process block 11 of the workpiece 1, and ensuring the rigid fixation of the workpiece 1 and the inner shape machining device 5 through adjustable support;
the central positioning support 2 comprises a positioning frame 21 and a positioning pin 22, the positioning frame 21 is arranged on the outer surface of the bottom of the workpiece 1, and the positioning pin 22 is inserted into the blind hole 12 in the center of the outer surface of the workpiece 1 through the positioning frame 21.
And the adjustable supports comprise an adjustable support A41 and an adjustable support B42, and the adjustable supports A41 and the adjustable supports B42 are used for improving the matching rigidity of the workpiece 1 and the inner shape machining device 5.
(4) Machining the inner surface of the workpiece 1 on a machine tool, wherein the feed amount of each pass is not more than 1.5mm, the rotating speed is not more than 30r/min, the feed speed is not more than 0.3mm/r, the distance between the machined inner surface and the theoretical surface is about 2-3mm, the machining is stopped, and the workpiece 1 and the inner machine are machined and separated;
(5) placing the roughly processed workpiece 1 into an annealing furnace for stress relief annealing treatment, wherein the annealing temperature is 100-140 ℃, the annealing time is 4-8 h, and within the temperature and time range, the processing precision of the workpiece is improved, but the strength and the elongation rate are not influenced;
(6) repeating the step (3) to clamp the inner shape machining device 5 and the workpiece 1;
(7) continuously machining the inner shape surface of the workpiece 1 on the machine tool, and turning the inner shape surface to the size of a finished product; when the machine is added to the last 2-3 cutters, in order to improve the processing precision, reduce the cutting deformation and reduce the cutting feed and the cutting feed, the cutting feed is controlled within 0.5 mm;
(8) the workpiece 1 is separated from the inside shape machining device 5 and waits for the next outside shape machining.
Further, in the step (3), the inside shape machining device 5 is installed and clamped schematically as shown in fig. 1, and mainly comprises: a jacking alignment assembly 31, an adjustable support A41, an adjustable support B42 and a center positioning support 2.
The jacking and aligning component 31 is combined with the central positioning support 2 for use and is matched with the blind hole 12 at the bottom of the workpiece 1 to position and fix the integral central shaft of the workpiece 1; the adjustable support A41 and the adjustable support B42 are used in a matched mode and used for improving the matched rigidity of the workpiece 1 and the inner forming machine machining device 5, reducing deformation of the workpiece 1 caused by centrifugal force and cutting force in the machining process and improving machining precision and quality.
Because the diameter-thickness ratio of the workpiece 1 is large, the workpiece is slightly eccentric in the initial clamping stage, which causes large deviation of the processed size, and in addition, the centrifugal force is large in the turning process, which also causes eccentricity, so that a clamping mode needs to be designed, the workpiece 1 can be fixed, and the eccentricity and looseness in the clamping and processing processes are prevented.
According to the invention, the size of the blind hole 12 is reasonably designed, so that the eccentricity of the workpiece 1 is avoided, and the precision of subsequent processing is effectively ensured; the rigidity of the weak-rigidity revolving body structure with the large diameter-thickness ratio is improved by reasonably designing the inner shape machining assembly 5; by skillfully designing the positioning frame 21 and the positioning pin 22 of the inner shape machining device 5 and matching with the blind hole 12 of the workpiece 1, the center positioning of the bottom of the spinning box without a central hole is realized, and the workpiece 1 is prevented from being eccentric in the process of machining the inner shape surface; by the process route design of firstly roughly machining the inner surface, stress relief annealing and finish machining the inner surface, the adverse effect on the precision caused by the release of the internal stress of the material in the machining process is obviously reduced; in the aspect of turning process design, the feed amount is controlled within 0.5mm by reducing the feed amount in the later processing stage, so that the cutting force in the cutting process is reduced, and the deformation is reduced.
The technical solutions of the present invention are described in detail below with reference to specific examples, which are not intended to limit the present invention, but rather to specifically describe certain aspects, features and embodiments of the present invention.
Example 1:
as shown in figure 1, a 2219-T6 aluminum alloy seal head with the thickness of 35mm is used as a blank, the diameter of the opening part of a target part is 3350mm, the wall thickness is 3.5mm, the wall thickness tolerance is (0, +0.5) mm, and the major half axis/minor half axis of an inner ellipsoid is 1.4.
(a) Turning a blind hole 12 with the thickness of 50mm and the depth of 10mm at the center of the bottom of the workpiece 1 by using a vertical lathe, and matching with the inner shape machining tool 5 to perform bottom center positioning;
(b) evenly welding 8 welding lugs 111 at positions 80mm away from the mouth, wherein the welding lugs 111 are made of 2219 aluminum alloy, and the workpiece 1 is pressed by pressing the welding lugs 111;
(c) the workpiece 1 is clamped on the inner shape machining device 5 through a lifting appliance, the positioning frame 21 and the positioning pin 22 are matched with the blind hole 12 of the workpiece 1, and the pressing mechanism 3 and the jacking structure 4 shown in the figure 1 are used for fixing the workpiece 1 and ensuring the rigidity of the workpiece 1;
(d) turning an inner profile on a vertical lathe, wherein the feed amount of each pass is 1.5mm, the rotating speed is 28r/min, the feed speed is 0.3mm/r, and the distance from the inner profile to the theoretical profile is 1.5 mm;
(e) putting the workpiece 1 into an annealing furnace for annealing at the annealing temperature of 140 ℃ for 4 h;
(f) repeating the sequence number (c) to carry out inner shape machining and clamping of the workpiece 1 and the workpiece 5;
(g) continuously turning the inner shape surface on the vertical lathe, turning the inner shape surface to the size of a finished product, and when turning to the last 2-3 cutters, in order to reduce cutting stress and improve precision, the cutter feeding amount is 0.3 mm;
(h) the workpiece 1 is separated from the inside shape machining device 5 and waits for the next outside shape machining.
In the embodiment, the annealing process is added, and compared with the drawing which requires the machining precision to be (0, +0.5) mm, the machining precision of the embodiment is (0, +0.32) mm, and the machining precision which is not subjected to the annealing process is (0, +0.47) mm, so that after the annealing process is added, the machining precision error is obviously reduced, namely the machining precision of the workpiece is improved to a certain extent.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. A processing method for the inner surface of the bottom of an integral central imperforate rocket tank is characterized by comprising the following steps:
s1: turning a blind hole in the center of the outer surface of the bottom of the workpiece by using a vertical lathe, and matching with the inner shape machining assembly;
s2: welding a plurality of auxiliary process blocks on the outer surface of the opening of the workpiece;
s3: roughly processing the inner surface;
s4: annealing and stress removing;
s5: and (5) finishing the inner shape of the dough.
2. The method for forming the inner surface of the tank bottom of the integral central aporate rocket tank as recited in claim 1, wherein the step S2 and the step S3 further comprise: clamping the workpiece on the inner profile machining device through a lifting appliance, and matching the workpiece with a central blind hole in the outer surface of the workpiece through a central positioning support to realize the positioning of the lower part of the workpiece; the upper part of the workpiece is positioned and fixed by matching the jacking and aligning component with the auxiliary process block of the workpiece; and the workpiece is ensured to be rigidly fixed with the machining tool of the inner shaping machine through adjustable support.
3. The method of machining the inner bottom surface of an integral central imperforate rocket tank of claim 2 wherein said centering support comprises a locating bracket and a locating pin, said locating bracket being disposed on the outer bottom surface of said workpiece, said locating pin being inserted through said locating bracket into a blind hole in the center of said outer bottom surface of said workpiece.
4. The method for machining the inner shape of the bottom of the integral central imperforate rocket tank as claimed in claim 2, wherein the adjustable support comprises an adjustable support A and an adjustable support B, and the adjustable support A and the adjustable support B are used for improving the fitting rigidity of the workpiece and the inner shape machining tool.
5. The method of profiling a case bottom of an integral central aporate rocket tank as recited in claim 2 wherein said profiling comprises repeating steps between said steps S2 and S3, including continuing to machine a workpiece inner profile on a machine tool, turning the inner profile to finished dimensions; when the machine is added to the last 2-3 cutters, the cutting feed amount and the cutting feed amount are reduced, and the cutting feed amount is controlled within 0.5 mm.
6. The method for machining the inner profile of the bottom of the integral central imperforate rocket tank as recited in claim 1, wherein said rough machining of the inner profile comprises machining the inner profile of the workpiece on a machine tool, wherein the feed rate per pass is not greater than 1.5mm, the rotation speed is not greater than 30r/min, the feed speed is not greater than 0.3mm/r, the distance from the theoretical profile when the workpiece is turned to the inner profile is about 2-3mm, the machining is stopped and the workpiece is separated from the inner profile machining device.
7. The method for processing the internal surface of the tank bottom of the integral central imperforate rocket tank as recited in claim 1, wherein said annealing for destressing comprises annealing the rough-processed workpiece in an annealing furnace for destressing.
8. The method for processing the inner surface of the bottom of the integral central imperforate rocket tank as recited in claim 1, wherein said blind holes have a diameter of 30-70mm and a depth of 10 mm.
9. The method for processing the inner surface of the bottom of the integral central imperforate rocket tank as claimed in claim 1, wherein said auxiliary blocks comprise 6-12 blocks and are uniformly distributed.
10. The method for machining the inner shape of the bottom of the tank of the integral central aporate rocket tank as recited in any one of claims 1 to 9, wherein the step S5 is followed by separating the workpiece from the inner shape machining device and waiting for the next outer shape machining.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210352691.6A CN114888526A (en) | 2022-04-06 | 2022-04-06 | Method for processing inner surface of box bottom of integral central imperforate rocket tank |
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| CN202210352691.6A CN114888526A (en) | 2022-04-06 | 2022-04-06 | Method for processing inner surface of box bottom of integral central imperforate rocket tank |
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| 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 |
| CN112405044A (en) * | 2020-11-19 | 2021-02-26 | 首都航天机械有限公司 | Additional device of integral spinning type semi-spherical shell inner surface molding machine |
| CN212762337U (en) * | 2020-08-07 | 2021-03-23 | 贵州航天朝阳科技有限责任公司 | Clamp for turning large-sized thin-wall storage box shell |
| CN113319300A (en) * | 2021-04-26 | 2021-08-31 | 浙江蓝箭航天空间科技有限公司 | Method for forming integral circular ring at bottom of rocket tank |
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2022
- 2022-04-06 CN CN202210352691.6A patent/CN114888526A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202825251U (en) * | 2012-06-07 | 2013-03-27 | 安徽德锐仕机床制造有限公司 | Locating pin with air discharge duct |
| CN104526284A (en) * | 2014-12-19 | 2015-04-22 | 常熟市常轴轴承有限公司 | Thin-walled bearing ring lathing process |
| CN107984175A (en) * | 2017-12-08 | 2018-05-04 | 中国航天科技集团公司长征机械厂 | A kind of processing method of ultra-thin titanium alloy spherical parts |
| 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 |
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Application publication date: 20220812 |