CN114523263A - Method for processing internal structure of composite tube shell - Google Patents
Method for processing internal structure of composite tube shell Download PDFInfo
- Publication number
- CN114523263A CN114523263A CN202210156659.0A CN202210156659A CN114523263A CN 114523263 A CN114523263 A CN 114523263A CN 202210156659 A CN202210156659 A CN 202210156659A CN 114523263 A CN114523263 A CN 114523263A
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- composite
- shell
- bottom hole
- broaching
- wall
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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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Milling, Broaching, Filing, Reaming, And Others (AREA)
Abstract
The invention discloses a method for processing an internal structure of a composite pipe shell, which comprises the following steps: using a mould with the shape of a composite pipe shell to bear and fix the composite pipe shell; drilling a bottom hole in the composite pipe shell; reaming the bottom hole; and broaching the inner wall of the composite tube shell by using a broaching tool with at least one group of cutting edges through the reamed bottom hole to form at least one flat groove on the inner wall, wherein the bottom of the flat groove is raised in the radial outward direction of the composite tube shell relative to the other parts of the inner wall.
Description
Technical Field
The invention relates to the field of microwave electric vacuum devices, in particular to a method for processing an internal structure of a composite tube shell.
Background
The space traveling wave tube is used as a vacuum microwave core device for space navigation, can play a role in microwave power amplification, and has the advantages of high power and the like. In the space traveling wave tube, the composite tube shell is taken as a core component of the slow wave component, which is affiliated to the space traveling wave tube, and can play a role in supporting and radiating. The size consistency of the internal structure of the composite tube shell influences the heat dissipation performance of the space traveling wave tube. The size of the internal structure of the composite tube shell is easy to be inconsistent by the common process for processing the internal structure of the composite tube shell, the processed internal structure and the composite tube shell have different circle centers, and an oxidation layer is arranged on the surface of the internal structure, so that the air bleeding rate of the internal structure is higher, and the stability and the reliability of the space traveling wave tube are reduced.
Disclosure of Invention
In view of the above problems, the present invention provides a method for processing an internal structure of a composite tube envelope, which can solve the problems of inconsistent size, high surface outgassing rate, and the like of the internal structure of the processed composite tube envelope.
To achieve the above object, the present invention provides a method for processing an internal structure of a composite envelope, comprising: using a mould with the shape of a composite pipe shell to bear and fix the composite pipe shell; drilling a bottom hole in the composite pipe shell; reaming the bottom hole; and broaching the inner wall of the composite tube shell by using a broaching tool with at least one group of cutting edges through the reamed bottom hole to form at least one flat groove on the inner wall, wherein the bottom of the flat groove is raised relative to other parts of the inner wall in the radial outward direction of the composite tube shell.
According to an embodiment of the present invention, the broaching the inner wall of the composite envelope using a broach having at least one set of cutting edges through the reamed pilot hole includes: and the broaching tool matched with the inner diameter of the bottom hole is adopted, the broaching tool is driven by the broaching machine to do main motion along the direction vertical to the plane of the bottom hole, and the cutting edge on the broaching tool does feed motion to finish broaching processing of the inner wall of the composite tube shell.
According to an embodiment of the present invention, the method further includes, after the broaching, the steps of: and putting the composite tube shell with at least one flat groove into a mixed solution of diamond yarn powder and acetone for ultrasonic cleaning to remove burrs.
An embodiment according to the invention is characterized by further comprising, after the ultrasonic cleaning: and putting the composite tube shell subjected to deburring into an acetone solution for ultrasonic deoiling cleaning to obtain the machined composite tube shell.
An embodiment of the method according to the invention is characterized in that after placing the composite cartridge in the mould, the composite cartridge is pressed and fixed by means of screws.
According to an embodiment of the present invention, the method further includes: broaching the inner wall of the composite tube shell by using a broaching tool with three groups of cutting edges through the reamed bottom hole so as to form three flat grooves on the inner wall, wherein the bottoms of the flat grooves are raised relative to other parts of the inner wall in the radial outward direction of the composite tube shell.
According to an embodiment of the present invention, the drilling of the bottom hole and the reaming are performed based on an outer diameter of the composite pipe case.
According to an embodiment of the present invention, the broaching process is performed with reference to the bottom hole.
According to the method for processing the internal structure of the composite tube shell of the space traveling-wave tube, provided by the embodiment of the invention, the bottom hole is processed in a drilling and reaming processing mode, and then the forming broach with the cutting edge is adopted for broaching, so that the processing of the internal structure of the composite tube shell is realized; the size from each flat groove to the center of the bottom hole in the processed internal structure is determined by a broach, and the processed size has good consistency; through the mode of machining, the internal structure surface after processing is bright and has no oxide layer, has reduced the gassing rate on surface.
Drawings
Fig. 1A schematically illustrates a front view of a composite pipe shell according to an embodiment of the invention;
fig. 1B schematically illustrates a cross-sectional view of the internal structure of a composite envelope according to an embodiment of the invention;
fig. 1C schematically illustrates an enlarged cross-sectional view of a bottom hole in the internal structure of a composite envelope in accordance with an embodiment of the present invention;
fig. 2 schematically illustrates a flow chart of a method for machining the internal structure of a composite shell in accordance with an embodiment of the invention;
fig. 3 schematically illustrates a cross-sectional view of the internal structure of a composite envelope as machined in accordance with an embodiment of the present invention;
fig. 4 schematically illustrates a perspective view of a broach according to an embodiment of the present invention;
fig. 5 schematically illustrates a cross-sectional view of the broach within the interior of a composite vessel according to an embodiment of the present invention;
fig. 6 schematically illustrates a cross-sectional view of the internal structure of a composite envelope during application according to an embodiment of the invention.
[ description of the above reference ] the following:
1: composite pipe shell
2: a pole shoe;
3: a connecting ring;
4: an internal structure;
5: a bottom hole;
6: a first flat groove;
7: a second flat groove;
8: a third flat groove;
9: broaching;
10: scrap containing flat groove
11: the outer diameter of the composite pipe shell;
12: the end face of the composite pipe shell;
13: round corners;
14: a clamping rod;
15: a helical line;
16: a first set of blades;
17: a second set of blades;
18: a third set of blades;
19: a leading portion;
20: a rear guide part.
Detailed Description
Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. It is to be understood that this description is made only by way of example and not as a limitation on the scope of the invention. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the invention. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.
Where a convention analogous to "at least one of A, B and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B and C" would include but not be limited to systems that have a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.).
In order that the objects, technical solutions and advantages of the present invention will become more apparent, the present invention will be further described in detail with reference to the accompanying drawings in conjunction with the following specific embodiments.
Fig. 1A schematically illustrates a front view of a composite pipe shell according to an embodiment of the invention; fig. 1B schematically illustrates a cross-sectional view of the internal structure of a composite envelope according to an embodiment of the invention; fig. 1C schematically illustrates an enlarged cross-sectional view of a bottom hole in the internal structure of a composite envelope in accordance with an embodiment of the present invention.
As shown in fig. 1A and 1B, the composite envelope 1 includes: sets of pole shoes 2, sets of connecting rings 3 and an inner structure 4. The internal structure 4 may include: the bottom hole 5 penetrates through the center of the composite pipe shell 1; and the bottom of the flat groove is convex relative to other parts of the inner wall in the radial outward direction of the composite pipe shell 1.
As shown in fig. 1B and 1C, the composite shell outside diameter 11, the composite shell end face 12, the bottom hole 5, the first flat groove 6, the second flat groove 7 and the third flat groove 8 can also be seen. The outer diameter 11 of the composite pipe shell is the outer diameter of the end face 12 of the composite pipe shell, the bottom hole 5 is positioned in the center of the end face 12 of the composite pipe shell, and the first flat groove 6, the second flat groove 7 and the third flat groove 8 are uniformly and equidistantly distributed on the edge of the bottom hole 5; at both ends of each flat slot there are rounded corners 13.
According to the embodiment of the invention, the internal structure of the composite tube shell is made into a structure of a bottom hole and three flat grooves, and the plane contact of the three flat grooves can increase a heat dissipation path and improve the heat dissipation performance of the space traveling wave tube.
Fig. 2 schematically illustrates a flow chart of a method for machining the internal structure of a composite envelope in accordance with an embodiment of the invention.
As shown in fig. 2, the method includes steps S201 to S204.
In step S201, a composite case is housed and fixed using a mold having a shape of the composite case.
In step S202, a bottom hole is drilled in the interior of the composite case.
In step S203, the bottom hole is reamed.
In step S204, the inner wall of the composite envelope is broached by a broach having at least one set of blades through the reamed bottom hole to form at least one flat groove on the inner wall, wherein the bottom of the flat groove is convex in a radially outward direction of the composite envelope relative to the other portions of the inner wall.
According to the embodiment of the invention, the mould for clamping the composite tube shell can be firstly processed into the semicircular shape matched with the composite tube shell on the processing equipment, specifically, two semicircular clamping moulds can be selected, when the composite tube shell is placed into one semicircular mould, the other semicircular mould can be connected in a screw or other movable connection mode, the composite tube shell can be pressed and fixed in the mould, so that the concentricity of the circle center of the bottom hole and the circle center of the composite tube shell can be ensured in the bottom hole processing process.
Fig. 3 schematically shows a cross-sectional view of the internal structure of a composite envelope as machined in accordance with an embodiment of the invention.
According to the embodiment of the invention, after the composite pipe shell is fixed, the position of the deep long hole can be selected by taking the outer diameter of the composite pipe shell as a reference, and the deep long hole can be positioned in the center of the composite pipe shell. As shown in fig. 3, the line a indicates that the machining is performed based on the composite case outer diameter 11 when the pilot hole 5 is machined. When the bottom hole 5 is drilled, a gun drill mode can be adopted to drill a deep long hole from the bottom of the composite pipe shell along the extension direction of the composite pipe shell, and the rough machining of the internal structure is completed. The gun drill can reserve a machining allowance of 0.1-0.3 mm in the process of machining the bottom hole. According to an alternative embodiment of the invention, the hole drilling mode can also adopt a drilling mode suitable for processing deep and long holes, such as vertical milling and the like, to drill the deep and long holes.
According to the embodiment of the invention, when the bottom hole is reamed, the same reference and fixing mode as that of the drilled bottom hole can be adopted, for example, the drilled bottom hole can be precisely reamed by taking the outer diameter of the composite pipe shell as the reference, so that the precise machining of the bottom hole is realized, the size of the hole is machined into the required size, the precision of the bottom hole can be improved by further reaming the bottom hole, and the precision of the reaming machining can reach-0.01 mm. According to an alternative embodiment of the present invention, the bottom hole may be precisely machined by honing or the like. The sizes of the bottom hole before processing and the bottom hole after processing can be adaptively adjusted according to actual needs.
According to the embodiment of the invention, the drilling and reaming of the bottom hole are carried out by taking the outer diameter of the composite pipe shell as a reference. During processing, the composite tube shell is compressed and fixed by external equipment, the drilling and reaming of the bottom hole can be realized by only replacing a processing tool without changing the position of the composite tube shell, and the circle center of the bottom hole of the internal structure can be ensured to be the same as that of the composite tube shell.
Fig. 4 schematically illustrates a perspective view of a broach according to an embodiment of the present invention; fig. 5 schematically illustrates a cross-sectional view of the broach within the interior of a composite envelope according to an embodiment of the present invention.
As shown in fig. 4 to 5, the formed broach 9 may be a broach 9 having three groups of blades, and the broach 9 may include a first group of blades 16, a second group of blades 17, and a third group of blades 18. The broach 9 also includes a leading portion 19, a trailing portion 20. The three groups of blades are uniformly and equidistantly distributed on the broaching tool 9, and based on the bottom hole 5 after reaming, the internal structure of the first flat groove 6, the second flat groove 7 and the third flat groove 8 which respectively correspond to the first group of blades 16, the second group of blades 17 and the third group of blades 18 is subjected to primary broaching processing in the internal structure of the bottom hole 5 after reaming, so that the broaching processing of the internal structure of the composite tube shell is finished.
According to the embodiment of the present disclosure, each group of blades may further include a plurality of sub-blades (not shown), and there may be more than 5 sub-blades, and the plurality of sub-blades are arranged in a stepped manner. Specifically, during broaching, the broaching tool 9 matched with the inner diameter of the bottom hole 5 can be adopted, the broaching tool 9 is driven by the broaching machine to make main motion along the direction vertical to the plane of the bottom hole 5, and the sub-cutting edge on the broaching tool 9 makes feed motion, so that the broaching of the composite tube shell is completed. The chip flutes 10 are also arranged beside each group of cutting edges, so that the processed surface can be prevented from being scratched by the burrs after broaching.
According to the embodiment of the invention, the forming broach can also be a broach with a group of blades, and the internal structure with three flat grooves is machined in the internal structure by broaching three times through the reamed bottom hole by taking the reamed bottom hole as a reference, so that the machining of the internal structure of the composite tube shell is completed.
According to the embodiment of the invention, the broaching machining is carried out by taking the reamed bottom hole as a reference, a composite pipe shell is not required to be installed and clamped, and the concentricity of the bottom hole and the three flat grooves can be ensured.
According to the embodiment of the invention, the three-way flat groove structure in the composite tube shell is machined by broaching through the forming broach, the distance from the flat groove to the center of the bottom hole is determined by the broach, and the distance from each flat groove to the center of the bottom hole in the machined composite tube shell internal structure has good consistency.
According to the embodiment of the invention, the bottom hole is machined in a drilling and reaming machining mode, and then the forming broach with the cutting edge is adopted for broaching, so that the machining of the internal structure of the composite tube shell is realized; the size of each flat groove from the center of the bottom hole is determined by a broach, and the processed size has good consistency; through the mechanical processing mode, the processed internal structure surface is bright and has no oxide layer, so that the air release rate of the surface is reduced; the stability and the reliability of the space traveling wave tube are improved. The processing method provided by the embodiment of the invention is easy to realize and complete, and is convenient to popularize and apply.
According to the embodiment of the invention, the composite tube shell after broaching can be placed into the mixed solution of carborundum powder and acetone for ultrasonic cleaning to remove burrs generated after broaching. The method can remove not only the burr with larger size but also the burr with small size, and the burr is removed more cleanly without damaging the surface of the inner structure.
According to the embodiment of the invention, the composite pipe shell after the burrs are removed can be placed into an acetone solution for ultrasonic cleaning again, so that the purpose of deoiling and cleaning the composite pipe shell is realized. The composite tube shell after being processed is cleaned by removing oil, so that oil stains possibly remained on the surface in the processing process are removed, the surface smoothness is improved, and the application performance of the composite tube shell is improved.
According to the embodiment of the invention, the composite tube shell after oil removal cleaning can be subjected to air tightness inspection. Before checking the air tightness, the composite pipe shell can be placed in a hydrogen atmosphere, heat preservation is carried out for 15 minutes at 800 ℃, and high-temperature cleaning treatment is carried out on the composite pipe shell, wherein the atmosphere type, the temperature and the heat preservation time involved in the high-temperature cleaning treatment process can be adjusted according to actual needs. The composite tube shell after high-temperature cleaning treatment can be used for detecting the air leakage rate of the composite tube shell through a helium mass spectrometer leak detector, and when the air leakage rate is smaller than or equal toAt 5X 10-10Pa·m3The product can be identified as a qualified product at the time of/s. However, the standard of the air leakage rate is not 5X 10-10Pa·m3The specific standard value can be determined according to actual needs.
According to the embodiment of the present invention, the appearance of the internal structure of the composite envelope can be checked, and specifically, the surface of the internal structure can be observed by an industrial endoscope such as an electronic endoscope or a fiber optic endoscope, and the brightness and the absence of oxidation of the internal surface can be observed.
According to the embodiment of the invention, the internal structure prepared by a mechanical method has no oxide layer on the surface, so that the air release rate of the surface of the internal structure can be reduced, and the stability and reliability of the space traveling wave tube are improved.
According to embodiments of the present invention, dimensional inspection of the machined composite package may also be performed.
As shown in fig. 3, R1 represents the distance from the first flat groove 6 to the center of the bottom hole 5, R2 represents the distance from the second flat groove 7 to the center of the bottom hole 5, and R3 represents the distance from the third flat groove 8 to the center of the bottom hole 5. By the method provided by the embodiment of the invention, any one of the sizes of R1, R2 and R3 of the processed internal structure is less than or equal to 0.005mm, and the size difference between R1 and R2, the size difference between R2 and R3 and the size difference between R1 and R3 in the corresponding R1, R2 and R3 are less than or equal to 0.005mm, namely, the sizes of R1, R2 and R3 are consistent. The outer diameter 11 of the composite pipe shell is used as a reference for processing, and the concentricity of the processed bottom hole 5 and the end face 12 of the composite pipe shell can be less than or equal to 0.05 mm.
As shown in fig. 1C, the enlarged bottom hole 5 shows that there are rounded corners 13 at both ends of each of the first flat groove 6, the second flat groove 7 and the third flat groove 8, and the rounded corners 13 may be 0.05 or less after machining by the method provided by the embodiment of the present invention.
Fig. 6 schematically illustrates a cross-sectional view of the internal structure of a composite envelope during application according to an embodiment of the invention.
As shown in fig. 6, the inner structure of the composite shell 1 is used to receive the clamping bar 14 and the helical wire 15 during application. The spiral line 15 is located at the center of the bottom hole 5, one end of each of the three clamping rods 14 is located in the first flat groove 6, the second flat groove 7 and the third flat groove 8, and the other end of each of the three clamping rods 14 is connected to the spiral line 15. The fillet that traditional handicraft was prepared is about 0.1mm, and when the assembly product, because the fillet is great, the both ends of flat groove do not have the direction, leads to the side of holding rod 14 to press on fillet 13, easily causes the place easy splitting of holding rod 14 and fillet 13 contact. In the composite tube shell internal structure provided by the embodiment of the invention, the processed round angle is less than or equal to 0.05, so that the possibility of splitting of the clamping rods can be reduced, and the yield of space traveling-wave tubes can be improved.
It should also be noted that directional terms, such as "upper", "lower", "front", "rear", "left", "right", "convex", etc., mentioned in the embodiments are only directions referring to the drawings, and are not intended to limit the protection scope of the present invention. Throughout the drawings, like elements are represented by like or similar reference numerals. Conventional structures or constructions will be omitted when they may obscure the understanding of the present invention.
And the shapes and sizes of the respective components in the drawings do not reflect actual sizes and proportions, but merely illustrate contents of the embodiments of the present invention. Furthermore, the word "comprising" does not exclude the presence of elements or steps not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements.
Similarly, it should be appreciated that in the foregoing description of exemplary embodiments of the invention, various features of the invention are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the invention and aiding in the understanding of one or more of the various inventive aspects. However, the method of the invention should not be construed to reflect the intent: that the invention as claimed requires more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing inventive embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this invention.
The above-mentioned embodiments, objects, technical solutions and advantages of the present invention are further described in detail, it should be understood that the above-mentioned embodiments are only examples of the present invention, and should not be construed as limiting the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A method for processing the internal structure of a composite envelope, comprising:
using a mould with the shape of a composite pipe shell to bear and fix the composite pipe shell;
drilling a bottom hole in the composite pipe shell;
reaming the bottom hole; and
broaching the inner wall of the composite tube shell by using a broaching tool having at least one set of cutting edges through the reamed bottom hole to form at least one flat groove on the inner wall, wherein the bottom of the flat groove is protruded in a radially outward direction of the composite tube shell relative to the other portions of the inner wall.
2. The method of claim 1, wherein broaching the inner wall of the composite shell with a broach having at least one set of cutting edges through the reamed pilot hole comprises:
and the broaching tool matched with the inner diameter of the bottom hole is adopted, the broaching tool is driven by the broaching machine to do main motion along the direction vertical to the plane of the bottom hole, and the cutting edge on the broaching tool does feed motion to finish broaching processing of the inner wall of the composite tube shell.
3. The method of claim 1, further comprising, after the broaching:
and putting the composite tube shell with at least one flat groove into a mixed solution of diamond yarn powder and acetone for ultrasonic cleaning to remove burrs.
4. The method of claim 3, further comprising, after the ultrasonic cleaning:
and putting the composite tube shell subjected to deburring into an acetone solution for ultrasonic deoiling cleaning to obtain the machined composite tube shell.
5. The method of claim 1 wherein the composite shell is compressed and secured by screws after the composite shell is placed in the mold.
6. The method of claim 1, further comprising: broaching the inner wall of the composite tube shell by using a broaching tool with three groups of cutting edges through the reamed bottom hole so as to form three flat grooves on the inner wall, wherein the bottoms of the flat grooves are raised relative to other parts of the inner wall in the radial outward direction of the composite tube shell.
7. The method of claim 1 wherein the drilling of the bottom hole and the reaming are performed relative to an outer diameter of the composite shell.
8. The method of claim 1, wherein the broaching is performed with reference to the bottom hole.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210156659.0A CN114523263B (en) | 2022-02-21 | 2022-02-21 | Method for processing internal structure of composite tube shell |
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| CN202210156659.0A CN114523263B (en) | 2022-02-21 | 2022-02-21 | Method for processing internal structure of composite tube shell |
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| CN114523263B CN114523263B (en) | 2023-07-25 |
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| CN86206011U (en) * | 1986-08-21 | 1987-11-11 | 石家庄市煤矿机械厂 | Combined broach for machining irregularly-shaped hole |
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| US20120255786A1 (en) * | 2011-04-08 | 2012-10-11 | Isenhour James D | Method and Apparatus for Reaming Well Bore Surfaces Nearer the Center of Drift |
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| US20140305708A1 (en) * | 2013-04-10 | 2014-10-16 | The Charles Machine Works, Inc. | Reamer With Replaceable Cutters |
| CN110303305A (en) * | 2019-07-23 | 2019-10-08 | 重庆申耀机械工业有限责任公司 | A kind of processing technology of outer ring |
| CN215787285U (en) * | 2021-08-06 | 2022-02-11 | 南京三乐集团有限公司 | Q wave band space traveling wave tube composite tube shell clamp |
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2022
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| CN86206011U (en) * | 1986-08-21 | 1987-11-11 | 石家庄市煤矿机械厂 | Combined broach for machining irregularly-shaped hole |
| CN1054467A (en) * | 1991-01-12 | 1991-09-11 | 余建民 | High secret spring cupboard, door lock |
| US20120255786A1 (en) * | 2011-04-08 | 2012-10-11 | Isenhour James D | Method and Apparatus for Reaming Well Bore Surfaces Nearer the Center of Drift |
| CN102990301A (en) * | 2012-11-27 | 2013-03-27 | 南京三乐电子信息产业集团有限公司 | Method for processing composite pipe shell with 120-degree equally divided straight flutes |
| US20140305708A1 (en) * | 2013-04-10 | 2014-10-16 | The Charles Machine Works, Inc. | Reamer With Replaceable Cutters |
| CN110303305A (en) * | 2019-07-23 | 2019-10-08 | 重庆申耀机械工业有限责任公司 | A kind of processing technology of outer ring |
| CN215787285U (en) * | 2021-08-06 | 2022-02-11 | 南京三乐集团有限公司 | Q wave band space traveling wave tube composite tube shell clamp |
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| 汪通悦: "《机械制造技术基础》" * |
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| CN114523263B (en) | 2023-07-25 |
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