CN112961967B - Single-side cold extrusion fatigue strengthening device and method for orifice of open pore structure - Google Patents
Single-side cold extrusion fatigue strengthening device and method for orifice of open pore structure Download PDFInfo
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- CN112961967B CN112961967B CN202110149387.7A CN202110149387A CN112961967B CN 112961967 B CN112961967 B CN 112961967B CN 202110149387 A CN202110149387 A CN 202110149387A CN 112961967 B CN112961967 B CN 112961967B
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- 239000011148 porous material Substances 0.000 title claims abstract description 40
- 238000005728 strengthening Methods 0.000 title claims abstract description 36
- 238000000641 cold extrusion Methods 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000001125 extrusion Methods 0.000 claims abstract description 50
- 238000005553 drilling Methods 0.000 claims description 6
- 230000002787 reinforcement Effects 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 4
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000008569 process Effects 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 239000000463 material Substances 0.000 description 4
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- 230000009286 beneficial effect Effects 0.000 description 2
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- 230000008859 change Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
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- 238000005253 cladding Methods 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D7/00—Modifying the physical properties of iron or steel by deformation
- C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
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Abstract
The invention discloses a device and a method for strengthening orifice unilateral cold extrusion fatigue of an open pore structure, and particularly relates to the field of aerospace assembly and manufacturing. A hole opening single-side cold extrusion fatigue strengthening device with a hole opening structure comprises a conical head core rod, wherein the conical head core rod is in threaded connection with a pull gun, the upper side of the conical head core rod is a conical body, and the maximum diameter of the conical head core rod is not larger than the hole diameter of the hole opening structure; the outer surface of the conical head core rod is wrapped with a lining, the outer surface of the lining is a rotary curved surface, the maximum diameter of the lining is not larger than the aperture of the opening structure, and the outer surface of the lining is also circumferentially and equidistantly distributed with slots; the conical head core rod is wrapped with an extrusion head, the outer surface of the extrusion head is provided with a revolution curved surface which is the same as the lining, the maximum diameter of the revolution curved surface on the extrusion head is larger than the aperture of the open pore structure, and the extrusion head is connected with a pull gun through threads. By adopting the technical scheme of the invention, the problem that the existing equipment or process cannot realize fatigue strengthening on the orifice is solved, and the fatigue resistance of the orifice with the open pore structure can be improved.
Description
Technical Field
The invention relates to the field of aerospace assembly and manufacturing, in particular to a device and a method for strengthening one-side cold extrusion fatigue of an orifice of an open pore structure.
Background
On an aircraft or spacecraft, the quality of the connection from component to component determines to a large extent the service life and safety performance of the aircraft and spacecraft. The hole structure is most common in riveting or threaded connection structures, but the bolt holes and riveting holes are easy to cause material discontinuity, the edge of the hole has serious structural stress concentration in the service process of an airplane, the hole structure is easy to generate fatigue fracture failure, and even catastrophic aviation accidents are caused. According to statistics, fatigue fracture is the main failure mode of the airplane structural member, about 70% of fatigue cracks in the failure structure are originated from connecting holes, about 90% of body accidents are caused by the failure of the hole structure, and how to efficiently and quickly improve the fatigue strength of the holes becomes one of the key technical problems for improving the safety performance and the benefit of the aerospace related field.
The cold extrusion is taken as the connecting hole fatigue strengthening means which is most widely applied internationally at present, and the fatigue life of the open pore structure can be prolonged by more than 3 times under the condition of good process control. The principle is that a core rod or a ball with the diameter larger than the diameter of the hole and the hardness higher than that of a material of the connecting hole is extruded through the connecting hole to force the material of the hole wall to generate elastic-plastic deformation, a large-depth high-amplitude controllable residual compressive stress layer is introduced into the hole wall, the hole edge local stress distribution state of the hole structure under the action of external load is improved, the fatigue strength, the stress corrosion resistance and the corrosion fatigue resistance of the connecting hole are greatly improved, and the method has the advantages of no change of materials, no change of structural design, no increase of airplane weight, low cost, obvious reinforcing effect, wide application aperture range and the like, meets the design and manufacturing concept of the current airplane to a great extent, and is widely applied to the reinforcement of the connecting holes of key load-bearing members of the airplane, such as the connecting holes between wings and an airplane body, bolt holes on the lower surfaces of the wings and the like.
At present, there are many techniques for improving the fatigue strength of the hole by cold extrusion, such as direct mandrel extrusion, slotted bushing extrusion, ball extrusion, and sleeve extrusion. However, the above methods have many disadvantages, such as high requirements on the size and shape of the workpiece, certain requirements on the structure of the hole, and incapability of recycling.
In view of the above problems, the method for cold extrusion processing of a slotted bushing disclosed in chinese patent application No. 201010137411.7 solves the problem that in the butt joint area of a wing body, because the space at the butt joint area is limited, the process path is poor, and only manual hole making can be adopted, the traditional cold extrusion steps of drilling a primary hole, reaming a primary hole, measuring a primary hole, cold extrusion, fine reaming and measuring a fine hole are improved. The method for preparing the hole by cold extrusion of the slotted bushing comprises the steps of drilling a primary hole, reaming the primary hole, checking the diameter of the hole, checking a core rod, carrying out cold extrusion on the hole, checking the diameter of the cold extrusion hole, finely reaming the hole and checking the diameter of a final hole. Wherein, when drilling the initial hole, the initial hole is prepared by drilling and expanding the hole for at least three times. According to the process method for preparing the initial hole for the slotted bushing with different diameters and specifications, the different diameters are combined with different drilling and reaming tool specifications and times, the prepared initial hole meets the requirements through plug gauge inspection, the requirements of the subsequent slotted bushing cold extrusion process are met, and the hole opening accuracy is high. However, in the above method, there is a certain requirement for the structure of the primary hole, and the bushing and the equipment need to be replaced only in one cold extrusion process, which is complicated in steps, and only one side of the hole periphery can be extruded, and the direction of the extrusion on the other side needs to be changed. The time spent on manufacturing and overhauling the airplane is long, the hole strengthening is difficult to be carried out efficiently, and the method only strengthens the hole wall and cannot effectively strengthen the hole opening.
Disclosure of Invention
The invention aims to provide a hole opening structure orifice unilateral cold extrusion fatigue strengthening device, and solves the problem that the existing equipment or process cannot realize the fatigue strengthening of the orifice.
In order to achieve the purpose, the technical scheme of the invention is as follows: a hole opening single-side cold extrusion fatigue strengthening device with a hole opening structure comprises a conical head core rod, wherein the bottom of the conical head core rod is in threaded connection with a pull gun, the middle of the conical head core rod is cylindrical, the upper side of the conical head core rod is a conical body, and the maximum diameter of the conical head core rod is not larger than the aperture of the hole opening structure; the outer side of the conical head core rod is wrapped with a bushing which has the same cone angle as the conical head core rod, the outer surface of the bushing is a revolution curved surface, the maximum diameter of the bushing is not larger than the aperture of the opening structure, slits are distributed on the outer surface of the bushing at equal intervals in the circumferential direction, and each slit is arranged along the axial direction of the bushing; the middle part cladding of conical head plug has the extrusion head that offsets with the bush, the surface that extrusion head and bush offset one end is equipped with the surface of gyration the same with the bush, the biggest diameter of gyration the surface is greater than the aperture of trompil structure on the extrusion head, the overhead one end threaded connection who keeps away from the bush of extrusion has and draws the rifle.
Furthermore, the outer surface of the bushing is in the shape of a conical surface, under the same conditions, the reinforcement degree of the hole opening structure along the axial direction increases along with the increase of the conical surface taper angle, and the reinforcement degree of the hole opening structure along the hole radial direction decreases along with the increase of the conical surface taper angle.
Through the arrangement, the fatigue strengthening device can be used for fatigue strengthening of the large-diameter hole opening in the hole opening structure.
Further, the shape of the outer surface of the bushing includes a generatrix so as to satisfy a power function
The equation of (a) is that x is R to x is a revolution surface in an interval of R, wherein R is the radius of the outer ring of the small end of the bushing, and R is the radius of the outer ring of the large end of the bushing.
Further, the shape of the outer surface of the bushing comprises a revolution surface of which a generatrix is in an interval from x to R in an equation meeting a trigonometric function, an inverse trigonometric function y is sinx, arcsinx, tanx and arctanx, wherein R is the radius of the outer ring of the small end of the bushing, and R is the radius of the outer ring of the large end of the bushing. .
Further, the shape of the outer surface of the bushing includes a generatrix so as to satisfy an exponential function, and a logarithmic function y is 2 x 、3 x 、log 2 x、log 3 And x is R to R is the radius of the outer ring of the small end of the bushing, and R is the radius of the outer ring of the large end of the bushing. .
Further, the strengthening method of the strengthening device comprises the following steps:
s101, selecting a proper bushing, a proper conical head core rod and a proper extrusion head according to the aperture of the open pore structure;
s103, connecting the extrusion head with a pull gun, connecting the middle part of the conical head core rod with another pull gun after penetrating through the bushing, and then putting the conical head core rod and the bushing into a hole with an open pore structure;
s105, tightly pushing the pull gun on one side of the extrusion head by force to enable the revolution surface of the extrusion head to be in contact with the outer side orifice of the open pore structure;
s107, starting a pull gun on one side of the conical head core rod, pulling the conical head core rod by the pull gun to move axially, enabling the outer surface of the conical head core rod to be in contact with the inner surface of the bushing and extrude the bushing, enabling a rotating curved surface on the outer surface of the bushing to open circumferentially along the slit and extrude an orifice on the inner side of the open pore structure, and driving the extrusion head to further extrude the orifice on the outer side of the open pore structure by axial tensile force generated by extrusion;
and S109, stopping pulling the gun when the extrusion displacement of the pull gun meets the requirement, releasing the pull force, recovering the original shape of the bushing under the elastic action, taking out the conical head core rod and the bushing, and completing the single-side cold extrusion fatigue strengthening of the orifice of the open pore structure.
Compared with the prior art, the beneficial effect of this scheme:
according to the scheme, extrusion force is applied to the orifice of the open pore structure, the orifice is subjected to plastic deformation, the microstructure of the orifice is improved, beneficial residual compressive stress is formed at the same time, and the fatigue life of the open pore structure is prolonged; through using the bush, the problem of loaded down with trivial details repeated dismantlement has been avoided in the poor or airtight trompil structure's of openness unilateral cold extrusion fatigue strengthening of having solved, has improved the efficiency of extrusion strengthening.
Drawings
FIG. 1 is a schematic view of an entire hole of the open-hole structure of example 1 before strengthening;
FIG. 2 is a schematic view of the whole process of reinforcing the upper orifice of the open-cell structure in example 1;
FIG. 3 is an isometric view of a cone head core rod of the present invention;
figure 4 is an isometric view of an extrusion head of the present invention.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the device comprises a perforated structure 1, a conical head core rod 2, a bushing 3 and an extrusion head 4.
Example 1
As shown in figures 1 and 2: the utility model provides a 1 drill way unilateral cold extrusion fatigue strengthening device of trompil structure, includes conical head plug 2, and the bottom of conical head plug 2 is equipped with the external screw thread, and the bottom threaded connection of conical head plug 2 has the rifle of drawing. As shown in fig. 3, the middle lower part of the conical head core rod 2 is cylindrical, the upper side of the conical head core rod 2 is a cone, the upper side of the conical head core rod 2 is used for extruding the bushing 3, and the maximum diameter of the conical head core rod 2 is not larger than the aperture of the open pore structure 1. The upper side of the conical head core rod 2 is coated with a lining 3 with the same taper angle as the upper taper angle of the conical head core rod 2, the outer surface of the lining 3 is a revolution surface, and the revolution surface of the lining 3 in the embodiment is a conical surface and is mainly suitable for fatigue strengthening of a large-diameter orifice in the open pore structure 1. Under the same condition, the strengthening degree of the orifice of the open pore structure 1 along the axial direction and the conical angle increase and increase, and the strengthening degree of the orifice of the open pore structure 1 along the radial direction of the orifice and the conical angle increase and decrease. The maximum diameter of the bushing 3 is not larger than the aperture of the open pore structure 1, the outer surface of the bushing 3 is also circumferentially and equidistantly distributed with 2-8 slots, each slot is arranged along the axial direction of the bushing 3, the number of slots is selected according to the aperture of the open pore structure 1, and the larger the aperture of the open pore structure 1 is, the more the number of slots is; the bushing 3 is used for extruding or closing the inner side hole opening of the open pore structure 1 to generate plastic deformation. As shown in the attached drawing 4, the middle lower part of the conical head core rod 2 is coated with an extrusion head 4 which is abutted against the lining 3, the outer surface of the upper side of the extrusion head 4 is provided with a revolution surface which is the same as the lining 3, the revolution surface of the extrusion head 4 and the revolution surface of the lining 3 are symmetrically distributed by the contact surfaces of the two, the contact surfaces of the extrusion head 4 and the lining 3 are positioned at the middle lower part of the conical head core rod 2, the bottom of the extrusion head 4 is provided with internal threads, and the bottom of the extrusion head 4 is in threaded connection with a pull gun.
The strengthening method of the strengthening device comprises the following steps:
s101, selecting a proper bushing 3, a proper conical head core rod 2 and a proper extrusion head 4 according to the aperture of the open pore structure 1; measuring the maximum outer diameter of the insert 3 when undeformed requires that the maximum outer diameter of the insert 3 is less than or equal to the bore diameter of the open-cell structure 1 so that the insert 3 can nest into the bore of the open-cell structure 1. The outer diameter of the middle lower part of the conical head core rod 2 is smaller than the minimum inner diameter of the selected bushing 3, so that the condition that the bushing 3 is damaged by interference fit is avoided. After the bushing 3 and the conical head core rod 2 are selected, a proper extrusion head 4 is selected, and the shape of the outer surface of the upper part of the extrusion head 4 is required to be completely the same as that of the revolution surface outside the bushing 33.
S103, connecting the extrusion head 4 with a pull gun, connecting the middle lower part of the conical head core rod 2 with another pull gun after penetrating through the bush 3, and then putting the conical head core rod 2 and the bush 3 into a hole of the open pore structure 1;
s105, forcibly jacking a pull gun on one side of the extrusion head 4 to enable the revolution curved surface of the extrusion head 4 to be in contact with the outer side orifice of the open pore structure 1;
s107, starting a pulling gun on one side of the conical head core rod 2, pulling the conical head core rod 2 to move axially, and enabling the outer surface of the upper side of the conical head core rod 2 to be in contact with the inner surface of the lining 3, so that the inner surface of the lining 3 can be extruded and the revolution surface of the outer surface of the lining 3 can be expanded circumferentially along the slit, an inner orifice of the open pore structure 1 can be extruded, and meanwhile, an axial tensile force generated by extrusion drives the extrusion head 4 to further extrude an outer orifice of the open pore structure 1;
s109, stopping pulling the gun when the extrusion displacement of the gun reaches the requirement, releasing the pulling force, recovering the original shape of the lining 3 under the elastic action, taking out the conical head core rod 2 and the lining 3, and completing the one-side cold extrusion fatigue strengthening of the orifice of the open pore structure 1.
By the scheme, one side of the hole in the open pore structure is outside, the other side of the hole is in the cavity with limited space, and the inside and the outside of the orifice are both required to be strengthened. The reinforcing device can enter the cavity from the outer side to simultaneously carry out fatigue reinforcement on the outer side and the inner side of the orifice of the open pore structure.
Example 2
This example differs from example 1 only in that: the shape of the outer surface of the liner 3 in the present embodiment includes generatrices to satisfy a power function
The equation of (a) is that x is R to x is R, the R is the radius of the outer ring of the small end of the bushing 3, and R is the radius of the outer ring of the large end of the bushing 3, and the method is suitable for fatigue strengthening of the orifice of the medium-diameter open-pore structure 1.
Example 3
This example differs from example 1 only in that: in the present embodiment, the outer surface shape of the bushing 3 includes a surface of revolution in an interval from x to x, R being a radius of an outer ring of the small end of the bushing 3, R being a radius of an outer ring of the large end of the bushing 3, and R being a radius of an outer ring of the small end of the bushing 3, in an equation where a generatrix satisfies a trigonometric function, an inverse trigonometric function y being sinx, arcsinx, tanx, and arctanx, and is suitable for fatigue strengthening of the orifice of the small-diameter open-cell structure 1.
Example 4
This example differs from example 1 only in that: the shape of the outer surface of the bush 3 in this embodiment includes that the bus bar is fullThe foot exponential function and the logarithmic function y are 2 x 、3 x 、log 2 x、log 3 In the equation of x, x is R to x is the revolution surface in the R interval, R is the radius of the outer ring of the small end of the bushing 3, R is the radius of the outer ring of the large end of the bushing 3, and the method is suitable for fatigue strengthening of the orifice of the small-diameter thick interlayer deep hole structure.
The above are merely examples of the present invention and common general knowledge of known specific structures and/or characteristics of the schemes has not been described herein in more detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (4)
1. The utility model provides a cold extrusion fatigue strengthening device of trompil structure drill way unilateral which characterized in that: the drilling tool comprises a conical head core rod, wherein a drawing gun is connected to the bottom of the conical head core rod in a threaded manner, the middle of the conical head core rod is cylindrical, a conical body is arranged on the upper side of the conical head core rod, and the maximum diameter of the conical head core rod is not larger than the aperture of an open pore structure; the outer side of the conical head core rod is wrapped with a bushing which has the same cone angle as the conical head core rod, the outer surface of the bushing is a revolution curved surface, the maximum diameter of the bushing is not larger than the aperture of the opening structure, slits are distributed on the outer surface of the bushing at equal intervals in the circumferential direction, and each slit is arranged along the axial direction of the bushing; the middle part of the conical head core rod is coated with an extrusion head which is abutted to the bushing, the outer surface of one end of the extrusion head which is abutted to the bushing is provided with a revolution surface which is the same as that of the bushing, the maximum diameter of the revolution surface on the extrusion head is larger than the aperture of the opening structure, and one end of the extrusion head which is far away from the bushing is connected with a pull gun in a threaded manner;
the strengthening method of the strengthening device comprises the following steps:
s101, selecting a proper bushing, a proper conical head core rod and a proper extrusion head according to the aperture of the open pore structure;
s103, connecting the extrusion head with a pull gun, connecting the middle part of the conical head core rod with another pull gun after penetrating through a lining, and then placing the conical head core rod and the lining into a hole with an open pore structure;
s105, tightly pushing the pull gun on one side of the extrusion head by force to enable the revolution surface of the extrusion head to be in contact with the outer side orifice of the open pore structure;
s107, starting a pull gun on one side of the conical head core rod, pulling the conical head core rod by the pull gun to move axially, contacting the outer surface of the conical head core rod with the inner surface of the lining and extruding the lining, opening the rotary curved surface of the outer surface of the lining along the circumferential direction of the slit and extruding the inner hole opening of the open pore structure, and driving the extrusion head to further extrude the outer hole opening of the open pore structure by axial tensile force generated by extrusion;
s109, stopping drawing the gun after the extrusion displacement of the drawing gun meets the requirement, releasing the tension, recovering the original shape of the bushing under the elastic action, taking out the conical head core rod and the bushing, and completing the single-side cold extrusion fatigue strengthening of the orifice of the open pore structure;
the outer surface of the bushing is in the shape of a conical surface, under the same condition, the reinforcement degree of the hole opening of the open hole structure along the axial direction is increased along with the increase of the conical surface taper angle, and the reinforcement degree of the hole opening of the open hole structure along the hole diameter direction is reduced along with the increase of the conical surface taper angle.
2. The open-structured-orifice single-sided cold extrusion fatigue-strengthening device of claim 1, wherein: the shape of the outer surface of the bushing includes a generatrix to satisfy a power function
The equation of (a) is that x is R to x is a revolution surface in an interval of R, wherein R is the radius of the outer ring of the small end of the bushing, and R is the radius of the outer ring of the large end of the bushing.
3. The open-structured-orifice single-sided cold extrusion fatigue-strengthening device of claim 1, wherein: the outer surface shape of the bushing comprises a revolution surface in an interval from x to R in an equation of which the generatrix satisfies a trigonometric function, an inverse trigonometric function y is sinx, arcsinx, tanx and arctanx, wherein R is the radius of the outer ring of the small end of the bushing, and R is the radius of the outer ring of the large end of the bushing.
4. The single-side cold extrusion fatigue strengthening device for the open-pore structure orifice according to claim 1, wherein: the shape of the outer surface of the bushing comprises a bus satisfying an exponential function and a logarithmic function y-2 x 、3 x 、log 2 x、log 3 And x is R to R is the radius of the outer ring of the small end of the bushing, and R is the radius of the outer ring of the large end of the bushing.
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| US20110045915A1 (en) * | 2009-08-20 | 2011-02-24 | Kuo-Chung Wang | Method for the fabrication of a screw member for plate member fastener |
| CN102205488A (en) * | 2010-03-31 | 2011-10-05 | 中国商用飞机有限责任公司 | Method for processing hole in split-sleeve cold extrusion manner |
| US20130092298A1 (en) * | 2011-10-12 | 2013-04-18 | Abbott Cardiovascular Systems, Inc | Methods of fabricating a refractory-metal article, and apparatuses for use in such methods |
| ITTO20120551A1 (en) * | 2012-06-22 | 2013-12-23 | Lucio Carretta | PROCEDURE FOR THE MANUFACTURE OF A METAL TUBE WITH AT LEAST A SMOOTH PORTION AND AT LEAST A SPLINED PORTION, EQUIPMENT USED IN THE PROCEDURE AND PRODUCT OBTAINED |
| CN203923287U (en) * | 2014-06-25 | 2014-11-05 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of slotted liner bushing and the plug being used in conjunction with this slotted liner bushing |
| CN105081111B (en) * | 2015-07-21 | 2017-03-01 | 贵州航太精密制造有限公司 | A kind of mechanical connection pressurizing unit |
| JP6958326B2 (en) * | 2017-12-19 | 2021-11-02 | トヨタ自動車株式会社 | How to manufacture high pressure tank |
| CN110408756B (en) * | 2019-07-15 | 2022-03-15 | 西北工业大学 | Rotary type hole cold extrusion strengthening device and method |
| CN211522268U (en) * | 2019-12-25 | 2020-09-18 | 广东工业大学 | Bushing pipe structure and small hole strengthening device |
| CN111635983B (en) * | 2020-06-12 | 2021-02-26 | 四川大学 | Hole pulling-twisting coupling cold extrusion strengthening core rod and strengthening method thereof |
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| CN1637273A (en) * | 2003-12-16 | 2005-07-13 | 臼井国际产业株式会社 | High-pressure fuel pipe for diesel engines |
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