CN107914183A - The flutter stability Forecasting Methodology of milling carbon fiber layer plywood - Google Patents
The flutter stability Forecasting Methodology of milling carbon fiber layer plywood Download PDFInfo
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- CN107914183A CN107914183A CN201711271399.7A CN201711271399A CN107914183A CN 107914183 A CN107914183 A CN 107914183A CN 201711271399 A CN201711271399 A CN 201711271399A CN 107914183 A CN107914183 A CN 107914183A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q17/00—Arrangements for observing, indicating or measuring on machine tools
- B23Q17/09—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring cutting pressure or for determining cutting-tool condition, e.g. cutting ability, load on tool
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Abstract
The present invention provides a kind of milling carbon fiber layer plywood flutter stability Forecasting Methodology, first using average milling force method, tested by the milling of the linear fit difference amount of feeding and obtain Milling Force, identify the Milling force parameter of carbon fiber layer plywood, it is then based on Regenerative Chatter theory, using diamond coatings square end mill, establish milling carbon fiber layer plywood kinetic model, the cutting tool mode parameter obtained finally by hammering experiment is as primary condition, the milling dynamics differential equation is solved on frequency domain, obtain the milling stability decision criteria of the machined parameters relation on spindle speed and axial cutting-in.Machined parameters can be reasonably selected according to the method, are effectively prevented from the vibration of Milling Process, improve workpiece surface quality, reduce tool wear, optimize carbon fibre composite Milling Process process.
Description
Technical field
The present invention relates to composite machine manufacture field, and in particular, to a kind of flutter of milling carbon fiber layer plywood is steady
Qualitative Forecast Methods.
Background technology
Composite product is with good characteristics such as its peculiar high intensity, high-modulus, light weights, with aerospace, vapour
Many fields such as car, electric, fitness equipment are widely applied, and most representational composite material includes glass fibre
Composite material, carbon fibre composite, aramid fiber reinforced composite and tough epoxy resin composite materials etc., these products into
Be required for greatly being machined after type to obtain required dimensional accuracy, but due to composite material have hardness is high, intensity is big,
The features such as poor thermal conductivity, anisotropy, be also easy to produce layering, tear, burr, wire drawing, collapse the defects of block, can lead in process
Cause product mechanics and performance to reduce, belong to typical difficult-to-machine material.Flutter is bad processing during actual processing
Universal phenomenon, and influence the principal element of Workpiece Machining Accuracy, flutter not only influences the surface quality of workpiece, but also can add
The abrasion of fast cutter, or even the service life of lathe can be influenced.At present in actual production, for the milling parameter of carbon fiber structural part
Selection, still rests on by rule of thumb, not the reference bar for avoiding producing vibration alternatively milling parameter in process
Part, therefore the flutter theoretical extension of processing metal material is applied to carbon fibre composite, it appears it is particularly necessary.
The content of the invention
For in the prior art the defects of, the object of the present invention is to provide a kind of flutter instability of milling carbon fiber layer plywood
Property Forecasting Methodology.
A kind of flutter stability Forecasting Methodology of the milling carbon fiber layer plywood provided according to the present invention, including following step
Suddenly：
Step 1：Using slotting cutter respectively to the unidirectional laminate of different fiber angles on milling machine, with the different amount of feeding
Carry out milling experiment；
Step 2：Milling Force of the unidirectional laminate of different fiber angles under the different amount of feeding is measured by measuring instrument, profit
With average Milling Force, the Milling force parameter of the unidirectional laminate of milling under different fiber angles is identified using linear fit；
Step 3：The Milling force parameter sum-average arithmetic of the unidirectional laminate of Single Fiber angle is obtained according to principle of stacking
The Milling force parameter of multi direction laminate；
Step 4：The frequency response function for obtaining milling cutter point of a knife point is tested using hammering, from the displacement frequency response function of milling cutter point of a knife point
Middle analysis obtains master mode parameter, and the master mode parameter includes a second order intrinsic frequency, damping and the rigidity of cutter；
Step 5：By the Cutting Force Coefficient of multi direction laminate, the milling laminate based on milling Regenerative Chatter principle is established
Kinetic model；
Step 6：The differential equation of kinetic model is solved using frequency domain method, obtains the speed of mainshaft and axial limit cutting-in
Relation；
Step 7：Gone out using Matlab numerical simulations using machine spindle speed as abscissa, axial cutting-in is steady for ordinate
Qualitative flap figure；
Step 8：Milling Process stability prediction is carried out to the stability lobes diagram, in the point of flap figure contour area above
Under the corresponding speed of mainshaft and cutting depth machined parameters, flutter does not occur for when processing, in flap figure contour region below
Under the corresponding speed of mainshaft of point and cutting depth machined parameters, flutter can occur for when processing.
Preferably, the step 1 includes：The rotation angle of slotting cutter is set as φ, the fibrinopeptides A of unidirectional laminate
For θ, fiber cutting angle is β, then：
β=φ+θ if β >=180then β=mod (β, 180).
Preferably, the step 2 includes：It is F to measure the Milling Force, then Milling Force F is F in X-direction milling componentx；
Milling component F in the Y directiony；In the opposite F of the cutting component of Z-directionxAnd FyIt can be ignored；Milling Force F is in slotting cutter knife
The radial load in the radial direction of tool is Fr；Tangential forces of the Milling Force F in the tangential direction of end mill tool beThen vertical milling
The tangential force F of knife cuttertWith radial load FrF can be passed throughxAnd FyIt is converted to by transition matrix, is specially：
Wherein：Represent deviation angle of the radial direction force direction relative to Y-direction.
Preferably, the average Milling Force includes average radial Milling ForceAveragely tangential Milling ForceWherein：
Wherein：pRepresent axial cutting-in during slotting cutter milling；F represents the amount of feeding；φsRepresent cutter entrance angle；φeRepresent
Cutter cuts out angle；KrcAnd KreRepresent radial cutting force coefficient；KtcAnd KteRepresent tangential cutting force coefficient.
Preferably, the step 5 includes：
The milling laminate kinetic model is：
Wherein, m=k/ ω2For the equivalent mass of vibrational system,For vibrational system equivalent damping (Ns/
M), k is vibrational system equivalent stiffness, and x (t) is the dynamic displacement of end mill tool.
Preferably, the step 6 includes：
The differential equation of kinetic model, the Expression formula of the kinetic model are solved using frequency domain method：
Wherein Δ F(t)For dynamic milling educational level, KtFor the multi direction laminate Milling force parameter described in step 3, A0For average milling
Force direction coefficient matrix, Δ u(t)For the vibration displacement of tooling system；
Kinetic model based on foundation, it is assumed that the flutter frequency ω of milling laminatec, it is induced by it in X and Y-direction
Vibration displacement Δ x and Δ y are expressed as with harmonic function in frequency domain：
Wherein, Δ u(t)=[Δ x Δs y]T；τ is the swing circle of end mill tool；T is a certain moment；For end mill tool and the transfer function matrix of laminate contact area；For contact area X
The direct transmission function in direction；For the direct transmission function of contact area Y-direction；To intersect letter
Number；A is the axial cutting-in of end mill tool；I is plural number.
Compared with prior art, the present invention has following beneficial effect：
1st, the milling stability decision criteria of the invention by spindle speed and the machined parameters relation of axial cutting-in,
Machined parameters are reasonably selected, effectively prevent the vibration of Milling Process；
2nd, the present invention improves laminate surface quality, reduces end mill tool abrasion, optimizes carbon fibre composite
Milling Process process.
Brief description of the drawings
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is Milling Process of the present invention experiment measurement and cutting tool mode measuring system schematic diagram；
Fiber cutting direction angle schematic diagram when Fig. 2 is Tool in Milling laminate diverse location；
Fig. 3 is slotting cutter milling carbon fiber layer plywood kinetic model schematic diagram；
Fig. 4 is the flutter instability flap numerical simulation figure of the specific embodiment of the invention；
Fig. 5 is the milling carbon fiber layer plywood flutter stability Forecasting Methodology flow chart of the specific embodiment of the invention.
In figure：1- dynamometers；2- carbon fiber layer plywood；3- diamond coatings slotting cutters；4- modal forces are hammered into shape；5- acceleration passes
Sensor；6- data acquisition processing systems.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following embodiments will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, some changes and improvements can also be made.These belong to the present invention
Protection domain.
As shown in figure 5, a kind of flutter stability Forecasting Methodology of the milling carbon fiber layer plywood provided according to the present invention, bag
Include following steps：
Step 1：As shown in Figure 1, preferred embodiment provided by the invention, with carbon fiber layer plywood 2 for Milling Process object,
Diamond coatings slotting cutter 3 is cutter, carries out groove milling carbon fiber layer plywood 2 using CNC planer type milling machine, carbon fiber layer plywood 2 is put
Put on dynamometer 1, both ends are fixed with briquetting, and dynamometer 1 is placed on milling machine processing platform, with six different feedings
It is respectively (0.10-0.15-0.20-0.25-0.30-0.35) mm/tooth, speed of mainshaft V to measure f：3000 (rpm), axial cutting-in
ap：2 (mm) carry out milling experiment.
Step 1.1：The fibrinopeptides A θ of four kinds of carbon fiber layer plywood 2 is respectively 0 ° -45 ° -90 ° -135 °, laying
Number equal 50, material property is shown in Table 1；A diameter of 10mm of the cutter, the cutter number of teeth 2.
Table 1
Step 1.2：Unlike the metal material of milling isotropic, with the rotation of cutter, point of a knife point and workpiece
Different fiber cutting angle β is formed, from formula (1) as can be seen that its anglec of rotation of change depending on fibrinopeptides A θ and cutter
Spend φ.
β=φ+θ if β >=180then β=mod (β, 180) (1)
By taking rotating three cutting positions of cutter as an example, the size at fiber cutting angle is calculated, as shown in Figure 2.
Step 1.3：Directlyed proportional according to cutting force to the size of the area of cut to the length of tool in cutting sword, act on cutter
Radial load F on cutting edgerWith tangential force FtExpression formula be：
Wherein, φs, φeRespectively entrance angle and cut out angle, KrcAnd KreRepresent radial cutting force coefficient；KtcAnd KteRepresent
Tangential cutting force coefficient.gj(φj) it is unit jump function, for determining whether cutter tooth enters cutting.
Step 1.4：To four kinds of laminates described in step 1.1 respectively with the amount of feeding milling described in step 1, difference is measured
X-direction milling component F of the laminate of fiber angle under the processing of each amount of feedingxWith the milling component F of Y-directiony, due to cutter
Helical angle it is smaller, cause experiment measure Z-direction component it is smaller, can not consider.
Step 1.5：The component for making experiment measure X and Y-direction by transition matrix is transformed into the tangential force F of cuttertAnd footpath
To power Fr, as shown in formula (3)：
Step 1.6：Due to the tangential Milling Force that in groove milling, is averagedCan be by formula (4), in cutter entrance angle φs
=0 ° and cut out angle φe=180 ° of integrations obtain,
Step 1.7：Similarly, average radial Milling ForceExpression formula is expressed as by formula (5)：
Step 1.8：The Milling force parameter K as fiber cutting angle beta function as described in step 1.6 and step 1.7tcWith
Kte, can be by the above-mentioned steps difference amount of feeding, such as the Milling Force that is tangentially averaged measured under same 45 ° of fiber anglesPass through
It is dependent variable that formula (4), which reversely solves 6 groups of obtained data, and using f as independent variable, progress linear fit is drawn is in fiber angles
θ1Tangential cutting force coefficientWith
Step 1.9：Similarly, for radial cutting force coefficientWithIt can be obtained with repeat step 1.6.
Step 1.10：It is 0 ° for fiber angles, 90 °, 135 ° of unidirectional carbon laminate, can be with repeat step 1.6-
1.8 are calculated the Cutting Force Coefficient under respective fiber angles
Step 1.11：More studied in laboratory science of unidirectional laminate is applied, in production application, more using multidirectional
The carbon fiber face sheets of laying, due to using symmetry principle laying more, so the Milling Force of the carbon fiber face sheets for multidirectional laying
Coefficient, can use principle of stacking, the i.e. Cutting Force Coefficient (K for laminate under the laying of Single Fiber angletc、Kte, Krc、
Kre) sum-average arithmetic acquisition.
Step 2：With the carbon fiber layer plywood cutter for same described in Milling Process step 1, tested using hammering and obtain milling cutter
The frequency response function of point of a knife point.
Step 3：Analysis obtains master mode parameter, including cutter X, Y-direction from the displacement frequency response function of milling cutter point of a knife point
Intrinsic frequency (ωx, ωy), damping (ξx, ξy), rigidity (kx, ky), as shown in table 2 and table 3.
Table 2
Table 3
Step 4：Using the Cutting Force Coefficient of the diamond coatings slotting cutter milling carbon fiber layer plywood obtained described in step 1
KtcAnd Krc, based on milling Regenerative Chatter principle establish milling laminate kinetic model, as shown in Figure 3.
Wherein, m=k/ ω2For the equivalent mass (kg) of vibrational system,For vibrational system equivalent damping (N
S/m), k is vibrational system equivalent stiffness (N/m), and x (t) is the dynamic displacement of cutter.
Step 5：Solved using frequency domain method, obtain the dynamic force expression formula of kinetic model：
Wherein：ΔF(t)For dynamic milling educational level, KtFor 2 Milling force parameter of carbon fiber layer plywood, A0For average milling force direction
Coefficient matrix, Δ u(t)For the vibration displacement of tooling system.
Step 6：Based on establishing milling carbon fiber kinetic model, it is assumed that the flutter frequency ω of milling workpiecec, it is induced by it
It is expressed as in X and the vibration displacement Δ x and Δ y of Y-direction with harmonic function in frequency domain：
Wherein, Δ u(t)=[Δ x Δs y]T, τ is the swing circle of cutter, and t is a certain moment,For cutter and the transfer function matrix of workpiece contact zone,For the straight of contact area X-direction
Connect transmission function,For the direct transmission function of contact area Y-direction,To intersect function, a is cutter
Axial cutting-in, i for plural number.
Step 7：The equation (7) is substituted into (6), the characteristic equation that can obtain system is：
Therefore the value of the feature of equation is：
Wherein ΛRAnd ΛIIt is characterized the real and imaginary parts of value.
Step 8：Derived by above-mentioned steps, the expression formula of axial limit cutting-in is：
The corresponding speed of mainshaft is：
K takes 0,1,2 ...
Step 9：In known vibrational system and kinetic parameter (N, a of the cutting system of machining toole, D, ωx, ωy,
ξx, ξy, kx, ky, Kt, Kr) in the case of, alim, V can be expressed as the function of ω and k, if ω and k take different values respectively,
Corresponding V and a can so be obtainedlimValue, therefore it is abscissa that machine tool chief axis V can be simulated by Matlab, with
Axial cutting-in alimFor the stability lobes diagram of ordinate.
Step 10：The geometric parameter and modal parameter of cutter according to above step, and cutting experiment obtain it and cut
The Cutting Force Coefficient of carbon fiber layer plywood 2 is cut, processing is drawn using above step and stablizes flap figure as shown in figure 4, in flap figure
Under the corresponding speed of mainshaft of point and cutting depth machined parameters of contour area above, flutter does not occur for when processing, conversely, then
Flutter can occur.As flutter occurs on flap figure for A points (2600rpm, 4.4mm), B points (2600rpm, 2.7mm) are in flap
Flutter does not occur on figure.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or change within the scope of the claims, this not shadow
Ring the substantive content of the present invention.In the case where there is no conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (6)
1. a kind of flutter stability Forecasting Methodology of milling carbon fiber layer plywood, it is characterised in that include the following steps：
Step 1：Carried out on milling machine using slotting cutter respectively to the unidirectional laminate of different fiber angles with the different amount of feeding
Milling is tested；
Step 2：Milling Force of the unidirectional laminate of different fiber angles under the different amount of feeding is measured by measuring instrument, using flat
Equal Milling Force, the Milling force parameter of the unidirectional laminate of milling under different fiber angles is identified using linear fit；
Step 3：The Milling force parameter sum-average arithmetic of the unidirectional laminate of Single Fiber angle is obtained according to principle of stacking multidirectional
The Milling force parameter of laminate；
Step 4：The frequency response function for obtaining milling cutter point of a knife point is tested using hammering, from the displacement frequency response function of milling cutter point of a knife point minute
Analysis obtains master mode parameter, and the master mode parameter includes a second order intrinsic frequency, damping and the rigidity of cutter；
Step 5：By the Cutting Force Coefficient of multi direction laminate, the milling laminate power based on milling Regenerative Chatter principle is established
Learn model；
Step 6：The differential equation of kinetic model is solved using frequency domain method, obtains the pass of the speed of mainshaft and axial limit cutting-in
System；
Step 7：Gone out using Matlab numerical simulations using machine spindle speed as abscissa, axial cutting-in is the stability of ordinate
Flap figure；
Step 8：Milling Process stability prediction is carried out to the stability lobes diagram, is corresponded in the point of flap figure contour area above
The speed of mainshaft and cutting depth machined parameters under, flutter does not occur for when processing, in the point pair of flap figure contour region below
Under the speed of mainshaft and cutting depth machined parameters answered, flutter can occur for when processing.
2. the flutter stability Forecasting Methodology of milling carbon fiber layer plywood according to claim 1, it is characterised in that described
Step 1 includes：The rotation angle of slotting cutter is set as φ, the fibrinopeptides A of unidirectional laminate is θ, and fiber cutting angle is β,
Then：
Then β=the mod (β, 180) of β=φ+θ if β >=180.
3. the flutter stability Forecasting Methodology of milling carbon fiber layer plywood according to claim 1, it is characterised in that described
Step 2 includes：It is F to measure the Milling Force, then Milling Force F is F in X-direction milling componentx；Milling component F in the Y directiony；
In the opposite F of the cutting component of Z-directionxAnd FyIt can be ignored；Radial directions in the radial direction of the Milling Force F in end mill tool
Power is Fr；Tangential forces of the Milling Force F in the tangential direction of end mill tool beThe then tangential force F of end mill tooltAnd footpath
To power FrF can be passed throughxAnd FyIt is converted to by transition matrix, is specially：
Wherein：Represent deviation angle of the radial direction force direction relative to Y-direction.
4. the flutter stability Forecasting Methodology of milling carbon fiber layer plywood according to claim 3, it is characterised in that described
Average Milling Force includes average radial Milling ForceAveragely tangential Milling ForceWherein：
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Wherein：apRepresent axial cutting-in during slotting cutter milling；F represents the amount of feeding；φsRepresent cutter entrance angle；φeRepresent knife
Tool cuts out angle；KrcAnd KreRepresent radial cutting force coefficient；KtcAnd KteRepresent tangential cutting force coefficient.
5. the flutter stability Forecasting Methodology of milling carbon fiber layer plywood according to claim 1, it is characterised in that described
Step 5 includes：
The milling laminate kinetic model is：
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Wherein, m=k/ ω2For the equivalent mass of vibrational system,For vibrational system equivalent damping (Ns/m), k is
Vibrational system equivalent stiffness, x (t) are the dynamic displacement of end mill tool.
6. the flutter stability Forecasting Methodology of milling carbon fiber layer plywood according to claim 1, it is characterised in that described
Step 6 includes：
The differential equation of kinetic model, the Expression formula of the kinetic model are solved using frequency domain method：
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Wherein Δ F(t)For dynamic milling educational level, KtFor the multi direction laminate Milling force parameter described in step 3, A0For average Milling Force side
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Kinetic model based on foundation, it is assumed that the flutter frequency ω of milling laminatec, it is induced by it the vibration in X and Y-direction
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Wherein, Δ u(t)=[Δ x Δs y]T；τ is the swing circle of end mill tool；T is a certain moment；For end mill tool and the transfer function matrix of laminate contact area；For contact area X side
To direct transmission function；For the direct transmission function of contact area Y-direction；To intersect function；a
For the axial cutting-in of end mill tool；I is plural number.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711271399.7A CN107914183B (en) | 2017-12-05 | 2017-12-05 | Chatter stability prediction method for milling carbon fiber laminated plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711271399.7A CN107914183B (en) | 2017-12-05 | 2017-12-05 | Chatter stability prediction method for milling carbon fiber laminated plate |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107914183A true CN107914183A (en) | 2018-04-17 |
| CN107914183B CN107914183B (en) | 2020-04-07 |
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| CN110377940A (en) * | 2019-06-10 | 2019-10-25 | 大连理工大学 | A method of obtaining CFRP workpiece milling vibration amplitude |
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| CN110750891A (en) * | 2019-10-12 | 2020-02-04 | 北京理工大学 | Parallel synchronous orthogonal turning and milling flutter stability lobe graph prediction method |
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| CN112380726A (en) * | 2020-11-26 | 2021-02-19 | 华中科技大学无锡研究院 | Robot milling critical stable cutting depth prediction method based on modal coupling chatter |
| CN115570160A (en) * | 2022-06-22 | 2023-01-06 | 湖南工业大学 | Slender shaft turning flutter stability prediction method with follow-up tool rest |
| CN114850547A (en) * | 2022-07-11 | 2022-08-05 | 成都飞机工业（集团）有限责任公司 | Carbon fiber member contour milling damage inhibition method |
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| CN115945725A (en) * | 2023-03-09 | 2023-04-11 | 齐鲁工业大学(山东省科学院) | Six-degree-of-freedom robot milling stability prediction method and system |
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