CN112170880A - Rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method - Google Patents
Rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method Download PDFInfo
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- CN112170880A CN112170880A CN202010957737.8A CN202010957737A CN112170880A CN 112170880 A CN112170880 A CN 112170880A CN 202010957737 A CN202010957737 A CN 202010957737A CN 112170880 A CN112170880 A CN 112170880A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B41/00—Boring or drilling machines or devices specially adapted for particular work; Accessories specially adapted therefor
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
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Abstract
The invention provides an ultrasonic-assisted hole making process method for a CFRP supporting plate at a rocket cabin section, which is characterized in that a main shaft of an ultrasonic vibration hole making device is rotated at 3000-4000 r/min, the feeding speed is 20-40 mm/min, the tool suspension length is 35-40mm, and the ultrasonic vibration frequency is 20-30 kHz. The method is suitable for processing the assembling connecting holes of the carbon fiber composite material supporting plate at the rocket cabin section, can improve the hole making quality and stability, improve the processing efficiency by more than 50 percent, and greatly reduce the operation difficulty and labor intensity of workers. Meanwhile, the method can be popularized and applied to all carbon fiber aluminum alloy sandwich products with similar structures and characteristics, and particularly has good application prospect on a new generation of carrier rockets.
Description
Technical Field
The invention belongs to the technical field of ultrasonic-assisted hole making processes, and particularly relates to an ultrasonic-assisted hole making process method for a CFRP supporting plate of a rocket cabin section.
Background
The instrument pod in the launch vehicle is the brain of the launch vehicle and its primary function is to provide sufficient space and mounting surface for the instruments installed therein. The instrument mounting plate of a new generation of carrier rocket is a new structure of an annular panel, is supported and fixed on a cabin section by a plurality of triangular support plates made of carbon fiber composite materials (CFRP) in a combined mode, is a most main instrument mounting platform of the whole cabin section, and is used for mounting a plurality of important instruments such as rocket-borne computers. The triangular support plate is connected with the instrument mounting plate through bolts and mainly bears tensile load, and the triangular support plate is connected with the cabin section through advanced titanium ring groove rivets and mainly bears shear load.
The assembling quality of the instrument mounting plate is the premise that an instrument can reliably work when the instrument mounting plate is mounted on the instrument mounting plate, and the processing quality of the triangular support plate assembling connecting hole is a key factor for determining the assembling reliability of the instrument mounting plate.
The triangular support plate assembly connecting hole comprises a rivet assembly hole connected with the cabin section and a bolt assembly hole connected with the instrument mounting plate. Limited by the I-shaped structure of the triangular supporting plate, and the drilling of the assembly connecting holes can only adopt the assembly drilling mode. And rivet assembling holes connected with the shell are drilled towards the supporting plate in a mode of pre-drilling bottom holes on cabin stringers, the processing material is an aluminum alloy/carbon fiber composite material lamination, and the processing sequence is aluminum alloy and carbon fiber composite material in sequence. The bolt connecting hole connected with the instrument mounting plate adopts a drill plate coordinated drilling mode, and the processing material is a carbon fiber composite material. When the triangular support plate assembly holes are drilled, one side of an outlet is the triangular support plate, and the CFRP material has the characteristics of anisotropy, low interlayer strength, high hardness and extremely strong wear resistance, so that better drilling quality is difficult to obtain, a machining cutter is fast in wear, the operation difficulty is high, and the drilling efficiency is low.
The system hole technology of present triangular support board pilot hole is manual air drill drilling, and the processing cutter is ordinary high-speed steel, mainly has following problem during the system hole:
1. the hole making quality is poor. The size precision of the hole is poor, and the fluctuation is large; the defects of layering, splitting, burrs and the like are easily generated at the inlet and the outlet of the hole, the appearance of the hole is uneven, and the quality defect degree is unstable.
2. The hole-making cutter has poor wear resistance and short service life. The high-speed steel drill bit is adopted for drilling holes, the wear resistance is not high, about 10 holes are generally drilled, the cutter needs to be sharpened again, on one hand, the abrasion of the cutter brings associated influence on the hole quality, and meanwhile, the operation cost, the influence efficiency and the processing cost are increased.
3. The manual hole making operation difficulty is high, and the hole making efficiency is low. In order to reduce the defects of layering, tearing and the like during hole making as much as possible and obtain better hole making quality, the feeding process must be strictly controlled and the slow and uniform feeding is kept, so that on one hand, the hole making process is difficult to control, meanwhile, the machining efficiency is low, and 1 hole is machined for about 20 seconds.
Since birth, ultrasonic vibration machining technology is widely applied in production by virtue of the outstanding performance of the ultrasonic vibration machining technology in the aspects of difficult-to-machine materials and high-precision part machining. The ultrasonic vibration assisted machining mechanism is that the machined material is continuously impacted and extruded through high-frequency vibration, the cutting motion of a cutter is periodic pulse cutting, the cutting stroke is short, the cutting amount is uniform, the cutting force is small, and only 1/3-1/10 of common cutting is achieved; the heat dissipation condition is good, the temperature of the processed surface is greatly reduced, and the processing precision and the surface quality are obviously improved (the principle is shown in figure 1); the cutting chips are easy to discharge, the abrasion of the cutter is small, and the service life of the cutter is greatly prolonged. Therefore, the ultrasonic vibration assisted hole making technology is introduced, and the ultrasonic vibration assisted hole making technology is necessary to be applied to the processing of the carbon fiber composite material at the rocket cabin section.
Disclosure of Invention
In view of the above, the invention aims to provide an ultrasonic-assisted hole drilling process method for a CFRP supporting plate of a rocket cabin section, so as to overcome the defects of the prior art, determine an applicable tool for drilling a carbon fiber composite triangular supporting plate assembly connecting hole and process parameters (ultrasonic frequency, tool overhang length, rotating speed and feeding speed) of ultrasonic-assisted hole drilling, and form a drilling process scheme for the rocket cabin section composite triangular supporting plate assembly connecting hole, so as to improve hole drilling precision, reduce hole drilling defects, enhance hole quality stability, reduce operation difficulty and labor intensity of workers, and realize high-quality, high-efficiency and automatic hole drilling.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method is characterized in that a main shaft of an ultrasonic vibration hole making device rotates at 3000-4000 r/min, the feeding speed is 20-40 mm/min, the tool hanging length is 35-40mm, and the ultrasonic vibration frequency is 20-30 kHz.
Further, the processing hole is a rivet connection radial hole of the cabin section triangular supporting plate and the cabin section, or a bolt connection axial hole of the cabin section triangular supporting plate and the instrument mounting plate; the cabin section is made of aluminum alloy materials, and the triangular supporting plate is made of carbon fiber composite materials.
Further, the cutter is a hard alloy drill bit.
Further, when the hanging length of the cutter is 35mm, the corresponding ultrasonic frequency is 27.1 KHz; when the hanging length of the cutter is 40mm, the corresponding ultrasonic frequency is 26.4 KHz.
Further, when a radial hole is machined, a special tool for the radial hole is used, wherein the special tool for the radial hole comprises a support, a guide rail, a sliding block and a holding seat; two linear guide rails are arranged on a vertical plate of the support along the vertical direction, and an execution end of the ultrasonic auxiliary hole making device is fixed on the linear guide rails through a holding seat and a sliding block to realize vertical sliding.
Further, when the axial hole is machined, a special tool for the axial hole is used, wherein the special tool for the axial hole comprises a support, a guide rail, a sliding block and a holding seat; two linear guide rails are installed on a cross beam of the support along the horizontal direction, and an execution end of the ultrasonic auxiliary hole making device is fixed on the linear guide rails through the holding seat and the sliding block to realize horizontal sliding.
Further, according to the position of the triangular support plate, a position for fixing a special tool for a radial hole or an axial hole is correspondingly machined on the outer edge of the fixture platform, and the position corresponds to the position of a hole to be machined; before processing, firstly, positioning and clamping a triangular support plate and a cabin section by using the existing drill plate; and fixing a special tool for the radial hole or the axial hole on the outer edge of the frame platform through a positioning pin hole and a bolt connecting hole on the bottom plate of the support, adjusting the position of the ultrasonic auxiliary hole making execution end on the guide rail, and realizing positioning and locking.
Compared with the prior art, the ultrasonic-assisted hole making process method for the CFRP supporting plate of the rocket cabin section has the following advantages:
the method is suitable for processing the assembling connecting holes of the carbon fiber composite material supporting plate at the rocket cabin section, can improve the hole making quality and stability, improve the processing efficiency by more than 50 percent, and greatly reduce the operation difficulty and labor intensity of workers. Meanwhile, the method can be popularized and applied to all carbon fiber aluminum alloy sandwich products with similar structures and characteristics, and particularly has good application prospect on a new generation of carrier rockets.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention and are not intended to limit the invention. In the drawings:
FIG. 1 is a schematic diagram of the principle of ultrasound-assisted hole making;
FIG. 2 is a schematic diagram of a cutting scheme of the cutter in the embodiment of the invention;
FIG. 3 is a schematic view of a processing object and a working condition in the embodiment of the present invention;
FIG. 4 is a schematic diagram of a hole site for machining according to an embodiment of the present invention;
FIG. 5 is a schematic view of a radial hole machining principle in an embodiment of the present invention;
FIG. 6 is a schematic view of the axial hole machining principle in the embodiment of the present invention;
description of reference numerals:
1-a workpiece; 2-cutting tools; 3-a horn; 4-an energy converter; 5-ultrasonic generator; 6-CFRP supporting plate; 7-aluminum alloy lamination; 8-type frame upper cover; 9-cabin section; a 10-type jig drilling plate; 11-a triangular support plate; 12-a jig platform; 13-axial bore; 14-radial holes; 15-a guide rail; 16-an ultrasonic-assisted hole making execution end; 17-support.
Detailed Description
It should be noted that the embodiments and features of the embodiments of the present invention may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings, which are merely for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be construed as limiting the invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
In the description of the invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "connected" and "connected" are to be construed broadly, e.g. as being fixed or detachable or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
The invention will be described in detail with reference to the following embodiments with reference to the attached drawings.
A rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method is characterized in that a spindle of an ultrasonic vibration hole making device rotates at a speed of 3000-4000 r/min, a feeding speed is 20-40 mm/min, a tool 2 is 35-40mm in hanging length, and the ultrasonic vibration frequency is 20-30 kHz.
The tool 2 is a cemented carbide drill. The hard alloy drill bit has good rigidity, high processing precision and better cutting performance, the problem of large brittleness is also improved under the assistance of ultrasound, and the hard alloy drill bit is a cutter which is more suitable for processing carbon fiber composite materials than a high-speed steel drill bit.
When the ultrasonic vibration assisted drilling is carried out, the ultrasonic resonance frequencies of the cutters 2 with different suspension lengths are different, and the clamping suspension length of the cutters 2 and the resonance frequency corresponding to the clamping suspension length are determined by transversely comparing the sizes of the machined holes and taking the aperture precision phi 5 +/-0.1 mm/phi 6 +/-0.1 mm as a judgment basis.
The suspension length of the cutter 2 is in direct proportion to the amplitude of the cutter 2, the larger the suspension length is, the larger the amplitude is, and the larger the transverse swing amplitude of the cutter is brought by the overlarge amplitude, so that the aperture is larger during processing, but the ultrasonic vibration effect is not obvious due to the overlarge amplitude;
when the clamping overhang length of the cutter 2 is 35mm (phi 5) and the ultrasonic frequency is 27.1KHz and the ultrasonic frequency is 26.4KHz and the ultrasonic frequency is 40mm (phi 6), the aperture can meet the aperture precision requirement, and meanwhile, the amplitude of the cutter 2 is the largest and the processing efficiency is the highest.
The shapes of the inlet, the outlet and the hole wall of the hole are comprehensively compared, and good hole quality can be obtained when the cutting process parameters are 3000-4000 r/min at the rotating speed and 20-40 mm/min at the feeding speed, layering and splitting defects are avoided, and the burr size is minimum.
The processing hole is a radial hole 14 for rivet connection of the cabin section triangular support plate 11 and the cabin section 9, or an axial hole for bolt connection of the cabin section triangular support plate 11 and the instrument mounting plate; the cabin section 9 is made of aluminum alloy material, the triangular supporting plate 11 is made of carbon fiber composite material (as shown in figure 3)
The processing holes are rivet connection holes (radial holes) of the cabin section triangular support plate 11 and the cabin section 9 and bolt connection holes (axial holes 13) of the instrument mounting plate, as shown in fig. 4. The processing material of the radial hole 14 is an aluminum alloy/carbon fiber composite material lamination, the hole making direction is from outside to inside (aluminum alloy → carbon fiber composite material), and a bottom hole is prefabricated through a shell section and matched with a drill; the processing material of the axial hole 13 is carbon fiber composite material, and the hole making direction is from top to bottom, and the drill is matched through the tool.
The processing equipment comprises: the portable ultrasonic auxiliary hole making execution end and the special positioning tool.
The portable ultrasonic vibration hole making device has the technical parameter requirements that: the rotating speed of the main shaft is not lower than 4000r/min, the feeding speed is not lower than 20mm/min, the feeding stroke is larger than 40mm, and the ultrasonic vibration frequency is 20-30 kHz.
(1) Radial hole (laminated aluminum alloy/carbon fiber composite material)
As shown in fig. 5, when a radial hole is machined, a radial hole dedicated tool is used, wherein the radial hole dedicated tool includes a bracket 17, a guide rail 15, a slider (not shown in the figure), and a holding seat (not shown in the figure); two linear guide rails 15 are installed on a vertical plate of a support 17 along the vertical direction, and an ultrasonic auxiliary hole making execution end 16 is fixed on the linear guide rails 15 through an embracing seat and a sliding block to realize vertical sliding. The bottom plate of the bracket 17 is provided with two groups of positioning pin holes and bolt connecting holes, and the side surfaces of the holding seat and the bracket are provided with a series of positioning pin holes.
According to the position of the triangular support plate 11, a position for fixing a special tool is correspondingly processed on the outer edge of the fixture platform 12. The special tool is respectively fixed at two positions on the outer edge of the fixture platform 12 through two groups of positioning pin holes and bolt connecting holes on the bottom plate of the support, and each position corresponds to the position of one row of holes to be machined. Positioning pin holes on the side surfaces of the holding seat and the support correspond to positions of holes to be processed in the vertical direction one by one, the position of the portable ultrasonic auxiliary hole making execution end 16 on the guide rail 15 is adjusted, and accurate positioning is realized through the positioning pins. As shown in fig. 5.
Before machining, the triangular support plate 11 and the cabin section 9 are positioned and clamped by using the existing jig drilling plate 10. The special tool is fixed on the outer edge of the fixture platform 12 through a positioning pin hole and a bolt connecting hole on a support bottom plate, the position of the portable ultrasonic auxiliary hole making execution end 16 on the guide rail 15 is adjusted, and positioning and locking are achieved through a positioning pin. And starting the portable ultrasonic auxiliary hole-making executing end 16, finishing the processing of the hole from outside to inside according to preset processing parameters, then adjusting the position of the portable ultrasonic auxiliary hole-making executing end 16 on the guide rail 15 to a second hole to be processed, completing positioning and locking by using a positioning pin, and then starting the processing of the hole. After 8 holes in the row are machined, the position of the special tool is adjusted, the special tool is positioned and locked by using the other group of positioning pin holes in the bottom plate of the support, and then the machining action is repeated to complete the machining of the holes in the second row.
(2) Axial hole (carbon fiber composite material)
As shown in fig. 6, when the axial hole 13 is machined, an axial hole dedicated tool is used, wherein the axial hole dedicated tool includes a bracket 17, a guide rail 15, a slider (not shown in the figure), and a locking seat (not shown in the figure); two linear guide rails 15 are installed on a cross beam of the support 17 along the horizontal direction, and an execution end of the ultrasonic auxiliary hole making device is fixed on the linear guide rails 15 through the holding seat and the sliding block to realize horizontal sliding. The whole special tool is fixed on the jig drilling plate 10 through a positioning pin hole and a bolt connecting hole on a bottom plate of the support 17. Two groups of positioning pin holes and bolt connecting holes are processed on a bottom plate of the support 17, a series of positioning pin holes are arranged on the side surfaces of a support beam and the holding seat, the positioning pin holes correspond to the positions of holes to be processed in the horizontal direction one by one, the position of the portable ultrasonic auxiliary hole making execution end 16 on the guide rail 15 is adjusted, and accurate positioning is realized through the positioning pins.
The use of the jig drill plate 10 ensures high positional accuracy between the holes. And a positioning pin hole and a bolt connecting hole for fixing a special tool are pre-processed on the jig drilling plate 10 corresponding to the position of the triangular support plate 11. The special tool is fixed on the jig drilling plate 10, and the position precision of the special tool relative to the jig drilling plate 10 is ensured through the positioning pin hole and the bolt connecting hole in the bottom plate of the support. Two groups of positioning pin holes and bolt connecting holes on the bottom plate of the bracket respectively correspond to the positions of two rows of holes on the triangular support plate 11. Positioning pin holes in the side faces of the holding seat and the support beam correspond to the holes in the horizontal direction one by one, the position of the portable ultrasonic auxiliary hole making execution end on the guide rail is adjusted, and accurate positioning is achieved through the positioning pins. As shown in fig. 6.
After the position of the fixed jig drilling plate 10 is adjusted, the special tool is fixed on the position, corresponding to the hole to be processed, of the drilling template through a positioning pin hole and a bolt connecting hole in the support bottom plate, the position of the portable ultrasonic auxiliary hole making execution end 16 on the guide rail is adjusted, and positioning and locking are completed through a positioning pin. And starting the portable ultrasonic auxiliary hole making execution end 16, and finishing the processing of the hole from top to bottom according to preset processing parameters. And then adjusting the position of the portable ultrasonic auxiliary hole making execution end 16 on the guide rail 15 to the next hole to be processed, completing positioning and locking through a positioning pin, and starting the processing of the hole. After the 6 rows of holes are machined, the position of the special tool is adjusted, the special tool is positioned and locked by using the other group of positioning pin holes on the bottom plate of the support, and then the machining action is repeated to complete the machining of the second row of holes.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the invention, so that any modifications, equivalents, improvements and the like, which are within the spirit and principle of the present invention, should be included in the scope of the present invention.
Claims (7)
1. A rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method is characterized by comprising the following steps: the main shaft rotating speed of the ultrasonic vibration hole making device is 3000-4000 r/min, the feeding speed is 20-40 mm/min, the tool hanging length is 35-40mm, and the ultrasonic vibration frequency is 20-30 kHz.
2. The rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method according to claim 1, characterized in that: the processing hole is a radial hole formed by connecting the cabin section triangular supporting plate with a rivet of the cabin section or an axial hole formed by connecting the cabin section triangular supporting plate with a bolt of the instrument mounting plate; the cabin section is made of aluminum alloy materials, and the triangular supporting plate is made of carbon fiber composite materials.
3. The rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method according to claim 1, characterized in that: the cutter is a hard alloy drill bit.
4. The rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method according to claim 1, characterized in that: when the hanging length of the cutter is 35mm, the corresponding ultrasonic frequency is 27.1 KHz; when the hanging length of the cutter is 40mm, the corresponding ultrasonic frequency is 26.4 KHz.
5. The rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method according to claim 1, characterized in that: when a radial hole is machined, a special tool for the radial hole is used, wherein the special tool for the radial hole comprises a support, a guide rail, a sliding block and a holding seat; two linear guide rails are arranged on a vertical plate of the support along the vertical direction, and an execution end of the ultrasonic auxiliary hole making device is fixed on the linear guide rails through a holding seat and a sliding block to realize vertical sliding.
6. The rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method according to claim 1, characterized in that: when an axial hole is machined, a special tool for the axial hole is used, wherein the special tool for the axial hole comprises a support, a guide rail, a sliding block and an embracing seat; two linear guide rails are installed on a cross beam of the support along the horizontal direction, and an execution end of the ultrasonic auxiliary hole making device is fixed on the linear guide rails through the holding seat and the sliding block to realize horizontal sliding.
7. The rocket cabin CFRP supporting plate ultrasonic-assisted hole making process method of claim 5 or 6, wherein: according to the position of the triangular support plate, correspondingly processing the position of a special tool for fixing a radial hole or an axial hole on the outer edge of the fixture platform, wherein the position corresponds to the position of a hole to be processed; before processing, firstly, positioning and clamping a triangular support plate and a cabin section by using the existing drill plate; and fixing a special tool for the radial hole or the axial hole on the outer edge of the frame platform through a positioning pin hole and a bolt connecting hole on the bottom plate of the support, adjusting the position of the ultrasonic auxiliary hole making execution end on the guide rail, and realizing positioning and locking.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010957737.8A CN112170880B (en) | 2020-09-11 | 2020-09-11 | Ultrasonic auxiliary hole making process method for CFRP support plate of rocket cabin |
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| CN202010957737.8A CN112170880B (en) | 2020-09-11 | 2020-09-11 | Ultrasonic auxiliary hole making process method for CFRP support plate of rocket cabin |
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| CN112170880B CN112170880B (en) | 2023-07-14 |
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| CN109108317A (en) * | 2017-06-23 | 2019-01-01 | 河南理工大学 | Vibration drilling method suitable for CFRP/ titanium (aluminium) alloy stack material |
| CN109264027A (en) * | 2018-08-13 | 2019-01-25 | 北京蓝箭空间科技有限公司 | Blanking cover, cargo tank structure and the space launch vehicle of bay section for space launch vehicle |
| CN111085703A (en) * | 2019-12-25 | 2020-05-01 | 首都航天机械有限公司 | High-precision rapid hole making equipment and hole making method for metal shell structure |
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2020
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| US20080292860A1 (en) * | 2005-11-25 | 2008-11-27 | Hamamatsu Foundation For Science And Technology Promotion | Ultrasonic Vibration Cutting Method and a Fiber Reinforced Plastic Member Manufactured by the Method |
| CN101628346A (en) * | 2009-07-25 | 2010-01-20 | 大连理工大学 | Method for slowing down outlet speed of carbon fiber composite material hand-made hole and buffer device thereof |
| CN109108317A (en) * | 2017-06-23 | 2019-01-01 | 河南理工大学 | Vibration drilling method suitable for CFRP/ titanium (aluminium) alloy stack material |
| CN107262761A (en) * | 2017-06-27 | 2017-10-20 | 南京航空航天大学 | A kind of vibration drilling device and processing method |
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