CN107633115A - The Finite Element Method of multiple spot laser impact forming - Google Patents
The Finite Element Method of multiple spot laser impact forming Download PDFInfo
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Abstract
The invention discloses a kind of Finite Element Method of multiple spot laser impact forming, comprise the following steps：Multiple spot laser-impact simulation is carried out to the feature unit body with certain size first using Finite Element Simulation Software ABAQUS, obtains the total residual stress distribution σ of thickness direction diverse locationTOT；By theoretical formula σLSP=σTOT‑σEQ, obtain the residual stress σ as caused by inducing laser-impactLSPThickness direction is distributed；σEQFor equilibrium stress；To residual stress σ caused by laser-impact induction in MatlabLSPThickness direction distributed data is fitted, and obtains σLSPIn the fitting function of thickness direction distribution；Using user's favorite subroutine SIGINI to define primary stress field in ABAQUS, and then the part with actual analysis physical dimension is implicitly analyzed, finally obtain part shape required under specific laser-impact technological parameter effect.The present invention spends less cost to set up the relation between laser impact forming technological parameter and required part shape using the theoretical method being combined with finite element modelling.
Description
Technical field
The present invention relates to multiple spot laser impact forming technical field, especially a kind of finite element of multiple spot laser impact forming
Analogy method.
Background technology
Laser impact forming is a new laser application field, by quick quick plasticity Accurate Shaping development
A kind of brand-new part forming technology come, can also be produced on part top layer while Shape Parts needed for acquisition has
Certain thickness residual compressive stress.Laser impact forming is using high power density, the laser of short pulse, passes through specific light
Learn element and form corresponding laser facula light beam, the light beam is irradiated on absorbed layer through the water constraint layer of flowing, and absorbed layer is inhaled
Receipts laser energy occurs gasification and produces steam, and steam continues to absorb laser energy formation etc. under the restraint condition of restraint layer water
Gas ions shock wave, due to the effect of restraint layer, plasma stock wave produces the stress wave propagated to inside parts, works as generation
Stress exceed material dynamic yield strength when, part produce macroscopic view plastic deformation.
In order to obtain the laser impact forming part of required shape, it is necessary to be optimized to laser-impact technological parameter, so
And in the complexity and shaping due to multiple spot laser impact forming mechanism many variable factors influence so that in optimize technique
Very big difficulty in parameter be present.If only relying on experimental data and operating experience to determine technological parameter, will spend substantial amounts of
Human and material resources and time, increase manufacturing cost.It is even more so when to the laser impact formings of heavy parts.Pass through fully profit
With the forming property of material and the architectural feature of part, with reference to finite element simulation calculation, to excavate new forming process.Cause
Finite element modelling is incorporated into multiple spot laser impact forming by this, and laser impact forming technological parameter is optimized.In reality
In operation, due to spot size very little, the part stock size of shaping is bigger, hot spot needed for Laser Shock Forming Process
Quantity is thousands of, while also needs to be refined in laser-impact area grid, and the amount of calculation of such finite element modelling will be non-
Chang Ju great, limited by cost is calculated, there is an urgent need to a kind of new multiple spot laser impact forming finite element modelling side now
Method.
The content of the invention
The technical problems to be solved by the invention are, there is provided a kind of finite element modelling side of multiple spot laser impact forming
Method, the method being combined using theory with finite element modelling, determined within the less time needed for multiple spot laser impact forming
Technological parameter, so as to spend less cost to set up between laser impact forming technological parameter and required part shape
Relation.
In order to solve the above technical problems, the present invention provides a kind of Finite Element Method of multiple spot laser impact forming, bag
Include following steps：
(1) more dot lasers are carried out to the feature unit body with certain size using Finite Element Simulation Software ABAQUS first
Shock simulation, obtain the total residual stress distribution σ of thickness direction diverse locationTOT；
(2) by theoretical formula σLSP=σTOT-σEQ, obtain the residual stress σ as caused by inducing laser-impactLSPThickness direction
Distribution；σEQFor equilibrium stress；
(3) to residual stress σ caused by laser-impact induction in MatlabLSPThickness direction distributed data is fitted,
Obtain σLSPIn the fitting function of thickness direction distribution；
(4) primary stress field is defined using user's favorite subroutine SIGINI in ABAQUS, and then to actual analysis
The part of physical dimension is implicitly analyzed, and finally obtains part shape required under specific laser-impact technological parameter effect.
Preferably, in step (1), the simulation of multiple spot laser-impact specifically comprises the following steps：
(11) geometrical model and definition material attribute are established；
(12) Explicit Analysis is set to walk；Time of analysis step is it is ensured that kinetic energy finally levels off to 0 in each analysis step；
(13) load and grid division are applied；
(14) analysis operation and post processing are submitted；FEM calculation is completed, obtains the total remnants of thickness direction diverse location
Stress distribution σTOT, wherein thickness direction is Z-direction, total residual stress distribution σTOTResidual stress including both direction,
The respectively stress σ of X axisTOT,XXWith the stress σ of Y-axisTOT,YY。
Preferably, in step (11), the dynamic constitutive of TC4 titanium alloys is described using such as drag；
In formula：A is yield strength, and B and n reflect the strain hardening feature of material, and C reflects strain rate to material property
Influence, εpRepresent equivalent plastic strain,Representative refers to strain rate,Represent dynamic strain rate.
Preferably, in step (1), the feature unit body and actual multiple spot laser impact forming part with certain size exist
Thickness direction has an identical size, and length and width dimensions are smaller than actual multiple spot laser impact forming part.
Preferably, the residual stress σ as caused by inducing laser-impact in step (2)LSPThickness direction is distributed, wherein thick
Degree direction is Z-direction, σLSPThe stress σ of residual stress including both direction, respectively X axisLSP,XXWith the stress of Y-axis
σLSP,YY。
Beneficial effects of the present invention are：Mould is carried out to the feature unit body with smaller physical dimension first in ABAQUS
Intend analysis, obtain the residual stress distribution in actual multiple spot laser impact forming part thickness direction, while multiple spot laser-impact mistake
Journey numerical simulation need to only carry out Explicit Analysis, apply process for the laser impact intensified load of more hot spots, using Fortran languages
The subprogram of speech editor realizes the loading of diverse location at different moments, improves efficiency, greatly reduces calculating cost；Adopt simultaneously
Processing is further fitted with the Matlab residual stress data obtained to simulation, residual stress distribution function is obtained, improves
The efficiency and accuracy of data analysis；Finally by by different technological parameters, (laser power density, spot radius, impact are strong
Change route, strengthen number, overlapping rate, pulsewidth) obtained thickness direction residual stress distribution data as primary stress field, by with
Family subprogram SIGINI is defined, to implicitly being analyzed with actual geometry large-scale part, zero of shape needed for acquisition
Part, therefore this method has the characteristics of rapid, inexpensive, simple and easy to do, calculating is accurate, has preferable future in engineering applications.
Brief description of the drawings
Fig. 1 is the method flow schematic diagram of the present invention.
Fig. 2 is more laser impact forming loading area schematic diagrames of the present invention.
Fig. 3 is the final part schematic shapes that more laser impact formings of the present invention obtain.
Embodiment
As shown in figure 1, a kind of Finite Element Method of multiple spot laser impact forming, comprises the following steps：
(1) more dot lasers are carried out to the feature unit body with certain size using Finite Element Simulation Software ABAQUS first
Shock simulation, obtain the total residual stress distribution σ of thickness direction diverse locationTOT；
(2) by theoretical formula σLSP=σTOT-σEQ, obtain the residual stress σ as caused by inducing laser-impactLSPThickness direction
Distribution；σEQFor equilibrium stress；
(3) to residual stress σ caused by laser-impact induction in MatlabLSPThickness direction distributed data is fitted,
Obtain σLSPIn the fitting function of thickness direction distribution；
(4) primary stress field is defined using user's favorite subroutine SIGINI in ABAQUS, and then to actual analysis
The part of physical dimension is implicitly analyzed, and finally obtains part shape required under specific laser-impact technological parameter effect.
The Finite Element Method for implementing multiple spot laser impact forming is described in detail below with reference to instantiation：
It is to carry out numerical simulation for multiple spot laser-impact feature unit body first, this process need to only be asked using Explicit
Solve device.Multiple spot laser-impact numerical simulation comprises the following steps：
1.1. geometrical model and definition material attribute are established：Laser impact intensified thin-wall part actual size is 150mm*
30mm*3mm, the feature unit body physical dimension of sunykatuib analysis is 25mm*25mm*3mm, density of material 4500kg/m3, Poisson
Than 0.34, modulus of elasticity 110GPa.The dynamic constitutive of TC4 titanium alloys is described using Johnson-Cook models, it is public
Formula 1 is the expression formula of the model.
In formula：A is yield strength, and B and n reflect the strain hardening feature of material, and C reflects strain rate to material property
Influence, εpRepresent equivalent plastic strain,Representative refers to strain rate,Represent dynamic strain rate；
1.2. Explicit Analysis is set to walk：Time of analysis step is it is ensured that kinetic energy finally levels off to 0 in each analysis step；
1.3. apply load and grid division：Loading area is used as shown in Fig. 2 shock wave peak pressure is 3.8GPa
Flat top beam, circular light class, spot size 3mm, pulse width are arranged to 10ns, overlapping rate 50%, compiled using Fortran
Collect subprogram and carry out more hot spot diverse locations and the application of load at different moments；It is thin that grid is carried out in Laser Shock Processing domain
Change, sizing grid is 150 μm x150 μm x75 μm；
1.4. analysis operation and post processing are submitted：FEM calculation is completed, obtains the total remnants of thickness direction diverse location
Stress distribution σTOT, wherein thickness direction is Z-direction, total residual stress distribution σTOTResidual stress including both direction,
The respectively stress σ of X axisTOT,XXWith the stress σ of Y-axisTOT,YY。
By theoretical formula σLSP=σTOT-σEQ, obtain the residual stress σ as caused by inducing laser-impactLSPThickness direction point
Cloth, wherein thickness direction are Z-direction, σLSPThe stress σ of residual stress including both direction, respectively X axisLSP,XXAnd Y
The stress σ of axial directionLSP,YY。
To residual stress σ caused by laser-impact induction in MatlabLSPThickness direction distributed data is fitted, and is obtained
To different zones σLSPIn the fitting function of thickness direction distribution, it is respectively：
When 0≤X≤50；100≤X≤150；During 0≤Z≤1.68
σLSP,XX=-208.6-376.5*cos (z*2.687)+174.1*sin (z*2.687)
-36.31*cos(2*z*2.687)+99.75*(2*z*2.687)
σLSP,YY=-188.3-361.4*cos (z*2.68)+149.1*sin (z*2.68)
-42.68*cos(2*z*2.68)+92.94*(2*z*2.68)
When 50≤X≤100；During 1.68≤Z≤3
σLSP,XX=-211+196*cos (z*2.627) -372.8*sin (z*2.627)
+27.71*cos(2*z*2.627)+104.6*(2*z*2.627)
σLSP,YY=-189.2+173.5*cos (z*2.634) -355*sin (z*2.634)
+31.82*cos(2*z*2.634)+99.06*(2*z*2.634)
Primary stress field is defined using user's favorite subroutine SIGINI in ABAQUS, and then to actual analysis geometry
The part of size is implicitly analyzed, and is finally obtained under specific laser-impact technological parameter effect, required part shape, finally
Part shape is as shown in Figure 3.
Although the present invention is illustrated and described with regard to preferred embodiment, it is understood by those skilled in the art that
Without departing from scope defined by the claims of the present invention, variations and modifications can be carried out to the present invention.
Claims (5)
1. a kind of Finite Element Method of multiple spot laser impact forming, it is characterised in that comprise the following steps：
(1) multiple spot laser-impact is carried out to the feature unit body with certain size using Finite Element Simulation Software ABAQUS first
Simulation, obtain the total residual stress distribution σ of thickness direction diverse locationTOT；
(2) by theoretical formula σLSP=σTOT-σEQ, obtain the residual stress σ as caused by inducing laser-impactLSPThickness direction is distributed；
σEQFor equilibrium stress；
(3) to residual stress σ caused by laser-impact induction in MatlabLSPThickness direction distributed data is fitted, and is obtained
σLSPIn the fitting function of thickness direction distribution；
(4) primary stress field is defined using user's favorite subroutine SIGINI in ABAQUS, and then to actual analysis geometry
The part of size is implicitly analyzed, and finally obtains part shape required under specific laser-impact technological parameter effect.
2. the Finite Element Method of multiple spot laser impact forming as claimed in claim 1, it is characterised in that in step (1),
The simulation of multiple spot laser-impact specifically comprises the following steps：
(11) geometrical model and definition material attribute are established；
(12) Explicit Analysis is set to walk；Time of analysis step is it is ensured that kinetic energy finally levels off to 0 in each analysis step；
(13) load and grid division are applied；
(14) analysis operation and post processing are submitted；FEM calculation is completed, obtains the total residual stress of thickness direction diverse location
It is distributed σTOT, wherein thickness direction is Z-direction, total residual stress distribution σTOTResidual stress including both direction, respectively
For the stress σ of X axisTOT,XXWith the stress σ of Y-axisTOT,YY。
3. the Finite Element Method of multiple spot laser impact forming as claimed in claim 2, it is characterised in that step (11)
In, the dynamic constitutives of TC4 titanium alloys is described using such as drag；
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In formula：A is yield strength, and B and n reflect the strain hardening feature of material, and C reflects shadow of the strain rate to material property
Ring, εpRepresent equivalent plastic strain,Representative refers to strain rate,Represent dynamic strain rate.
4. the Finite Element Method of multiple spot laser impact forming as claimed in claim 1, it is characterised in that in step (1),
Feature unit body with certain size and actual multiple spot laser impact forming part are in thickness direction with identical size, length and width
Size is smaller than actual multiple spot laser impact forming part.
5. the Finite Element Method of multiple spot laser impact forming as claimed in claim 1, it is characterised in that in step (2)
The residual stress σ as caused by inducing laser-impactLSPThickness direction is distributed, and wherein thickness direction is Z-direction, σLSPIncluding two
The stress σ of the residual stress in individual direction, respectively X axisLSP,XXWith the stress σ of Y-axisLSP,YY。
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| CN113221394A (en) * | 2021-02-08 | 2021-08-06 | 西北工业大学 | Simulation method for laser shot-peening forming of integral wall panel of airplane |
| CN114492113A (en) * | 2022-01-05 | 2022-05-13 | 南京航空航天大学 | Impact damage numerical simulation optimization method based on laser mapping entity grid |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111310375A (en) * | 2020-02-14 | 2020-06-19 | 广东工业大学 | Machining method for optimizing shock wave pressure of laser double-sided simultaneous opposite impact titanium alloy blade |
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| CN111931408A (en) * | 2020-08-13 | 2020-11-13 | 广东工业大学 | Finite element simulation method for laser spalling process |
| CN113221394A (en) * | 2021-02-08 | 2021-08-06 | 西北工业大学 | Simulation method for laser shot-peening forming of integral wall panel of airplane |
| CN113221394B (en) * | 2021-02-08 | 2023-03-17 | 西北工业大学 | Simulation method for laser shot blasting forming of integral wall panel of airplane |
| CN114492113A (en) * | 2022-01-05 | 2022-05-13 | 南京航空航天大学 | Impact damage numerical simulation optimization method based on laser mapping entity grid |
| WO2023131035A1 (en) * | 2022-01-05 | 2023-07-13 | 南京航空航天大学 | Impact damage numerical simulation optimization method based on laser mapping of entity grid |
| CN114492113B (en) * | 2022-01-05 | 2024-06-11 | 南京航空航天大学 | Impact damage numerical simulation optimization method based on laser mapping solid grids |
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