CN114227008A - 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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- CN114227008A CN114227008A CN202111649755.0A CN202111649755A CN114227008A CN 114227008 A CN114227008 A CN 114227008A CN 202111649755 A CN202111649755 A CN 202111649755A CN 114227008 A CN114227008 A CN 114227008A
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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 etching depths and a plurality of incident pulse energy fluxes of the laser corresponding to the single-scribing etching depths on the test piece, and fitting according to the provided theoretical formula to obtain a material removal threshold and a characteristic absorption depth; s2, sequentially stacking the protective base plate, the carbon fiber composite material, the pressing plate and the magnet on a bearing and moving platform of the laser processing system, wherein the pressing plate is made of a material with light transmittance of more than or equal to 85% under the wavelength of laser; and S3, setting the incident pulse energy flux, obtaining the corresponding single-time scribing etching depth according to a calculation formula, determining the processing scanning times, projecting remote laser to penetrate through the pressing plate and irradiate the carbon fiber composite material, and performing laser cutting. The method of the invention can give consideration to high efficiency, precision and reliability in the ultrafast laser cutting process by quantifying relevant rules and formulating a clamping method.
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 light-weight design requirements of products in the fields of aerospace, aviation, rail transit, weaponry and the like, the traditional homogeneous metal materials, such as aluminum alloy, titanium alloy, conventional single ceramic, high polymer and other engineering materials, are increasingly difficult to meet the comprehensive requirements of various 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 a honeycomb structure to form a structure with excellent strength, rigidity and thermal expansibility, and becomes a non-two-junction choice for meeting the requirements of large-load-bearing and high-stability structures. For example, the three-layer structure of carbon fiber composite skin-honeycomb-carbon fiber composite skin, which is the most widely used structure on satellites, is widely used in structural plate products of space vehicles such as boxboard type load-carrying cabins.
According to whether the layering is symmetrical or not, the carbon fiber composite thin-wall structure is in a plane state or a curled state in a natural state; in use, the carbon fiber composite thin-wall structure is generally required to be subjected to material reduction processing such as edge cutting and hole opening. The existing processing generally adopts mechanical contact processing modes such as milling, grinding and cutting by a grinding wheel, drilling, stamping and the like. However, the carbon fiber composite material has the characteristics of light weight, hardness, brittleness and high modulus, and brings the problems of large damage scale, more tool consumables, complex clamping process, low production efficiency, increased cost and the like for material reduction processing while bringing excellent mechanical properties to products. The existing contact processing method can be implemented only by manufacturing an equal-breadth metal drilling mold to cover the blank to be processed or manufacturing an equal-breadth non-metal cover plate to cover the blank to be processed. For the breadth metal drill jig, once the preset processing structure is changed, the metal drill jig needs to be added additionally or even has to be discarded due to the lack of the processing allowance of the drill jig, the processing cost of the breadth metal drill jig is higher, and the reusability and the flexibility are poor; the breadth nonmetal drill jig is a disposable tool as a structure which needs to be cut off together with a processed workpiece. In the clamping process, because the material is easy to absorb moisture and expand, the existing processing mode generally adopts a dry cutting method to process a three-layer structure of a pressing plate, a carbon fiber composite material and a protective base plate, and because the mechanical property of the composite material is strong, adverse effects such as large resistance to cutting, easy abrasion of a cutter and the like are easily caused, if a reliable clamping means is not adopted, the problems of horizontal slippage of the carbon fiber composite material, interlayer separation of the three-layer structure and the like are caused; for a processing structure, the problems of position deviation of the processing structure such as hole position or structural edge damage are easily caused. The reliable clamping method depending on the positioning of the mechanical tool brings about the problems of overlong clamping time and low efficiency. In the aspect of cutting damage, because the carbon fiber composite material is a high-strength high-hardness laminated structure, the existing contact type processing mode easily causes quality problems of surface wire drawing, layering and the like, thereby influencing the precision and mechanical property of the product. If a non-contact processing method is adopted, for example, laser scanning galvanometer reciprocating etching cutting, in the prior art, reliability and high-efficiency processing cannot be considered in the cutting process. If the cutting frequency is 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 a sufficient number of cuts are applied, the cut through is ensured, but not only is time wasted, but the protective padding below 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 material thin-wall structure, which has the advantages of quick clamping and de-clamping 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 single scribing etching depths (d) corresponding to the incident pulse energy fluxes on a test piece made of the same material as the carbon fiber composite material, and fitting to obtain a material removal threshold value (F)th) And a characteristic absorption depth (d)0) Setting the initial spot overlap rate O of the laser processing system1In the range of [0.96, 0.99%]；
S2, sequentially stacking a protective base 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% under the wavelength of the laser processing light beam;
s3, setting the pulse energy flux F of the laser processing system incident to the surface of the workpiece to be processed according to the removal threshold value (F)th) Characteristic absorption depth (d)0) Obtaining 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)1And 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 in a different order or simultaneously, 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 utilizing remote laser processing such as a scanning galvanometer and the like. In the conception of the invention, a non-contact stress clamping mode matched with press mounting of a magnetic adsorption pressurizing plate is used, and ultrafast laser processing is utilized to carry out quantitative processing on thin-wall carbon fiber composite materials with laminated structures. The light transmittance of the pressing plate under the laser processing beam is not less than 85%, so that the incident pulse energy of the laser processing beam under the remote laser mode can effectively act on the carbon fiber composite material, and the reliability of the fitting result in the step S1 is further ensured.
In the invention, the carbon fiber composite material is reliably clamped only by the transparent pressing plate with one side being a plane and the other side being an equal-height synapse array structure and a small amount of magnets; for small-sized flat blanks, the above-mentioned transparent press plate can also be dispensed with. Greatly simplifying the clamping process and reducing the requirement on the clamping stress. In addition, the non-contact processing characteristic avoids the defects of force-induced delamination, skin tearing, edge breakage and the like of the carbon fiber composite material in the processing process, and the method 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 scribe 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 relational expression0And removing the threshold flux FthThe range of the spot overlap ratio O of the laser processing system is set to [0.96,0.99 ]]；
The step S2 is performed before the step S3, in step S2, the protection mat is laid on a bearing and moving platform with ferromagnetism, the carbon fiber composite material is laid on the protection mat, 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, the magnet is placed on the other side of the pressing plate, and the protection mat, the carbon fiber composite material and the pressing plate are firmly adsorbed on the bearing and moving platform;
in step S3, a pulse energy flux F of the laser processing system incident on the surface of the workpiece to be processed is set to pass through the absorption feature depth d0And removing the threshold flux FthDetermining the etching depth d of the single machining which can be removed in each scanning machining, and further determining the number N of machining scans required for cutting through the carbon fiber composite material1；
Maintaining the overlap rate O of processing light spots2Unchanged by the number of processing scans N1Cutting the carbon fiber composite material using the laser machining beam, wherein the machining spot overlap ratio O2The value range is [0.2,0.95 ]]。
The laser cutting method for the carbon fiber composite material is a processing method which is good in processing tool flexibility and capable of being repeatedly used. The invention provides a pressing plate tool made of transparent materials with synapse parts, which realizes the reusability of the pressing plate for many times by utilizing the characteristics that materials can be removed only in a focusing area by laser processing, and most of an energy field can penetrate through the transparent pressing plate without damaging the pressing plate. Therefore, the process flow of machining, clamping and preparing is effectively shortened, and the effects of good flexibility, reusability and great reduction of the material cost of the tool are achieved.
In accordance with one aspect of the present invention,
in steps S1 and S3, the pulse width of the laser machining beam is ≦ 20 ps.
In accordance with one aspect of the present invention,
in the 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 used2The spot diameter defined by "type" is equivalent to that defined by other types, for example "1/e" type, 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 diameter range of the convex contact is 0.3mm-3mm, and the pressing plate is made of high polymer materials.
In the concept of the present invention, the shape of the convex contact portion is not limited, and may be a cylindrical shape or a truncated cone shape.
Preferably, in the concept of the present invention, the height of the convex contact portion is more than or equal to 10 times the Rayleigh length of the laser processing beam. If the synapse height is too small, on one hand, the lower surface of the pressing plate is also in a Rayleigh length area near the beam waist, so that the pressing plate is easy to be damaged, and on the other hand, the chip removal is not facilitated.
In accordance with one aspect of the present invention,
in step S1, the relationship between the etching depth d of the single scribe and the energy flux F of different incident pulses is determined, and the fitting relationship is:
d(F)＝(4/3)/(1-O)×d0×ln(F/Fth)3/2，
where d is the single scribe etch depth, F is the incident pulse energy flux, d0Is the absorption characteristic depth FthIs the ablation threshold flux and 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 processing etching depth d and the processing scanning times N1Has the following relationship:
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-processing etching depth d needs to be calculated by the fitting relational expression,
d＝(4/3)/(1-O)×d0×ln(F/Fth)3/2
where O is the spot overlap ratio and d0Is the absorption characteristic depth, FthIs to remove the threshold flux, FIs the pulse energy flux incident on the surface of the workpiece to be machined.
In the processing of the present invention, the incident pulse energy flux F of the laser processing system is first set, i.e., d ═ 4/3)/(1-O) × d according to the relationship0×ln(F/Fth)3/2Obtaining the corresponding single-time scribing etching depth d, and determining the processing scanning times N according to the thickness of the carbon fiber composite material1I.e. by N1The number of machining scans N is calculated as (1.2-1.4) × (DD/d)1And then projecting remote laser to penetrate through the pressing plate and irradiate the carbon fiber composite material for laser cutting. The safety factor is set to be 1.2-1.4, and the scanning times N of etching processing are ensured when the laser acts on the interface profile of the processing structure to be processed at the bottom of the synapse part1After 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 reuse 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, the carbon fiber composite material is in a curled shape or a plane shape in a free state, and can be flattened in an elastic deformation range;
specifically, the method can be used for processing the thin-wall carbon fiber composite material in a curled state and a flat state, a pressing plate is required to be used when the curled carbon fiber composite material and the large-breadth flat carbon fiber composite material are processed, and only a magnet can be used when the small-breadth flat carbon fiber composite material is processed.
In accordance with one aspect of the present invention,
the magnet is a permanent magnet or a soft magnet.
The invention has the following beneficial effects: the laser cutting method provided by the invention aims at the carbon fiber composite material which is high in hardness and difficult to process and is less than 3mm thick, provides necessary cutting times, and realizes both processing reliability and high efficiency.
The laser cutting method provided by the invention aims at the thin-wall structure of the carbon fiber composite material, is a method which has no processing contact stress, can rapidly clamp and unclamp, and quantizes the key cutting process, and can realize the cutting effect with high efficiency, low cost and high quality.
The ultrafast laser cutting method for the carbon fiber composite material structure is reliable in principle, small in calculated amount and capable of considering both processing reliability and efficiency. By quantifying the relevant rules, the reliability and the high efficiency in the cutting process can be considered. The etching depth of each pass is deduced according to the linear absorption law of the carbon fiber composite material, the necessary times required for cutting the carbon fiber composite completely are quantized, reliable cutting is guaranteed, excessive cutting due to the fact that the cutting is guaranteed is avoided, invalid processing time is effectively prevented from being consumed, the protective base plate is prevented from being damaged, and the increase of the processing cost is avoided.
Drawings
FIG. 1 is a flow chart of an ultra-fast laser cutting method for carbon fiber composite structures in one embodiment of the present invention.
Fig. 2 is a schematic view of a laser machining system in accordance with the present invention.
The reference numbers: 1-laser machining a beam; 2-a magnet; 3, pressing a plate; 4-carbon fiber composite material; 5-a protective backing plate; 6-carrying 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 used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
The processing structure in the present specification refers to a geometric structural element that is required to be cut out of a carbon fiber composite material by laser processing and reciprocating etching, and includes, for example: the overall outer contour boundary of the workpiece, round holes and long round holes inside the outer contour boundary and other simple structures such as patterned special-shaped structures.
Referring to fig. 1, an ultrafast laser cutting method for a carbon fiber composite structure according to an embodiment of the present invention includes the following steps:
s1, measuring and recording a plurality of incident pulse energy fluxes F and single scribing etching depths d corresponding to the incident pulse energy fluxes F on a test piece made of the same material as the carbon fiber composite material, and fitting to obtain a material removal threshold FthAnd a characteristic absorption depth d0Setting the initial spot overlap rate O of the laser processing system1In the range of [0.96, 0.99%]；
S2, sequentially stacking the protective backing plate 5, the carbon fiber composite material 4, the pressing plate 3 and the magnet 2 on a bearing and moving platform 6 of the 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 the laser processing light beam 1;
s3, setting the 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 FthCharacteristic absorption depth d0And calculating a formula to obtain the corresponding single-scribing etching depth d, and determining the processing scanning times N according to the thickness DD of the carbon fiber composite material 41And remotely projecting a laser processing beam 1 to penetrate through the pressing plate 3 and irradiate the carbon fiber composite material 4, and cutting the processing structure of the carbon fiber composite material 4 by laser.
The ultrafast laser cutting method for the carbon fiber composite material structure provided by the embodiment is a non-contact processing method using remote laser processing such as scanning galvanometer. In this embodiment, a non-contact stress clamping mode in which the magnetic force of the magnet 2 is used to adsorb the pressurizing plate 3 for press-fitting and matching is adopted, and ultrafast laser processing is utilized for the lamination structureThe thin-walled carbon fiber composite material 4 is subjected to quantitative processing. The light transmittance of the pressing plate 3 under the laser processing beam 1 is not less than 85%, so that the incident pulse energy of the laser structure beam 1 under the remote laser mode can effectively act on the carbon fiber composite material 4, and the reliability of the laser of the result fitted in the step S1 is further ensured. Specifically, the initial spot overlap ratio O of the laser processing beam 1 satisfying the set remote laser processing method of the present embodiment is set1In the range of [0.96, 0.99%]And the platen 3 is made of a material having a light transmittance of not less than 85% at the wavelength of the laser processing beam 1, it can be considered that 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 show the original relationship with respect to the processing flux.
In the embodiment, the carbon fiber composite material 4 is reliably clamped only by the pressing plate 3 with one side being a plane and the other side being an equal-height synapse array structure and the assistance of a small amount of magnets 2; for small-sized flat blanks, the above-mentioned press plate 3 can also be omitted. Greatly simplifying the clamping process and reducing the requirement on the clamping stress. In addition, the non-contact processing characteristic avoids the defects of force-induced delamination, skin tearing, edge breakage and the like of the carbon fiber composite material 4 in the processing process.
In the present embodiment, it is preferred that,
in step S1, the energy flux F of the incident pulse in the laser beam 1 and the corresponding single scribe depth d are measured and recorded on the test piece, and the material removal threshold F is obtained by fitting the theoretical formulathAnd a characteristic absorption depth d0Setting the initial spot overlap rate O of the laser processing system1In the range of [0.96, 0.99%]；
Step S2 is performed before step S3, in step S2, the protective padding plate 5 is laid on the bearing and moving platform 6 with ferromagnetism, the carbon fiber composite material 4 is laid on the protective padding plate 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 padding plate 5, the carbon fiber composite material 4 and the pressing plate 3 are adsorbed and fixed on the bearing and moving platform 6;
in step S3, a pulse energy flux F of the laser processing system incident on the surface of the workpiece to be processed is set and passes through the absorption feature depth d0And removing the threshold flux FthThe single process etch depth d that can be removed for each scan process can be determined and further the number of process scans N required to cut through the carbon fiber composite material 4 can be determined1；
Maintaining the overlap rate O of processing light spots2Unchanged by the number of machining scans N1Cutting the carbon fiber composite material 4 using the laser processing beam 1, wherein the processing spot overlap rate O2The value range is [0.2,0.95 ]]。
The laser cutting method for the carbon fiber composite material provided by the embodiment is a processing method which is good in processing tool flexibility and can be repeatedly utilized. The embodiment provides the pressing plate 3 made of transparent material with synapse parts, and the characteristic that materials can be removed only in a focusing area by laser processing and an energy field can mostly penetrate through the pressing plate 3 without damaging the pressing plate 3 is utilized, so that the reusability of the pressing plate 3 is realized. Therefore, the process flow of machining, clamping and preparing is effectively shortened, and the effects of good flexibility, reusability and great reduction of the material cost of the tool are achieved.
In the present embodiment, it is preferred that,
in steps S1 and S3, the pulse width of the laser machining beam 1 is ≦ 20 ps.
In the present embodiment, it is preferred that,
in steps S1 and S3, the spot overlap ratio O is calculated as follows:
O＝1-v/Df
wherein v is the scanning speed of the laser beam used and D is "1/e" of the laser beam used2The spot diameter defined by "type" is equivalent to that defined by other types, for example "1/e" type, and f is the pulse frequency of the laser used.
In the present embodiment, it is preferred that,
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 range of the convex contact part is 0.3mm-3mm, and the pressing plate 3 is made of high polymer materials.
In the present embodiment, the shape of the convex contact portion is a cylindrical shape. The bottom of the synapse is provided with a plane in contact with the carbon fiber composite material 4. The plane is set up in order to increase the area of contact of synapse portion with carbon-fibre composite 4, prevents fish tail carbon-fibre composite 4, also prevents that carbon-fibre composite 4's surface from scraping the flower with clamp plate 3, because clamp plate 3 scrapes the flower and can cause the luminousness decline of clamp plate 3, reduces clamp plate 3's reuse rate.
In this embodiment, the protruding portion height is greater than 4mm, and this makes the distance between the lower surface of the planar portion of clamp plate 3 and carbon-fibre composite 4 not undersize, can enough guarantee good chip removal, can prevent again that the lower surface of the planar portion of clamp plate 3 from being ablated by laser: if the synapse height is too small, the lower surface of the platen is also within the rayleigh length region near the beam waist, and the platen is easily damaged.
In the present embodiment, it is preferred that,
in step S1, the relationship between the single scribe etching depth d and the energy flux F of different incident pulses is determined, and the fitting relationship is:
d(F)＝(4/3)/(1-O)×d0×ln(F/Fth)3/2，
where d is the single scribe etch depth, F is the incident pulse energy flux, d0Is the absorption characteristic depth FthIs the ablation threshold flux and O is the spot overlap ratio.
In the present embodiment, it is preferred that,
in step S3, the carbon fiber composite thickness DD has the following relationship with the single process etching depth d and the number of process scans 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 etching depth d of the single processing needs to be calculated by a fitting relation,
d＝(4/3)/(1-O)×d0×ln(F/Fth)3/2
where O is the spot overlap ratio and d0Is the absorption characteristic depth, FthIs the ablation threshold flux and F is the pulse energy flux incident on the surface of the workpiece to be machined.
In the processing of this embodiment, the pulse energy flux F incident on the surface of the workpiece to be processed of the laser processing system is first set, that is, the relation d of (4/3)/(1-O) × d passing through the test piece is0×ln(F/Fth)3/2Obtaining the corresponding single-time scribing etching depth d, and determining the processing scanning times N according to the thickness of the carbon fiber composite material1I.e. by N1The number of machining scans N is calculated as (1.2-1.4) × (DD/d)1And then, long-distance laser is projected to penetrate through the pressing plate 3 and irradiate the carbon fiber composite material 4, so that laser cutting is performed. The safety factor is set to be 1.2-1.4, and the scanning times N of etching processing are ensured when the laser acts on the interface profile of the processing structure to be processed at the bottom of the synapse part1After that, complete cutting can be achieved.
In the present embodiment, it is preferred that,
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 backing plate 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 reuse rate.
In the present embodiment, it is preferred that,
the thickness of the carbon fiber composite material 4 is less than or equal to 3.0mm, and the carbon fiber composite material 4 is in a curled shape or a plane shape 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, it is preferred that,
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 necessary cutting times for the carbon fiber composite material 4 with high hardness and difficult processing and thickness less than 3mm, and achieves both processing reliability and high efficiency.
The laser cutting method provided by the embodiment is a method which is free of machining contact stress, capable of rapidly clamping and de-clamping and capable of quantifying cutting key processes, and can achieve the cutting effect with high efficiency, low cost and high quality aiming at the carbon fiber composite material thin-wall structure.
The ultrafast laser cutting method for the carbon fiber composite material structure provided by the embodiment is a method which is reliable in principle, small in calculated amount and capable of considering both processing reliability and efficiency. By quantifying the relevant rules, the reliability and the high efficiency in the cutting process can be considered. The etching depth of each pass is deduced according to the linear absorption law of the carbon fiber composite material, the necessary times required for cutting through the carbon fiber composite material are quantized, reliable cutting through is guaranteed, over-cutting due to the fact that the cutting through is guaranteed is avoided, invalid processing time is effectively prevented from being consumed, the protective base plate 5 is prevented from being damaged, and the increase of the processing cost is avoided.
In another embodiment of the present invention, an ultrafast laser cutting method for a carbon fiber composite structure includes 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 between the etching depth d of the single scribing and the energy flux F of different incident pulses, and calculating the formula d (F) (4/3)/(1-O) x d)0×ln(F/Fth)3/2Fitting to obtain the depth d of the absorption feature0And removing the threshold flux FthWherein O is [0.96,0.99 ]]The interval is a certain value, and is selected to be 0.97.
The carbon fiber composite material 4 in this embodiment has a curled structure. The carbon fiber composite material 4 has the component M55/BS-4 and the thickness of 0.40 mm. The laser for processing is a Gaussian pulse sequence with the central wavelength of 1064nm and the single pulse duration of 12ps, is remotely transmitted by a scanning galvanometer processing system, and generates a light spot diameter with the diameter D being 23 +/-1 mu m on the surface of the material after being focused by a flat field lens. Fitting equation d (f) ═ 4/3)/(1-O) × d0×ln(F/Fth)3/2Then, 5 incident pulse energies are selectedFlux, i.e. F2.4, 3.3, 6.1, 8.2, 15.0J/cm2. The scanning speed v of the laser processing beam of single scribing etching is 0.7m/s, the spot diameter D is 23 +/-1 μm, and the pulse frequency f is 1.0MHz, so the initial spot overlapping rate O11-v/Df ≈ 0.97. This degrades the fitting equation to practical values of d (f) ═ 4/3)/(1-O) × d0×ln(F/Fth)3/2＝43.8×d0×ln(F/Fth)3/2. By using Origin software fitting, the most probable fitting value can be obtained to remove the threshold flux Fth＝1.39±0.010J/cm2Absorption characteristic depth d0243 ± 5 nm. It should be noted that, in the present embodiment, a single scribe etching method is adopted, and if the method is equivalent to the in-situ tapping method, the method is approximately equivalent to N ═ 1/(1-O) ≈ 33 pulses during the in-situ tapping. According to the well-known processing threshold hatching effect, at 30-50 in-situ tapping pulses, the processing threshold of the material, although not the saturation value, which is typically the lowest of the processing thresholds at in-situ tapping of hundreds to thousands of pulses, has tended to approach the saturation value. Therefore, although the machining threshold corresponding to the action of tens of pulses is measured in the present embodiment, the measured machining threshold can approximately represent the threshold for in-situ machining by hundreds or even thousands of pulses, which is a necessary condition for realizing cutting by back and forth etching. This results in the removal threshold flux F determined hereth＝1.39±0.010J/cm2Absorption characteristic depth d0243 +/-5 nm, and can be used in a calculation formula used for determining the machining scanning number N1 without obvious errors.
As shown in figure 2 of the drawings, in which,
s2, a planar protection base plate 5 made of asbestos rubber plates and meeting the requirements for thickness uniformity is laid on a bearing and moving platform 6 with ferromagnetism, one surface of a carbon fiber composite material 4 is attached to the upper surface of the protection base plate 5, one side of a pressing plate 3 with an equal synapse 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 magnets face the laser emitting surface, and no interface of a processing structure is arranged right below the pressing plate 3 at the distribution position.
The thickness tolerance of the planar protective backing plate 5 is 0.05mm, and in particular, the thickness uniformity ensures that the flatness of the thin-walled workpiece 4 to be machined, which is subsequently spread on the protective backing plate 5, is not affected.
The pressing plate 3 is formed by die pressing and is made of polymethyl methacrylate, namely organic glass acrylic. The transparency of the organic glass acrylic is similar to that of glass, and the organic glass acrylic glass is not easy to crack due to good shock resistance, has higher surface hardness, and has the wear resistance close to that of an aluminum material; the organic glass acrylic has good plastic forming performance and mechanical cutting performance, and smooth surface, and is one of ideal pressing plate 3 materials. Before use, all contaminants such as dust on the outer surface of the pressing plate 3 need to be wiped to ensure good transmittance. The organic glass acrylic pressure plate 3 can be integrally processed by a mechanical cutting mode and can also be integrally formed by molding and shaping.
S3, projecting a remote laser processing beam 1 to penetrate through the pressing plate 3 and irradiate the to-be-processed area of the processed workpiece 4, and determining the etching depth d of single processing and the processing scanning times N required by cutting through according to a calculation formula1. In this embodiment, the carbon fiber composite material 4 has a width of more than 1m × 1m, which is much larger than the range of < 10cm of the scanning processing system used for projecting the remote laser 12Therefore, the processing structure interface of the processed workpiece 4 is correspondingly processed through the mode of 'reciprocating etching + block splicing'.
Specifically, it is found that the processing spot overlap ratio O is 1-v/Df and 0.5652, and the pulse energy flux F incident on the surface of the workpiece is 15.0J/cm, using the beam scanning speed v of 10.0m/s, the spot diameter D of 23 ± 1 μm, and the pulse frequency F of 1.0MHz2The etching depth d of the single process is (4/3)/(1-O) × d0×ln(F/Fth)3/22.73 μm. Therefore, in order to cut through the carbon fiber composite material 4 having a carbon fiber composite material thickness D of 0.4mm, it is theoretically necessary to etch in situ at least 147 times to cut through. In practice, in order to refine the cutting time and achieve the purpose of cutting through without wasting the etching times, the obtained theoretical minimum times are multiplied by a safety factor of 1.2-1.4. In practice, if only in-situ reciprocation is desiredEtching N1If the cut-through is realized 205 times (1.2-1.4) x (D/D) -176-D, a larger spot is required, which also has the characteristic of large depth of focus, or N is required to be etched along each track line by multiple tangent paralleling, i.e. parallel cutting1The cutting can be realized by increasing the width of the cutting seam.
The foregoing is merely exemplary of particular aspects of the present invention and devices and structures not specifically described herein are understood to be those of ordinary skill in the art and are intended to be implemented in such conventional ways.
The above is only one embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made to the present invention by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An ultrafast laser cutting method for a carbon fiber composite structure is characterized by comprising the following steps:
s1, measuring and recording a plurality of incident pulse energy fluxes (F) and single scribing etching depths (d) corresponding to the incident pulse energy fluxes on a test piece made of the same material as the carbon fiber composite material (4), and fitting to obtain a removal threshold value (F)th) And a characteristic absorption depth (d)0) Setting the initial spot overlap ratio (O) of the laser processing system1) 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 the 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 according to the removal threshold (F)th) Characteristic absorption depth (d)0) Obtaining the corresponding single scribing etching depth (d) according to the relational expression, and then obtaining the specific value relation between the thickness (DD) of the carbon fiber composite material and the single scribing etching depth (d)Determining the number of machining scans (N)1) And remotely projecting the laser processing 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.
2. The ultrafast laser cutting method for carbon fiber composite structures of claim 1,
the step S1 is performed before the step S3, and in the step S1, a plurality of single scribe etching depths (d) and a plurality of incident pulse energy fluxes (F) of the corresponding laser processing beams (1) are measured and recorded on the test piece, and the absorption feature depths (d) are calculated by fitting the relational expressions0) And removing the threshold flux (F)th) Setting an initial spot overlap ratio (O) of the laser processing system1) In the range of [0.96, 0.99%]；
The step S2 is performed before the step S3, in step S2, the protective padding plate (5) is laid on a bearing and moving platform (6) with ferromagnetism, the carbon fiber composite material (4) is laid on the protective padding plate (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 padding plate (5), the carbon fiber composite material (4) and the pressing plate (3) are adsorbed and fixed on the bearing and moving platform (6);
in step S3, a pulsed energy flux (F) of the laser processing system incident on the surface of the workpiece to be processed is set by absorbing a characteristic depth (d)0) And removing the threshold flux (F)th) Determines a single machining etch depth (d) that can be removed per scanning machining and further determines at least the number of machining scans (N) required to cut through the carbon-fibre composite material (4)1)；
Maintaining the overlap ratio (O) of processing light spots2) Unchanged by the number of machining scans (N)1) Cutting the carbon fiber composite material (4) using the laser machining beam (1), wherein the machining spot overlap ratio (O)2) The value range is [0 ].2,0.95]。
3. The ultrafast laser cutting method for carbon fiber composite structures of claim 2,
in steps S1 and S3, the pulse width of the laser machining beam (1) is ≦ 20 ps.
4. The ultrafast laser cutting method for carbon fiber composite structures of claim 3,
in the steps S1 and S3, the initial spot overlap ratio (O)1) And processing spot overlap ratio (O)2) Are spot overlap ratios (O), and are 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. The ultrafast laser cutting method for carbon fiber composite structures of claim 3,
one side of the pressing plate (3) is a plane, the height of a convex contact part with equal height arranged on the other side is more than or equal to 10 times of the Rayleigh length of the laser processing light 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 high polymer materials.
6. The ultrafast laser cutting method for carbon fiber composite structures as claimed in claim 3, wherein in said step S1, the relationship between the single scribe etching depth (d) and the different incident pulse energy fluxes (F) is determined, and said fitted relationship is:
d(F)＝(4/3)/(1-O)×d0×ln(F/Fth)3/2，
where d is the single scribe etch depth, F is the incident pulse energy flux, d0Is the absorption characteristic depth FthIs the ablation threshold flux and O is the spot overlap ratio.
7. The ultrafast laser cutting method for carbon fiber composite material structure as claimed in claim 3, wherein in the step S3, the carbon fiber composite material thickness (DD) is related to the single process etching depth (d) and the number of process scans (N)1) Has the following relationship:
N1(1.2-1.4) x (DD/d), wherein DD is the thickness of the carbon fiber composite material, d is the etching depth of single processing,
the single-process etching depth (d) needs to be calculated by the fitted relational expression,
d＝(4/3)/(1-O)×d0×ln(F/Fth)3/2where O is the spot overlap ratio and d0Is the absorption characteristic depth, FthIs the ablation threshold flux and F is the pulse energy flux incident on the surface of the workpiece to be machined.
8. The ultrafast laser cutting method for carbon fiber composite structures of claim 3,
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).
9. The ultrafast laser cutting method for carbon fiber composite structures as claimed in claim 3, wherein the thickness of the carbon fiber composite (4) is less than or equal to 3.0mm, and the carbon fiber composite (4) is in a curled or flat shape in a free state and can be flattened in an elastic deformation range.
10. Ultrafast laser cutting method for carbon fiber composite structures as claimed in claim 3, characterized in that said magnets (2) are permanent and soft magnets.
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Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006272374A (en) * | 2005-03-28 | 2006-10-12 | National Institute For Materials Science | Cutting/machining method of carbon fiber and its apparatus |
| US20110240617A1 (en) * | 2004-03-31 | 2011-10-06 | Imra America, Inc. | Laser-based material processing apparatus and methods |
| DE102012014056A1 (en) * | 2012-07-13 | 2013-03-07 | Daimler Ag | Laser processing of fiber materials, preferably e.g. carbon fiber- and/or glass fiber material, comprises processing fiber material using laser beam, and providing fluid layer on fiber material in region of interaction zone |
| CN103817368A (en) * | 2014-02-27 | 2014-05-28 | 大连理工大学 | Method of machining carbon-fibre composite material by combination of laser and machinery |
| CN105073848A (en) * | 2013-03-07 | 2015-11-18 | 三菱丽阳株式会社 | Carbon-fiber-reinforced thermoplastic-resin composite material and molded body using same |
| CN106975847A (en) * | 2017-05-27 | 2017-07-25 | 南京工程学院 | The apparatus and method that a kind of fiber pulse induced with laser cuts carbon fibre composite |
| JP2017217677A (en) * | 2016-06-09 | 2017-12-14 | 福井県 | Laser processing method and laser processing device |
| CN108817699A (en) * | 2018-08-22 | 2018-11-16 | 北京卫星制造厂有限公司 | A method of two-phase composite material is cut using ultrafast laser |
| JP2019000904A (en) * | 2017-06-16 | 2019-01-10 | 株式会社タカラ工芸社 | Laser processing method for carbon fiber-reinforced composite-laminated sheet, and laser-processed carbon fiber-reinforced composite-laminated sheet |
| CN109338341A (en) * | 2018-10-29 | 2019-02-15 | 北京卫星制造厂有限公司 | A kind of preparation method of carbon fiber enhancement resin base composite material surface gold plate |
| KR101951879B1 (en) * | 2018-07-19 | 2019-02-25 | 천종우 | Method for constructing seismic frame to automatic laser processed and jointed structure using carbon fiber reinforced composite material fastener |
| CN110560907A (en) * | 2019-09-19 | 2019-12-13 | 中国民用航空飞行学院 | Infrared laser surface treatment process for carbon fiber composite material |
| CN110586579A (en) * | 2019-08-30 | 2019-12-20 | 江苏大学 | Device and method for laser cleaning and surface modification composite processing of carbon fiber composite material |
| CN111016188A (en) * | 2019-11-18 | 2020-04-17 | 南京理工大学 | Near-infrared laser surface treatment method for carbon fiber/resin matrix composite material |
| CN111618443A (en) * | 2020-05-06 | 2020-09-04 | 湖北工业大学 | Green light ultrafast laser processing system and method for carbon fiber resin matrix composite material |
| CN111999387A (en) * | 2020-08-31 | 2020-11-27 | 广东工业大学 | Laser ultrasonic automatic detection system and method for carbon fiber composite material blade |
| CN112380677A (en) * | 2020-11-02 | 2021-02-19 | 中国科学院沈阳自动化研究所 | Simulation method for temperature field in release agent for stripping carbon fiber material based on laser cleaning |
| CN112537921A (en) * | 2020-12-17 | 2021-03-23 | 中国科学院上海硅酸盐研究所 | Phenolic resin coated chopped carbon fiber composite powder for laser 3D printing and preparation method thereof |
| CN113102902A (en) * | 2021-05-10 | 2021-07-13 | 武汉华工激光工程有限责任公司 | Burr-free laser drilling method for carbon fiber composite material |
-
2021
- 2021-12-30 CN CN202111649755.0A patent/CN114227008B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110240617A1 (en) * | 2004-03-31 | 2011-10-06 | Imra America, Inc. | Laser-based material processing apparatus and methods |
| JP2006272374A (en) * | 2005-03-28 | 2006-10-12 | National Institute For Materials Science | Cutting/machining method of carbon fiber and its apparatus |
| DE102012014056A1 (en) * | 2012-07-13 | 2013-03-07 | Daimler Ag | Laser processing of fiber materials, preferably e.g. carbon fiber- and/or glass fiber material, comprises processing fiber material using laser beam, and providing fluid layer on fiber material in region of interaction zone |
| CN105073848A (en) * | 2013-03-07 | 2015-11-18 | 三菱丽阳株式会社 | Carbon-fiber-reinforced thermoplastic-resin composite material and molded body using same |
| CN103817368A (en) * | 2014-02-27 | 2014-05-28 | 大连理工大学 | Method of machining carbon-fibre composite material by combination of laser and machinery |
| JP2017217677A (en) * | 2016-06-09 | 2017-12-14 | 福井県 | Laser processing method and laser processing device |
| CN106975847A (en) * | 2017-05-27 | 2017-07-25 | 南京工程学院 | The apparatus and method that a kind of fiber pulse induced with laser cuts carbon fibre composite |
| JP2019000904A (en) * | 2017-06-16 | 2019-01-10 | 株式会社タカラ工芸社 | Laser processing method for carbon fiber-reinforced composite-laminated sheet, and laser-processed carbon fiber-reinforced composite-laminated sheet |
| KR101951879B1 (en) * | 2018-07-19 | 2019-02-25 | 천종우 | Method for constructing seismic frame to automatic laser processed and jointed structure using carbon fiber reinforced composite material fastener |
| CN108817699A (en) * | 2018-08-22 | 2018-11-16 | 北京卫星制造厂有限公司 | A method of two-phase composite material is cut using ultrafast laser |
| CN109338341A (en) * | 2018-10-29 | 2019-02-15 | 北京卫星制造厂有限公司 | A kind of preparation method of carbon fiber enhancement resin base composite material surface gold plate |
| CN110586579A (en) * | 2019-08-30 | 2019-12-20 | 江苏大学 | Device and method for laser cleaning and surface modification composite processing of carbon fiber composite material |
| CN110560907A (en) * | 2019-09-19 | 2019-12-13 | 中国民用航空飞行学院 | Infrared laser surface treatment process for carbon fiber composite material |
| CN111016188A (en) * | 2019-11-18 | 2020-04-17 | 南京理工大学 | Near-infrared laser surface treatment method for carbon fiber/resin matrix composite material |
| CN111618443A (en) * | 2020-05-06 | 2020-09-04 | 湖北工业大学 | Green light ultrafast laser processing system and method for carbon fiber resin matrix composite material |
| CN111999387A (en) * | 2020-08-31 | 2020-11-27 | 广东工业大学 | Laser ultrasonic automatic detection system and method for carbon fiber composite material blade |
| CN112380677A (en) * | 2020-11-02 | 2021-02-19 | 中国科学院沈阳自动化研究所 | Simulation method for temperature field in release agent for stripping carbon fiber material based on laser cleaning |
| CN112537921A (en) * | 2020-12-17 | 2021-03-23 | 中国科学院上海硅酸盐研究所 | Phenolic resin coated chopped carbon fiber composite powder for laser 3D printing and preparation method thereof |
| CN113102902A (en) * | 2021-05-10 | 2021-07-13 | 武汉华工激光工程有限责任公司 | Burr-free laser drilling method for carbon fiber composite material |
Non-Patent Citations (1)
| Title |
|---|
| 底才翔;孙艳军;王菲;陈?;丁伟;: "激光切割碳纤维复合材料的温度场仿真", 激光技术, no. 05, pages 108 - 112 * |
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