CN114227008B - Ultrafast laser cutting method for carbon fiber composite material structure - Google Patents
Ultrafast laser cutting method for carbon fiber composite material structure Download PDFInfo
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- CN114227008B CN114227008B CN202111649755.0A CN202111649755A CN114227008B CN 114227008 B CN114227008 B CN 114227008B CN 202111649755 A CN202111649755 A CN 202111649755A CN 114227008 B CN114227008 B CN 114227008B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/36—Removing material
- B23K26/38—Removing material by boring or cutting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/08—Devices involving relative movement between laser beam and workpiece
- B23K26/082—Scanning systems, i.e. devices involving movement of the laser beam relative to the laser head
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/70—Auxiliary operations or equipment
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Abstract
The invention relates to an ultrafast laser cutting method for a carbon fiber composite material structure, which comprises the following steps of: s1, measuring and recording a plurality of single scribing and etching depths and a plurality of incident pulse energy fluxes of lasers corresponding to the single scribing and etching depths on a test piece, and fitting according to a proposed theoretical formula to obtain a material removal threshold flux and a characteristic absorption depth; s2, sequentially stacking a protective backing plate, a carbon fiber composite material, a pressing plate and a magnet on a bearing and moving platform of a laser processing system, wherein the pressing plate is made of a material with light transmittance more than or equal to 85% under the wavelength of laser; s3, setting the energy flux of the incident pulse, obtaining the corresponding single scribing etching depth according to a calculation formula, determining the machining scanning times, projecting remote laser to penetrate through the pressing plate and irradiating the carbon fiber composite material, and carrying out laser cutting. According to the method, through quantification related rules and the establishment of the clamping method, the high efficiency, the precision and the reliability in the ultra-fast laser cutting process can be considered.
Description
Technical Field
The invention relates to the field of high-performance processing of carbon fiber composite material structures, in particular to an ultrafast laser cutting method for a carbon fiber composite material structure.
Background
With the improvement of the lightweight design requirements of products in the fields of aerospace, aviation, rail transit, weaponry and the like, the conventional homogeneous metal materials, such as aluminum alloy, titanium alloy, conventional single ceramic, high polymer and other engineering materials are more and more difficult to meet the comprehensive requirements of all fields, and the fiber composite material becomes an ideal choice for manufacturing aerospace products due to the excellent comprehensive properties of low density, high rigidity, high thermal stability, fatigue resistance, strong designability and the like. Especially, the carbon fiber composite material thin-wall structure can be compounded with other light structures such as honeycomb structures to form a structure with excellent strength, rigidity and thermal expansibility, and is a non-two-junction selection meeting the requirements of a large-bearing and high-stability structure. For example, the three-layer structure of the most widely used "carbon fiber composite skin-honeycomb-carbon fiber composite skin" on satellites is widely used in structural panel products of space vehicles such as box-panel load cabins.
According to whether the layering is symmetrical, the carbon fiber composite material thin-wall structure presents a plane state or a curled state in a natural state; in use, the carbon fiber composite material thin-wall structure is usually required to be subjected to material reduction processing such as trimming, perforating and the like. The existing machining generally adopts mechanical contact machining modes such as milling, grinding wheel grinding cutting, drilling, stamping and the like. But the characteristics of the carbon fiber composite material, such as light weight, hardness, brittleness and high modulus, bring excellent mechanical properties to the product, and simultaneously bring the problems of large damage scale, multiple tool consumables, complex clamping process, low production efficiency, increased cost and the like to the material reduction processing of the product. In the existing contact processing method, the processing can be implemented only by covering the blank to be processed through a constant-width metal drill die or covering the blank to be processed through a constant-width nonmetal cover plate. For the breadth metal drilling jig, once the preset processing structure is changed, the processing metal drilling jig needs to be complemented, even the processing metal drilling jig has to be abandoned due to the defect of the processing allowance of the drilling jig, the processing cost of the breadth metal drilling jig is higher, and the reusability and the flexibility are poor; the non-metal drilling jig is a disposable tool as a structure to be cut off together with a processed workpiece. In the clamping process, because the materials are easy to absorb moisture and expand, the existing processing mode generally adopts a dry cutting method to process the three-layer structure of the pressing plate-carbon fiber composite material-protective backing plate, and the problems of large resistance to cutting tools, easy abrasion of cutters and the like are easily caused due to strong mechanical properties of the composite material, and if a reliable clamping means is not adopted, horizontal sliding of the carbon fiber composite material, interlayer separation of the three-layer structure during cutter lifting and the like are caused; for the processing structure, the problems of position deviation of the processing structure such as hole sites or damage of the edge of the structure and the like are easily caused. The reliable clamping method based on mechanical tool positioning brings the problems of overlong clamping time and low efficiency. In the aspect of cutting damage, the carbon fiber composite material belongs to a laminated structure with high strength and high hardness, and the existing contact processing mode is extremely easy to cause quality problems such as surface wire drawing, layering and the like, so that the precision and mechanical properties of the product are affected. If the non-contact processing method is changed, for example, laser scanning galvanometer reciprocating etching cutting, in the prior art, both reliability and efficient processing cannot be achieved in the cutting process. If the cutting times are insufficient, the material cannot be cut through, so that the material to be removed is difficult to fall off, and a preset structure cannot be formed; if the cutting times are enough, the cutting can be ensured, but the time is wasted and the protective backing plate under the skin is easily damaged.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the cutting method for the carbon fiber composite thin-wall structure, which has the advantages of quick clamping and clamping removing processes, quantitative and reliable cutting times and low cutting damage.
The invention provides an ultrafast laser cutting method for a carbon fiber composite material structure, which comprises the following steps:
s1, measuring and recording a plurality of incident pulse energy fluxes F and corresponding single scribing etching depths d on a test piece of the same material as the carbon fiber composite material, thereby fitting and obtaining a material removal threshold flux F th And a characteristic absorption depth d 0 Setting an initial spot overlap ratio O of the laser processing system 1 Is in the range of [0.96,0.99 ]]；
S2, sequentially stacking a protective backing plate, the carbon fiber composite material, a pressing plate and a magnet on a bearing and moving platform of a laser processing system, wherein the pressing plate is made of a material with light transmittance of more than or equal to 85% at the wavelength of a laser processing beam;
s3, setting pulse energy flux F of the laser processing system, which is incident to the surface of the workpiece to be processed, according to the removal threshold flux F th Depth of feature absorption d 0 Obtaining a corresponding single scribing etching depth d, and determining the processing scanning times N according to the ratio relation of the thickness DD of the carbon fiber composite material and the single scribing etching depth d 1 And remotely projecting the laser processing light beam to penetrate through the pressing plate and irradiate the carbon fiber composite material, and cutting the carbon fiber composite material by laser.
In the concept of the present invention, the steps S1 and S2 may be performed simultaneously without any sequence, and are performed before the step S3.
The invention provides an ultrafast laser cutting method for a carbon fiber composite material structure, which is a non-contact processing method for remote laser processing by using a scanning galvanometer and the like. In the conception of the invention, a non-contact stress clamping mode matched with the pressing and mounting of the magnetic adsorption pressurizing plate is used, and ultra-fast laser processing is utilized to quantitatively process the thin-wall type carbon fiber composite material of the laminated structure. The light transmittance of the pressing plate under the laser processing beam is more than or equal to 85%, so that the incident pulse energy of the laser processing beam in a remote laser mode can be effectively acted on the carbon fiber composite material, and the reliability of the fitting result in the step S1 is further ensured.
In the invention, the reliable clamping of the carbon fiber composite material is realized only by the transparent pressing plate with the planar one side and the contour-height synapse array structure on the other side and a small amount of magnets; for small-sized flat blanks, the transparent pressing plate can be omitted. The clamping process is greatly simplified, and the requirement on clamping stress is reduced. In addition, the non-contact processing characteristic avoids the defects of force-induced delamination, surface tearing, edge breakage and the like of the carbon fiber composite material in the processing, and is an efficient and precise clamping and cutting method.
In accordance with one aspect of the present invention,
the step S1 is performed before the step S3, and in the step S1, a plurality of single scribing etching depths d and a plurality of incident pulse energy fluxes F of the corresponding laser processing beams are measured and recorded on the test piece, and the absorption feature depth d is calculated by fitting a relation 0 And removing the threshold flux F th Setting the range of the spot overlapping rate O of the laser processing system as [0.96,0.99 ]]；
Step S2 is implemented before step S3, in step S2, the protective pad is laid on a bearing and moving platform with ferromagnetism, the carbon fiber composite material is laid on the protective pad, the pressing plate is laid on the carbon fiber composite material, wherein the convex contact part on one side of the pressing plate is pressed on the carbon fiber composite material, a magnet is placed on the other side of the pressing plate, and the protective pad, the carbon fiber composite material and the pressing plate are firmly adsorbed on the bearing and moving platform;
in step S3, the pulse energy flux F of the laser processing system incident on the surface of the workpiece is set by the absorption feature depth d 0 And removing the threshold flux F th Determining a single process etching depth d which can be removed by each scanning process, and further determining the cuttingAt least the number of processing scans N required to penetrate the carbon fiber composite material 1 ；
Maintaining the overlap rate O of processing light spots 2 Unchanged, by the processing scanning times N 1 Cutting the carbon fiber composite material using the laser processing beam, wherein the processing spot overlap ratio O 2 The value range is [0.2,0.95 ]]。
The laser cutting method for the carbon fiber composite material provided by the invention is a machining method with good flexibility and reusability of a machining tool. The invention provides a pressing plate tool made of transparent materials with a synaptic part, which can remove materials only in a focusing area by utilizing laser processing, and the energy field can mostly penetrate through the transparent pressing plate without damaging the characteristics of the pressing plate, so that the repeated reusability of the pressing plate is realized. Therefore, the processing and clamping preparation process flow is effectively shortened, and the effects of good flexibility, reusability and great reduction of the consumable cost of the tool are realized.
In accordance with one aspect of the present invention,
in steps S1 and S3, the pulse width of the laser processing beam is less than or equal to 20ps.
In accordance with one aspect of the present invention,
in the steps S1 and S3, the spot overlapping ratio O is calculated according to the following formula:
O＝1-v/Df
wherein v is the scanning speed of the laser beam used, and D is "1/e" of the laser beam used 2 The "type-defined spot diameter" is equivalent to another type of definition, for example, the "1/e" type, and is converted according to physical meaning, and f is the pulse frequency of the laser used.
In accordance with one aspect of the present invention,
one side of the pressing plate is a plane, and the height of the equal-height convex contact part arranged on the other side is more than or equal to 10 times of the Rayleigh length of the laser processing beam; the convex contact part of the pressing plate is provided with a planar bottom, the convex contact diameter is in the range of 0.3mm-3mm, and the pressing plate is made of high polymer materials.
In the concept of the present invention, the shape of the protruding contact part is not limited and may be a cylinder shape or a truncated cone shape.
Preferably, in the concept of the present invention, the height of the bump is 10 times the rayleigh length of the laser processing beam. If the synapse height is too small, the lower surface of the platen may be in the region of the length of the rake Li Ruili near the beam waist, which may be prone to damage to the platen, and may be detrimental to debris removal.
In accordance with one aspect of the present invention,
in the step S1, a relationship between the single scribing etching depth d and the energy flux F of different incident pulses is measured, and the fitting relationship is:
d(F)＝(4/3)/(1-O)×d 0 ×ln(F/F th ) 3/2 ，
wherein d is the etching depth of the single scribing, F is the energy flux of the incident pulse, d 0 Is the absorption feature depth F th Is the removal threshold flux, O is the spot overlap ratio.
In accordance with one aspect of the present invention,
in the step S3, the thickness DD of the carbon fiber composite material, the single-pass etching depth d, and the number of processing scans N 1 Has the following relationship:
N 1 ＝(1.2-1.4)×(DD/d)，
wherein DD is the thickness of the carbon fiber composite material, d is the single processing etching depth,
the single process etching depth d is calculated from the fitting relation,
d＝(4/3)/(1-O)×d 0 ×ln(F/F th ) 3/2
wherein O is the light spot overlapping rate, d 0 Is the depth of absorption feature, F th Is the removal threshold flux and F is the pulse energy flux incident on the surface of the workpiece to be machined.
In the processing of the invention, firstly, the incident pulse energy flux F of the laser processing system is set, namely the relation d= (4/3)/(1-O) x d can be used 0 ×ln(F/F th ) 3/2 Obtaining a corresponding single scribing etching depth d, and determining the adding according to the thickness of the carbon fiber composite materialNumber of times of work scan N 1 I.e. by N 1 The machining scanning times N are calculated by the method of the combination of the components of the machine tool with the frequency of the machining scanning, namely, the frequency of the machining scanning, namely 1 And then, projecting a remote laser to penetrate through the pressing plate and irradiate the carbon fiber composite material to perform laser cutting. The safety factor is set to be 1.2-1.4, so that the etching processing scanning times N are ensured when laser acts on the interface profile of the processing structure to be processed at the bottom of the synaptic part 1 After that, complete cutting can be achieved.
In accordance with one aspect of the present invention,
the protective backing plate is made of a material with the laser energy reflectivity less than 20% and the damage threshold more than or equal to 3 times of the threshold of the carbon fiber composite material.
The protective backing plate with smaller reflectivity and higher damage threshold can effectively protect the bearing and moving platform of the laser processing system, is not easy to damage, and has higher recycling rate.
In accordance with one aspect of the present invention,
the thickness of the carbon fiber composite material is less than or equal to 3.0mm, and the carbon fiber composite material is curled or planar in a free state and can be flattened in an elastic deformation range;
specifically, the method of the invention can be used for processing the coiled and flat thin-wall carbon fiber composite material, a pressing plate is needed when the coiled carbon fiber composite material and the large-breadth and flat carbon fiber composite material are processed, and only a magnet can be used when the small-breadth and flat carbon fiber composite material is processed.
In accordance with one aspect of the present invention,
the magnets are permanent magnets and soft magnets.
The invention has the following beneficial effects: the laser cutting method provided by the invention provides the necessary cutting times for the carbon fiber composite material with high hardness and difficult processing and with the thickness of less than 3mm, and realizes the combination of processing reliability and high efficiency.
The laser cutting method provided by the invention aims at a carbon fiber composite material thin-wall structure, is a method for realizing quantification of key cutting processes without processing contact stress and capable of rapidly clamping and removing, and can realize cutting effects with high efficiency, low cost and high quality.
The ultrafast laser cutting method for the carbon fiber composite material structure provided by the invention is a method which is reliable in principle, small in calculated amount and capable of considering processing reliability and efficiency. By quantifying the correlation law, both reliability and efficiency in the cutting process can be considered. The etching depth of each pass of the performance is deduced according to the linear absorption law of the carbon fiber composite material, and the necessary times for cutting through the carbon fiber composite are quantized, so that reliable cutting through is guaranteed, cutting through is avoided due to the fact that cutting through is guaranteed, invalid processing time is effectively avoided, the protective backing plate is damaged, and the increase of processing cost is avoided.
Drawings
FIG. 1 is a flow chart of an ultrafast laser cutting method for carbon fiber composite structures in one embodiment of the present invention.
Fig. 2 is a schematic diagram of a laser processing system in accordance with the present invention.
Figure number: 1-laser processing a beam; 2-magnet; 3-pressing plates; 4-carbon fiber composite material; 5-a protective backing plate; 6-a bearing and moving platform;
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
The machining structure in the present specification refers to a structural element having a geometric shape, which is to be etched and cut back and forth by laser machining, for example: simple structures such as round holes, oblong holes and the like and special-shaped structures such as patterning inside the outer contour boundary of the whole workpiece.
According to the method for ultrafast laser cutting of a carbon fiber composite structure in one embodiment of the present invention, as shown in fig. 1, the steps are as follows:
s1, measuring and recording a plurality of incident pulse energy fluxes F and corresponding single scribing etching depths d on a test piece of the same material as the carbon fiber composite material, thereby fitting and obtaining a material removal threshold flux F th And a characteristic absorption depth d 0 Setting an initial spot overlapping rate O of a laser processing system 1 Is in the range of [0.96,0.99 ]]；
S2, sequentially stacking a protective backing plate 5, a carbon fiber composite material 4, a pressing plate 3 and a magnet 2 on a bearing and moving platform 6 of a laser processing system, wherein the pressing plate 3 is made of a material with light transmittance more than or equal to 85% under the wavelength of a laser processing beam 1;
s3, setting pulse energy flux F of the laser processing system, which is incident to the surface of the workpiece to be processed, according to the removal threshold flux F th Depth of feature absorption d 0 And a calculation formula to obtain a corresponding single scribing etching depth d, and determining the processing scanning times N according to the thickness DD of the carbon fiber composite material 4 1 The remote projection laser processing beam 1 penetrates through the pressing plate 3 and irradiates the carbon fiber composite material 4, and the laser cuts the processing structure of the carbon fiber composite material 4.
The ultrafast laser cutting method for the carbon fiber composite material structure provided by the embodiment is a non-contact processing method by utilizing remote laser processing such as scanning galvanometer and the like. In this embodiment, the ultra-fast laser processing is used to quantitatively process the thin-walled carbon fiber composite material 4 of the laminated structure by using a non-contact stress clamping method in which the additional pressing plate 3 is pressed and assembled by the magnetic force of the magnet 2. The transmittance of the pressing plate 3 under the laser processing beam 1 is more than or equal to 85%, so that the incident pulse energy of the laser structure beam 1 under the remote laser mode can be effectively acted on the carbon fiber composite material 4, and the reliability laser of the fitting result in the step S1 is further ensured. Specifically, the remote laser is set up in satisfying the present embodimentInitial spot overlap ratio O of laser processing beam 1 of processing method 1 Is in the range of [0.96,0.99 ]]And the pressure plate 3 is made of a material with a light transmittance of more than or equal to 85% at the wavelength of the laser processing beam 1, it can be considered that the relationship between the incident pulse energy flux acting on the carbon fiber composite material 4 and the single etching depth generated on the carbon fiber composite material still shows an original processing flux.
In the embodiment, the reliable clamping of the carbon fiber composite material 4 is realized only by the pressing plate 3 with the planar one side and the contour synapse array structure other side and a small amount of magnets 2; for small-sized flat blanks, the above-mentioned press plate 3 can also be omitted. The clamping process is greatly simplified, and the requirement on clamping stress is reduced. In addition, the characteristics of non-contact processing avoid the defects of force-induced delamination, surface tearing, edge breakage and the like of the carbon fiber composite material 4 in the processing.
In the present embodiment of the present invention, in the present embodiment,
in step S1, the incident pulse energy flux F and the corresponding single scribing etching depth d in the laser beam 1 are measured and recorded on the test piece, and the material removal threshold flux F is obtained by fitting according to the proposed theoretical formula th And a characteristic absorption depth d 0 Setting an initial spot overlapping rate O of a laser processing system 1 Is in the range of [0.96,0.99 ]]；
Step S2 is performed before and after step S3, in step S2, the protective pad 5 is laid on the carrying and moving platform 6 with ferromagnetism, the carbon fiber composite material 4 is laid on the protective pad 5, the pressing plate 3 is laid on the carbon fiber composite material 4, wherein the convex contact part on one side of the pressing plate 3 is pressed on the carbon fiber composite material 4, the magnet 2 is placed on the other side of the pressing plate 3, and the protective pad 5, the carbon fiber composite material 4 and the pressing plate 3 are firmly adsorbed on the carrying and moving platform 6;
in step S3, the pulse energy flux F of the laser processing system incident on the surface of the workpiece is set and passes through the absorption feature depth d 0 And removing the threshold flux F th The depth d of the single process etch removable per scan process can be determined and further the cut-through carbon fiber composite 4 can be determinedAt least the required number of processing scans N 1 ；
Maintaining the overlap rate O of processing light spots 2 Unchanged, by the number of processing scans N 1 Cutting a processed structure of the carbon fiber composite material 4 using the laser processing beam 1, wherein a processing light spot overlapping rate O 2 The value range is [0.2,0.95 ]]。
The laser cutting method for the carbon fiber composite material provided by the embodiment is a machining method with good flexibility of a machining tool and reusability. The present embodiment provides a platen 3 made of transparent material with a synapse, and uses laser processing to remove material only in the focal region, and the energy field can mostly penetrate the platen 3 without damaging the platen 3, thereby achieving multiple reusability of the platen 3. Therefore, the processing and clamping preparation process flow is effectively shortened, and the effects of good flexibility, reusability and great reduction of the consumable cost of the tool are realized.
In the present embodiment of the present invention, in the present embodiment,
in steps S1 and S3, the pulse width of the laser processing beam 1 is 20ps or less.
In the present embodiment of the present invention, in the present embodiment,
in steps S1 and S3, the spot overlap ratio O is calculated according to the following formula:
O＝1-v/Df
wherein v is the scanning speed of the laser beam used, and D is "1/e" of the laser beam used 2 The "type-defined spot diameter" is equivalent to another type of definition, for example, the "1/e" type, and is converted according to physical meaning, and f is the pulse frequency of the laser used.
In the present embodiment of the present invention, in the present embodiment,
one side of the pressing plate 3 is a plane, and the height of the equal-height convex contact part arranged on the other side is more than or equal to 10 times of the Rayleigh length of the laser processing beam 1; the convex contact part of the pressing plate 3 is provided with a plane bottom, the diameter of the convex contact part ranges from 0.3mm to 3mm, and the pressing plate 3 is made of high polymer materials.
In this embodiment, the shape of the protruding contact is cylindrical. The bottom of the synapse is provided with a flat surface in contact with the carbon fiber composite material 4. The plane is arranged to increase the contact area between the synapse part and the carbon fiber composite material 4, prevent the carbon fiber composite material 4 from being scratched, and also prevent the surface of the carbon fiber composite material 4 from scratching the pressing plate 3, because the scratching of the pressing plate 3 can cause the reduction of the light transmittance of the pressing plate 3, and reduce the recycling rate of the pressing plate 3.
In this embodiment, the height of the protruding contact portion is greater than 4mm, which makes the distance between the lower surface of the planar portion of the pressing plate 3 and the carbon fiber composite material 4 not too small, so that not only can good chip removal be ensured, but also the lower surface of the planar portion of the pressing plate 3 can be prevented from being ablated by laser: if the synapse height is too small, the lower surface of the platen may also be in the region of the length of the target Li Ruili near the beam waist, thereby being vulnerable to damage.
In the present embodiment of the present invention, in the present embodiment,
in step S1, the relationship between the single scribe etching depth d and the energy flux F of different incident pulses is measured, and the fitting relationship is:
d(F)＝(4/3)/(1-O)×d 0 ×ln(F/F th ) 3/2 ，
wherein d is the etching depth of the single scribing, F is the energy flux of the incident pulse, d 0 Is the absorption feature depth F th Is the removal threshold flux, O is the spot overlap ratio.
In the present embodiment of the present invention, in the present embodiment,
in step S3, the carbon fiber composite material thickness DD has the following relationship with the single process etching depth d and the process scanning number N1:
N1＝(1.2-1.4)×(DD/d)，
wherein DD is the thickness of the carbon fiber composite material, d is the single processing etching depth,
the single process etch depth d is calculated from a fitting relationship,
d＝(4/3)/(1-O)×d 0 ×ln(F/F th ) 3/2
wherein O is the light spot overlapping rate, d 0 Is the depth of absorption feature, F th Is the removal threshold flux and F is the pulse energy flux incident on the surface of the workpiece to be machined.
In the processing of the embodiment, firstly, pulse energy flux of the laser processing system incident on the surface of the workpiece is setThe amount F is obtained by the relation d= (4/3)/(1-O). Times.d of the test piece 0 ×ln(F/F th ) 3/2 Obtaining a corresponding single scribing etching depth d, and determining the processing scanning times N according to the thickness of the carbon fiber composite material 1 I.e. by N 1 The machining scanning times N are calculated by the method of the combination of the components of the machine tool with the frequency of the machining scanning, namely, the frequency of the machining scanning, namely 1 A remote laser is then projected through the platen 3 and irradiated to the carbon fiber composite 4 for laser cutting. The safety factor is set to be 1.2-1.4, so that the etching processing scanning times N are ensured when laser acts on the interface profile of the processing structure to be processed at the bottom of the synaptic part 1 After that, complete cutting can be achieved.
In the present embodiment of the present invention, in the present embodiment,
the protective backing plate 5 is made of a material with the laser energy reflectivity less than 20% and the damage threshold more than or equal to 3 times of the threshold of the carbon fiber composite material 4.
The protective pad 5 with smaller reflectivity and higher damage threshold can effectively protect the bearing and moving platform 6 of the laser processing system, is not easy to damage, and has higher recycling rate.
In the present embodiment of the present invention, in the present embodiment,
the thickness of the carbon fiber composite material 4 is less than or equal to 3.0mm, the carbon fiber composite material 4 is curled or planar in a free state, and can be flattened in an elastic deformation range;
the protective backing plate 5 is an asbestos rubber plate or an asbestos latex plate.
In the present embodiment of the present invention, in the present embodiment,
the pressing plate 3 is made of polymethyl methacrylate;
the magnet 2 is a rare earth permanent magnet;
the laser cutting method provided by the embodiment provides the necessary cutting times for the carbon fiber composite material 4 with high hardness and difficult processing and with the thickness of less than 3mm, and realizes the combination of processing reliability and high efficiency.
The laser cutting method provided by the embodiment aims at the carbon fiber composite material thin-wall structure, is a method which can realize no processing contact stress, can rapidly clamp and remove clamping and cut key process quantification, and can realize high-efficiency, low-cost and high-quality cutting effects.
The ultrafast laser cutting method for the carbon fiber composite material structure is reliable in principle, small in calculated amount and capable of achieving machining reliability and efficiency. By quantifying the correlation law, both reliability and efficiency in the cutting process can be considered. The etching depth of each pass of the performance is deduced according to the linear absorption law of the carbon fiber composite material, and the necessary times for cutting through the carbon fiber composite are quantized, so that reliable cutting through is guaranteed, cutting through is avoided due to the fact that cutting through is guaranteed, invalid processing time is effectively avoided, the protective backing plate 5 is damaged, and the increase of processing cost is avoided.
In another embodiment of the invention, an ultrafast laser cutting method for carbon fiber composite structures, comprises the steps of:
s1, selecting a test piece with the same parameters as the carbon fiber composite material 4 and the thickness of 0.40mm, measuring the relation of the single scribing etching depth d along with different incident pulse energy fluxes F, and calculating a formula d (F) = (4/3)/(1-O) x d 0 ×ln(F/F th ) 3/2 Fitting to obtain the depth d of the absorption characteristic 0 And removing the threshold flux F th Wherein O is [0.96,0.99 ]]A certain value of the interval, here chosen to be 0.97.
The carbon fiber composite material 4 in this embodiment has a crimped structure. The carbon fiber composite material 4 comprises the components of M55/BS-4 and has the thickness of 0.40mm. The processing laser is a Gaussian pulse sequence with a center wavelength of 1064nm and a single pulse duration of 12ps, and is remotely transmitted through a scanning galvanometer processing system, and a spot diameter of D=23+/-1 mu m is generated on the surface of a material after being focused through a flat field lens. Fitting formula d (F) = (4/3)/(1-O) ×d 0 ×ln(F/F th ) 3/2 At the time, 5 incident pulse energy fluxes are selected, namely F= 2.4,3.3,6.1,8.2, 15.0J/cm 2 . Since the scanning speed v=0.7 m/s, the spot diameter d=23±1 μm, and the pulse frequency f=1.0 MHz of the laser processing beam for single scribing etching, the initial spot overlap ratio O 1 =1-v/df≡0.97. This effectively degenerates the fitting equation to d (F) = (4/3)/(1-O) x d 0 ×ln(F/F th ) 3/2 ＝43.8×d 0 ×ln(F/F th ) 3/2 . Fitting by using Origin software to obtain the most probable fitting value to remove the threshold flux F th ＝1.39±0.010J/cm 2 Depth of absorption feature d 0 =243±5nm. It should be noted that, in this embodiment, a single scribe etching method is adopted, which is approximately equivalent to n=1/(1-O) ≡33 pulses when in the in-situ tapping method. According to the well-known processing threshold hatching effect, at 30-50 in-situ tap pulses, the processing threshold of the material, while not saturated, is typically the lowest of the processing thresholds at the in-situ tap of hundreds to thousands of pulses, but has tended to approach the saturation. Thus, although the processing threshold corresponding to several tens of pulses is measured in the present embodiment, it may already approximately represent the threshold when processing in situ by several hundred or even thousands of pulses, which is a necessary condition for achieving cutting by the reciprocating etching later. This results in a removal threshold flux F as determined herein th ＝1.39±0.010J/cm 2 Depth of absorption feature d 0 The product =243±5nm can be used in the calculation formula used in the subsequent determination of the machining scan number N1 without causing significant errors.
As shown in the figure 2 of the drawings,
s2, a planar protection backing plate 5 made of asbestos rubber plates with thickness uniformity meeting requirements is flatly paved on a ferromagnetic bearing and moving platform 6, one surface of a carbon fiber composite material 4 is attached to the upper surface of the protection backing plate 5, one side of a pressing plate 3 with an isosynaptic part is used for pressing the carbon fiber composite material 4, then a plurality of magnets 2 are distributed on the other side of the pressing plate 3, namely, the facing surface of laser is provided, and no interface of a processing structure exists under the pressing plate 3 at the distribution position.
The protective pad 5 of the plane used has a thickness tolerance of 0.05mm, in particular, this thickness uniformity ensures that the flatness of the thin-walled workpiece 4 to be processed, which is subsequently spread on the protective pad 5, is not affected.
The pressing plate 3 is formed by compression molding and is made of polymethyl methacrylate, namely organic glass acrylic. The organic glass acrylic has the transparency similar to that of glass, is not easy to crack due to good shock resistance, has higher surface hardness and has wear resistance similar to that of aluminum materials; the organic glass acrylic has good plastic forming performance and mechanical cutting performance, and has smooth surface, thus being one of ideal materials for the pressing plate 3. Before use, in order to ensure good transmittance, all contaminants such as dust on the outer surface of the pressing plate 3 need to be wiped. The pressing plate 3 of the organic glass acrylic can be integrally processed by a mechanical cutting mode or formed by molding and shaping.
S3, projecting a remote laser processing beam 1 to penetrate through the pressing plate 3, irradiating the processing area of the processed workpiece 4, and determining a single processing etching depth d and a processing scanning frequency N required by cutting through according to a calculation formula 1 . In the embodiment, the carbon fiber composite material 4 is larger than 1m multiplied by 1m, and the range of the scanning processing system used for projecting the remote laser 1 is far larger than 10cm 2 Therefore, the processing structure interface of the processed workpiece 4 is correspondingly processed through the mode of 'reciprocating etching and block splicing'.
Specifically, the beam scanning speed v=10.0 m/s, the spot diameter d=23±1 μm, and the pulse frequency f=1.0 MHz are adopted, and it is known that the processing spot overlap ratio o=1-v/df≡ 0.5652, the pulse energy flux f=15.0J/cm incident on the surface of the workpiece to be processed 2 The processing parameters of (2) can obtain the single processing etching depth d= (4/3)/(1-O) x d 0 ×ln(F/F th ) 3/2 =2.73 μm. Therefore, in order to cut through the carbon fiber composite material 4 having the carbon fiber composite material thickness d=0.4 mm, it is theoretically necessary to etch 147 times in situ to cut through. In practice, in order to precisely cut time, the number of times of etching is not wasted, and the obtained theoretical minimum number of times is multiplied by a safety coefficient of 1.2-1.4. In practice, if one wants to etch N reciprocally in situ only 1 The cutting is realized for 176-205 times by = (1.2-1.4) × (D/D) = 176-205 times, so that a large light spot is required, and the laser has the characteristic of large focal depth, or N is required to be etched by multiple tangent lines in parallel, namely by parallel cutting along each track line 1 The cutting-through can be realized by increasing the cutting-through width for the second time.
The foregoing is merely exemplary of embodiments of the invention and, as regards devices and arrangements not explicitly described in this disclosure, it should be understood that this can be done by general purpose devices and methods known in the art.
The above is only one embodiment of the present invention, and is not limited thereto, and various modifications and variations of the present invention will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. An ultrafast laser cutting method for a carbon fiber composite material structure is characterized by comprising the following steps:
s1, measuring and recording a plurality of incident pulse energy fluxes F and corresponding single scribing etching depths d on a test piece of the same material as the carbon fiber composite material (4), and fitting to obtain a removal threshold flux F th And a characteristic absorption depth d 0 Setting an initial spot overlap ratio O of the laser processing system 1 Is in the range of [0.96,0.99 ]]；
S2, sequentially stacking a protective backing plate (5), the carbon fiber composite material (4), a pressing plate (3) and a magnet (2) on a bearing and moving platform (6) of a laser processing system, wherein the pressing plate (3) is made of a material with light transmittance of more than or equal to 85% under the wavelength of a laser processing light beam (1);
s3, setting the pulse energy flux F of the laser processing system incident to the surface of the workpiece to be processed, and removing the threshold flux F according to the pulse energy flux F th Depth of feature absorption d 0 Obtaining a corresponding single scribing etching depth d, and determining the processing scanning times N according to the ratio relation of the thickness DD of the carbon fiber composite material and the single scribing etching depth d 1 Remotely projecting the laser processing light beam (1) to penetrate through the pressing plate (3) and irradiate the carbon fiber composite material (4), and cutting the carbon fiber composite material (4) by laser;
the height of the contour convex contact part arranged on one side of the pressing plate (3) is more than or equal to 10 times of the Rayleigh length of the laser processing beam (1), wherein the convex contact part of the pressing plate (3) is provided with a bottom of the plane, the diameter range of the convex contact part is 0.3mm-3mm, and the pressing plate (3) is made of a high polymer material;
in the step S1, a relationship between the single scribing etching depth d and different incident pulse energy fluxes F is measured, and the fitted relationship is:
d(F)=(4/3)/(1-O)×d 0 ×ln(F/F th ) 3/2 ，
wherein d is the etching depth of the single scribing, F is the energy flux of the incident pulse, d 0 Is the depth of absorption feature, F th Is the removal threshold flux, O is the spot overlap ratio;
in the step S3, the thickness DD of the carbon fiber composite material, the single processing etching depth d and the processing scanning times N are calculated 1 Has the following relationship:
N 1 = (1.2-1.4) x (DD/d), where DD is the carbon fiber composite thickness, d is the single process etch depth,
the single process etch depth d is calculated from the fitted relation,
d=(4/3)/(1-O)×d 0 ×ln(F/F th ) 3/2 wherein O is the light spot overlapping rate, d 0 Is the depth of absorption feature, F th Is the removal threshold flux and F is the pulse energy flux incident on the surface of the workpiece to be machined.
2. The method for ultrafast laser cutting of carbon fiber composite structures, as recited in claim 1, wherein,
the step S1 is performed before the step S3, and in the step S1, a plurality of single scribing etching depths d and a plurality of incident pulse energy fluxes F of the corresponding laser processing light beam (1) are measured and recorded on the test piece, and the absorption characteristic depth d is calculated by fitting a relation 0 And removing the threshold flux F th Setting an initial spot overlapping rate O of the laser processing system 1 Is in the range of [0.96,0.99 ]]；
Step S2 is performed before step S3, in step S2, the protective pad (5) is tiled on a bearing and moving platform (6) with ferromagnetism, the carbon fiber composite material (4) is laid on the protective pad (5), the pressing plate (3) is laid on the carbon fiber composite material (4), wherein a convex contact part on one side of the pressing plate (3) is pressed on the carbon fiber composite material (4), a magnet (2) is placed on the other side of the pressing plate (3), and the protective pad (5), the carbon fiber composite material (4) and the pressing plate (3) are firmly adsorbed on the bearing and moving platform (6);
in step S3, the pulse energy flux F of the laser processing system, which is incident on the surface of the workpiece to be processed, is set by absorbing the characteristic depth d 0 And removing the threshold flux F th Determining a single process etch depth d removable per scan process and further determining at least a number of process scans N required to cut through the carbon fiber composite (4) 1 ；
Maintaining the overlap rate O of processing light spots 2 Unchanged, by the processing scanning times N 1 Cutting the carbon fiber composite material (4) using the laser processing beam (1), wherein the processing spot overlap ratio O 2 The value range is [0.2,0.95 ]]。
3. The method for ultrafast laser cutting of carbon fiber composite structures, as recited in claim 2, wherein,
in steps S1 and S3, the pulse width of the laser processing beam (1) is less than or equal to 20ps.
4. An ultrafast laser cutting method for carbon fiber composite structures, as recited in claim 3, wherein,
in the steps S1 and S3, the initial light spot overlapping rate O 1 And processing spot overlap ratio O 2 The light spot overlapping rate is 0, and the light spot overlapping rate is calculated according to the following formula:
O=1-v/Df
where v is the scanning speed of the laser beam used, D is the spot diameter of the laser beam used, and f is the pulse frequency of the laser beam used.
5. An ultrafast laser cutting method for carbon fiber composite structures, as recited in claim 3, wherein,
the protective backing plate (5) is made of a material with the laser energy reflectivity less than 20% and the damage threshold more than or equal to 3 times of the threshold of the carbon fiber composite material (4).
6. An ultrafast laser cutting method for carbon fiber composite structures, according to claim 3, wherein the thickness of the carbon fiber composite (4) is 3.0mm or less, the carbon fiber composite (4) being in a curled or planar shape in a free state and being capable of flattening in an elastic deformation range.
7. An ultrafast laser cutting method for carbon fiber composite structures, according to claim 3, wherein the magnets (2) are permanent magnets and soft magnets.
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